# @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 FASTENER HOLES AT FRAME 40 VERTICAL WEB ABOVE CENTER WING BOX LOWER PANEL **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES The ALI 57.11.02 was initiated after crack findings in Frame 40 Front Fitting during FSFT (Full Scale Fatigue Test). Recently it appears necessary to modify this inspection due to the availability of in service findings in the Frame 40 Rear Fitting. The latter were discovered thanks to the HF/EC Rototest inspections done during the embodiment of the modification 52094S17923 through recommended Service Bulletin No. A330-57-3083 which has pre-modification 44360S13013 and 44360S13482 and post-modification 44360S13013 and 44360S13482 - pre-modification 49202S16307 effectivity. This Service Bulletin mandates the Inspection of the fasteners holes at Frame 40 Vertical Web - above Center Wing Box lower panel, left and right sides for all A330 aircraft pre-modification 55306S18660 and 55792S18775 embodiments. The aim of this Inspection Service Bulletin is to implement the corrective inspection necessary to the in-service aircraft. For aircraft on which FR40 web is already repaired on one side or on both sides as per Repair Instruction R57115092, Inspection task of this ISB is not valid for the repaired side(s); dedicated RDAS instructions have to be followed. For aircraft previously inspected as per Technical Disposition ref. LR57D11029170, LR57D11023714, LR57D11029172 or LR57D11030740, next inspection is due based on ISB 57-3115 interval value or dedicated RDAS instruction requirements in case of deviation to the Technical Disposition instructions. Accomplishment of this ISB will permit early detection of cracks on the FR40 Vertical web above Center Wing Box lower panel, left and right sides and will contribute to maintain the structural integrity of the area.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 1 5

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# @A330 SERVICE BULLETIN SUMMARY The Task ALI 57-11-02 applicable to aircraft Post modifications 44360S13013 and 44360S13482 , Pre modification 55306S18660 and Pre modification 55792S18775 will be superseded by accomplishment of Service Bulletin No. A330-57-3115. 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 573115A01R02 2 4,100.00 Screws, Washers, Nuts Kit 573115A02R02 2 3,600.00 Screws, Washers, Nuts TOTAL 7,700.00 **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 573115A01R02 2 4,100.00 Screws, Washers, Nuts Kit 573115A03R02 2 3,100.00 Screws, Washers, Nuts TOTAL 7,200.00 **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 573115A01R02 2 4,100.00 Screws, Washers, Nuts Kit 573115A04R03 2 2,100.00 Screws, Washers, Nuts TOTAL 6,200.00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 2 5

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# @A330 SERVICE BULLETIN SUMMARY **CONF 004 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 573115A01R02 2 4,100.00 Screws, Washers, Nuts Kit 573115A05R02 2 4,500.00 Screws, Washers, Nuts TOTAL 8,600.00 **CONF 005 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 573115A06R03 2 5,900.00 Screws, Washers, Nuts **CONF 006 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 573115A06R03 2 5,900.00 Screws, Washers, Nuts **CONF 007 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 573115A06R03 2 5,900.00 Screws, Washers, Nuts EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

38W AAR ACA ACI AEA AFR ALK ASY AZA BEL BER BMA BTV C9G CAL CCA CES CPA CRL CSC CSN DAH DAL DGA DLH EDW EIN ETD EVA FWI GFA GIA GRL HDA HFY HVN I2L IAC ISS IWD IYE JAV JST KAL KLM MAS MON MSR OHY PAL QAF QFA QTR RSY RYN SAI SAS TAM TAP TCX THA THY TSC UAE USA VKG VOZ XAX XLF CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 57.11.00.007 OEB None DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 3 5

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# @A330 SERVICE BULLETIN SUMMARY AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER OIT ref. 999.0086/11 and 999.0082/12 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 573115-832-801-001: Inspection TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 Task 573115-833-801-001: Repair TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 **CONF 002 Task 573115-832-801-001: Inspection TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 Task 573115-833-801-001: Repair TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 **CONF 003 Task 573115-832-801-001: Inspection TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 Task 573115-833-801-001: Repair TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 4 5

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# @A330 SERVICE BULLETIN SUMMARY **CONF 004 Task 573115-832-801-001: Inspection TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 Task 573115-833-801-001: Repair TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 **CONF 005 Task 573115-832-801-001: Inspection TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 Task 573115-833-801-001: Repair TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 **CONF 006 Task 573115-832-801-001: Inspection TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 Task 573115-833-801-001: Repair TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 **CONF 007 Task 573115-832-801-001: Inspection TOTAL MANHOURS 38.00 ELAPSED TIME (HOURS) 38.00 Task 573115-833-801-001: Repair TOTAL MANHOURS 42.50 ELAPSED TIME (HOURS) 42.50 APPENDICES **CONF ALL Appendix 01 : Inspection Report

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 5 5

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# @A330 SERVICE BULLETIN SUMMARY

**CONF ALL FR47

FR40

FR40 

### B
**B** 

## A

**B** LH SIDE SHOWN RH SIDE SYMMETRICAL **NOTE:** HOLE OF THE AREA A TO BE INSPECTED 

### A

HOLES OF THE AREA B TO BE INSPECTED STGR38

STGR39

STGR40 STGR37 H263 H260 H262 H261

H14 H22 H21 H13 H12

VIEW LOOKING AFT − Z141 Z142

H23 H24 CENTER WING BOX LOWER PANEL REFERENCE

AREA HOLE NUMBER 12, 13, 14, 21, 22, 23, B 260 A 24, 261, 262, 263

G_SB_573115_5_SAAA_01_04 Figure A-FSAAA - Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 6 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 FASTENER HOLES AT FRAME 40 VERTICAL WEB ABOVE CENTER WING BOX LOWER PANEL 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: This Service Bulletin is applicable only to aircraft on which Mod. No. 55306S18660 (REPLACE THE ONE-PIECE FITTING BY A SPLICE AND AN ANGLE AT FR.40 (ADAPTATION SOLUTION)) and Mod. No. 55792S18775 (REINFORCE FUSELAGE AT FR40 (SERIAL SOLUTION)) are not embodied. (1) Models 330-202 330-203 330-223 330-243 330-301 330-302 330-303 330-321 330-322 330-323 330-341 330-342 330-343 (2) Effectivity by MSN 0012 0017 0030 0037 0045 0050 0054-0055 0060 0062 0064-0066 0070-0072 0077 0082-0083 0086-0087 0095-0096 0098-0099 0102 0106-0107 0109 0111-0113 0116 0118-0122 0127 0132 0138 0140 0143-0144 0148 0153 0155 0162 0165 0171-0172 0177 0181 0183-0184 0188-0189 0191 0195 0198 0200 0203 0205-0206 0209 0211 0219 0222-0224 0226 0229-0232 0234 0238 0240-0241 0244 0247-0251 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 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 1 5

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# @A330 SERVICE BULLETIN

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 0500-0513 0515-0516 0518-0519 0521-0522 0524-0527 0529-0530 0532-0533 0535-0536 0539 0542 0548-0553 0555 0558 0564-0565 0567-0568 0570-0571 0573-0574 0576 0578-0579 0581 0584 0587-0588 0591 0593 0595 0597 0600 0602-0603 0605 0607 0609-0610 0612 0614 0616 0618 0620-0621 0623 0625 0627 0629 0631-0638 0640-0642 0644-0645 0647-0650 0652-0659 0661-0667 0669-0671 0673-0676 0678-0680 0682-0684 0686-0688 0690-0693 0695-0697 0699-0701 0703-0705 0707-0709 0711-0714 0716-0718 0720-0722 0724-0726 0728-0730 0732-0735 0737-0739 0741-0743 0745-0747 0749-0752 0754-0756 0758-0760 0769-0770 0772-0774 0776-0778 0780-0782 0784-0786 0788-0789 0791-0792 0795-0797 0799 0801-0803 0805-0807 0809-0811 0813-0815 0817-0823 0826 (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 AAR 0640 0676 0708 0772 0803 ACA 0277 0279 0284 0344 0400 0408 0412 0419 ACI 0507 0510 AEA 0505 0526 0551 0597 0733 0745 0749 0814 AFR 0422 0443 0448 0458 0465 0481 0498 0500 0502 0503 0516 0519 0567 0584 0657 ALK 0303 0306 0311 0313 0404 0456 0627 ASY 0747 AZA 0272 0339 BEL 0030 0037 0045 0082 0095 0229 0249 0324 BER 0288 0322 0403 0432 0444 0454 0469 0476 0493 0665 0739 BMA 0398 BTV 0205 0330 C9G 0461 CAL 0602 0607 0641 0671 0675 0691 0699 0707 0714 0725 0752 0769 0805 0823 CCA 0750 0756 0759 0780 0785 0797 0810 0815 CES 0713 0720 0728 0732 0735 0773 0777 0781 0782 0791 0821 CPA 0012 0102 0113 0118 0121 0155 0386 0389 0393 0418 0420 0421 0423 0439 0539 0548 0565 0669 0673 0679 0776 CRL 0285 0320 CSC 0462 CSN 0649 0652 0656 0664 0818 DAH 0644 0647 0650 0653 0667 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 2 5

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# @A330 SERVICE BULLETIN

OPERATOR MSN DAL 0524 0533 0542 0549 0552 0578 0588 0591 0609 0614 0618 0620 0621 0631 0633 0663 0674 0690 0718 0722 0778 0784 0796 0799 0806 0817 DGA 0240 DLH 0570 0576 0579 0629 0636 0642 0645 0648 0687 0701 EDW 0291 EIN 0269 0397 ETD 0658 0688 0717 0724 0729 0730 0737 0751 0788 0807 0809 EVA 0530 0535 0555 0573 0587 0634 0655 0661 0678 0693 0755 FWI 0253 0758 GFA 0276 0281 0286 0287 0334 0340 0532 GIA 0138 0140 0144 0148 0153 0165 GRL 0230 HDA 0017 0071 0083 0099 0106 0109 0234 0244 0405 0479 0512 0581 0654 0662 0692 0716 0741 0786 HFY 0096 0127 0211 0262 HVN 0275 0294 0299 0366 I2L 0358 0364 0527 0529 0822 IAC 0353 0362 ISS 0802 IWD 0670 IYE 0625 0632 JAV 0255 JST 0506 0508 0513 0522 KAL 0162 0172 0206 0219 0222 0226 0241 0256 0258 0267 0338 0350 0351 0368 0425 0428 0484 0490 0550 KLM 0682 0686 0703 0738 0770 0801 0811 0819 MAS 0077 0107 0116 0119 0290 0296 0300 MON 0261 0265 MSR 0600 0610 0666 0683 0696 0709 0726 OHY 0072 0087 0098 0143 PAL 0183 0184 0188 0189 0191 0198 0200 0203 QAF 0487 0605 QFA 0553 0558 0564 0574 0593 0595 0603 0695 0705 0712 QTR 0441 0473 0489 0511 0521 0571 0612 0616 0623 0637 0638 0659 0680 0684 0711 0721 0734 0743 0746 0760 0789 0792 0813 0820 0826 RSY 0120 0171 RYN 0343 SAI 0055 0070 0086 SAS 0496 0497 0515 0568 TAM 0232 0238 0247 0259 0361 0466 0472 0477 0486 0700 TAP 0181 0195 0223 0305 0308 0312 0317 TCX 0254 0266 0301 THA 0050 0060 0062 0064 0065 0066 0112 0122 0209 0224 0231 0346 THY 0463 0504 0697 0704 0742 0754 0774 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 3 5

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# @A330 SERVICE BULLETIN

OPERATOR MSN TSC 0111 0132 0177 0250 0271 0369 0407 0427 0480 0795 UAE 0248 0251 0283 0293 0295 0314 0316 0326 0328 0345 0348 0382 0384 0392 0396 0409 0437 0451 0452 0455 0491 0494 0509 0518 0525 0536 USA 0315 0323 0333 0337 0342 0370 0375 0380 0388 VKG 0309 0349 0356 0357 VOZ 0365 0372 XAX 0054 XLF 0501 0635 (4) Configuration by MSN MSN CONFIGURATION 0012 0017 0030 0037 0045 0050 0054 0055 0060 0062 0064 0065 0066 0070 0071 0072 0077 0082 0083 0086 0087 0095 0096 0098 0099 0102 0106 0107 0109 0111 0112 001
0113 0116 0118 0119 0120 0121 0122 0127 0132 002 0138 0140 0143 0144 0155 004 0148 0153 0162 0165 0171 0172 003 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 005

0511 006

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 4 5

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# @A330 SERVICE BULLETIN

MSN CONFIGURATION 0513 0515 0516 0518 0519 0521 0524 0525 0526 0527 0529 0530 0532 0533 0535 0536 0539 0542 0548 0549 0550 0551 0552 0553 0555 0558 0564 0565 0567 0568 0570 0571 0573 0574 0576 0578 0579 0581 0584 0587 0588 0591 0593 0595 0597 0600 0602 0603 0605 0607 0609 0610 0612 0614 0616 0618 0620 0621 0623 0625 0627 0629 0631 0632 0633 0634 0635 0636 0637 0638 0640 0641 0642 0644 0645 0647 0648 0649 0650 0652 0653 0654 0655 0656 0657 0658 0659 0661 0662 0663 0664 0665 0666 0667 0669 0670 0671 0673 0674 0675 0676 0678 0679 0680 0682 0683 0684 0686 0687 0688 0690 0691 0692 0693 0695 0696 0697 0699 0700 0701 0703 0704 0705 0707 0708 0709 0711 0712 0713 0714 0716 0717 0718 0720 0721 0722 0724 0725 0726 0728 0729 0730 0732 0733 0734 0735 0737 0738 0739 0741 0742 0743 0745 0746 0747 0749 0750 0751 0752 0754 0755 0756 0758 0759 0760 0769 0770 0772 0773 0774 0776 0777 0778 0780 0781 0782 0784 0785 0786 0788 0789 0791 0792 0795 0796 0797 0799 0801 0802 0803 0805 0806 0807 0809 0810 0811 0813 0814 0815 0817 0818 0819 0820 0821 0822 0823 0826 007

(5) Configuration definition **CONF 001 Config. 001 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND FRONT SPAR (ADAPTATION SOLUTION)), Mod No. 41652S11819 (INTRODUCE A340 COMMONALITY ITEMS) and Mod No. 44360S13482 (MODIFY FR40 AND FRONT SPAR (SERIAL SOLUTION)) are not embodied and on which Service Bulletin No. A330-57-3032 is accomplished (or Mod No. 43577S12677 (MODIFY LOWER KEEL FITTING AND FORWARD LOWER SHELL CONNECT.(RETROFIT SOLUTION VIA SB ONLY)) is embodied). **CONF 002 Config. 002 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND FRONT SPAR (ADAPTATION SOLUTION)) and Mod No. 44360S13482 (MODIFY FR40 AND FRONT SPAR (SERIAL SOLUTION)) are not embodied and Mod No. 41652S11819 (INTRODUCE A340 COMMONALITY ITEMS) is embodied and on which Service Bulletin No. A330-57-3046 is accomplished (or Mod No. 44440S13324 (REINFORCE KEEL ANGLE OF FRONT SPAR (RETROFIT SOLUTION)) is embodied). **CONF 003 Config. 003 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND FRONT SPAR (ADAPTATION SOLUTION)) and Mod No. 44360S13482 (MODIFY FR40 AND FRONT SPAR (SERIAL SOLUTION)) are not embodied and on which Mod No. 44440S13090 (MODIFY LOWER KEEL FITTING AND FWD LOWER SHELL CONNECTION (SERIAL SOLUTION))and Mod No. 41652S11819 (INTRODUCE A340 COMMONALITY ITEMS) are embodied.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 5 5

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# @A330 SERVICE BULLETIN
**CONF 004 Config. 004 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND FRONT SPAR (ADAPTATION SOLUTION)) and Mod No. 44360S13482 (MODIFY FR40 AND FRONT SPAR (SERIAL SOLUTION)) are not embodied and on which Mod No. 44440S13276 (REINFORCE LOWER KEEL ANGLE OF FRONT SPAR (ADAPTATION SOLUTION)) and Mod No. 41652S11819 (INTRODUCE A340 COMMONALITY ITEMS) are embodied. **CONF 005 Config. 005 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND FRONT SPAR (ADAPTATION SOLUTION)), Mod No. 44360S13482 (MODIFY FR40 AND FRONT SPAR (SERIAL SOLUTION)) and Mod No.41652S11819 (INTRODUCE A340 COMMONALITY ITEMS) are embodied and on which Mod No. 49202S16307 (REINFORCE SECTION 15/21) is not embodied. **CONF 006 Config. 006 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND FRONT SPAR (ADAPTATION SOLUTION)), Mod No. 44360S13482 (MODIFY FR40 AND FRONT SPAR (SERIAL SOLUTION)), Mod No. 50755S16633 (REDUCE APPLICATION OF MOD 49194 AND 49202), Mod No. 49202S16307 (REINFORCE SECTION 15/21) and Mod No. 41652S11819 (INTRODUCE A340 COMMONALITY ITEMS) are embodied. **CONF 007 Config. 007 is valid for aircraft on which Mod No. 44360S13013 (MODIFY FR40 AND FRONT SPAR (ADAPTATION SOLUTION)), Mod No. 44360S13482 (MODIFY FR40 AND FRONT SPAR (SERIAL SOLUTION)), Mod No. 41652S11819 (INTRODUCE A340 COMMONALITY ITEMS) and Mod No. 49202S16307 (REINFORCE SECTION 15/21) are embodied and on which Mod No. 55306S18660 (REPLACE THE ONE-PIECE FITTING BY A SPLICE AND AN ANGLE AT FR.40 (ADAPTATION SOLUTION)) and Mod No. 55792S18775 (REINFORCE FUSELAGE AT FR40 (SERIES AIRCRAFT)) are not embodied. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 573115A01R02 2 Kit 573115A02R02 2 Consumable CMLA01 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 573115A01R02 2 Kit 573115A03R02 2 Consumable CMLA01 1

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 6 5

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# @A330 SERVICE BULLETIN
**CONF 003 MATERIAL QTY PER A/C SEE NOTES Kit 573115A01R02 2 Kit 573115A04R03 2 Consumable CMLA01 1 **CONF 004 MATERIAL QTY PER A/C SEE NOTES Kit 573115A01R02 2 Kit 573115A05R02 2 Consumable CMLA01 1 **CONF 005 thru 007 MATERIAL QTY PER A/C SEE NOTES Kit 573115A06R03 2 Consumable CMLA01 1 **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON (1) History The ALI 57.11.02 was initiated after crack findings in Frame 40 Front Fitting during FSFT (Full Scale Fatigue Test). Recently it appears necessary to modify this inspection due to the availability of in service findings in the Frame 40 Rear Fitting. The latter were discovered thanks to the HF/EC Rototest inspections done during the embodiment of the modification 52094S17923 through recommended Service Bulletin No. A330-57-3083 which has pre-modification 44360S13013 and 44360S13482 and post-modification 44360S13013 and 44360S13482 - pre-modification 49202S16307 effectivity. (2) Objective/Action This Service Bulletin mandates the Inspection of the fasteners holes at Frame 40 Vertical Web - above Center Wing Box lower panel, left and right sides for all A330 aircraft pre-modification 55306S18660 and 55792S18775 embodiments. The aim of thisInspection Service Bulletin is to implement the corrective inspection necessary to the inservice aircraft. For aircraft on which FR40 web is already repaired on one side or on both sides as per Repair Instruction R57115092, Inspection task of this ISB is not valid for the repaired side(s); dedicated RDAS instructions have to be followed.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 7 5

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# @A330 SERVICE BULLETIN For aircraft previously inspected as per Technical Disposition ref. LR57D11029170, LR57D11023714, LR57D11029172 or LR57D11030740, next inspection is due based on ISB 57-3115 interval value or dedicated RDAS instruction requirements in case of deviation to the Technical Disposition instructions. (3) Advantages Accomplishment of this ISB will permit early detection of cracks on the FR40 Vertical web above Center Wing Box lower panel, left and right sides and will contribute to maintain the structural integrity of the area. (4) Operational/Maintenance Consequences The Task ALI 57-11-02 applicable to aircraft Post modifications 44360S13013 and 44360S13482 , Pre modification 55306S18660 and Pre modification 55792S18775 will be superseded by accomplishment of Service Bulletin No. A330-57-3115. D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 573115-832-801-001: Inspection (1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side (2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side (3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side (4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side (5) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side (6) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side (7) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side (8) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side (9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side (10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 8 5

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# @A330 SERVICE BULLETIN Task 573115-833-801-001: Repair (1) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (2) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (3) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (4) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (5) Install New same Fasteners of the Area B in transition fit, LH Side (6) Install New same Fasteners of the Area B in transition fit, RH Side (7) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side (8) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side (9) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side (10) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side (11) Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side (12) Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side (13) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (14) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (15) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (16) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (17) Install New Fasteners of the Area B in transition fit, LH Side (18) Install New Fasteners of the Area B in transition fit, RH Side

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 9 5

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# @A330 SERVICE BULLETIN
**CONF 002 Task 573115-832-801-001: Inspection (1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side (2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side (3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side (4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side (5) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side (6) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side (7) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side (8) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side (9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side (10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side Task 573115-833-801-001: Repair (1) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (2) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (3) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (4) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (5) Install New same Fasteners of the Area B in transition fit, LH Side (6) Install New same Fasteners of the Area B in transition fit, RH Side (7) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side (8) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 10 5

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# @A330 SERVICE BULLETIN Oversize in comparison with the current hole diameter, RH Side (9) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side (10) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side (11) Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side (12) Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side (13) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (14) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (15) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (16) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (17) Install New Fasteners of the Area B in transition fit, LH Side (18) Install New Fasteners of the Area B in transition fit, RH Side **CONF 003 Task 573115-832-801-001: Inspection (1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side (2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side (3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side (4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side (5) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side (6) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side (7) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 11 5

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# @A330 SERVICE BULLETIN (8) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side (9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side (10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side Task 573115-833-801-001: Repair (1) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (2) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (3) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (4) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (5) Install New same Fasteners of the Area B in transition fit, LH Side (6) Install New same Fasteners of the Area B in transition fit, RH Side (7) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side (8) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side (9) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side (10) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side (11) Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side (12) Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side (13) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (14) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (15) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (16) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 12 5

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# @A330 SERVICE BULLETIN (17) Install New Fasteners of the Area B in transition fit, LH Side (18) Install New Fasteners of the Area B in transition fit, RH Side **CONF 004 Task 573115-832-801-001: Inspection (1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side (2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side (3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side (4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side (5) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side (6) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side (7) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side (8) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side (9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side (10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side Task 573115-833-801-001: Repair (1) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (2) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (3) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (4) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (5) Install New same Fasteners of the Area B in transition fit, LH Side (6) Install New same Fasteners of the Area B in transition fit, RH Side DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 13 5

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# @A330 SERVICE BULLETIN (7) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side (8) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side (9) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side (10) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side (11) Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side (12) Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side (13) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (14) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (15) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (16) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (17) Install New Fasteners of the Area B in transition fit, LH Side (18) Install New Fasteners of the Area B in transition fit, RH Side **CONF 005 Task 573115-832-801-001: Inspection (1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side (2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side (3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side (4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side (5) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side (6) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 14 5

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# @A330 SERVICE BULLETIN
Area A of the Frame 40, RH Side (7) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side (8) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side (9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side (10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side Task 573115-833-801-001: Repair (1) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (2) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (3) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (4) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (5) Install New same Fasteners of the Area B in transition fit, LH Side (6) Install New same Fasteners of the Area B in transition fit, RH Side (7) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side (8) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side (9) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side (10) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side (11) Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side (12) Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side (13) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (14) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 15 5

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# @A330 SERVICE BULLETIN (15) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (16) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (17) Install New Fasteners of the Area B in transition fit, LH Side (18) Install New Fasteners of the Area B in transition fit, RH Side **CONF 006 Task 573115-832-801-001: Inspection (1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side (2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side (3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side (4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side (5) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side (6) Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side (7) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side (8) Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side (9) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side (10) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side Task 573115-833-801-001: Repair (1) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (2) Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (3) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (4) Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 16 5

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# @A330 SERVICE BULLETIN
transition fit, RH Side (5) Install New same Fasteners of the Area B in transition fit, LH Side (6) Install New same Fasteners of the Area B in transition fit, RH Side (7) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side (8) Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side (9) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side (10) Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side (11) Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side (12) Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side (13) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (14) Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (15) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side (16) Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side (17) Install New Fasteners of the Area B in transition fit, LH Side (18) Install New Fasteners of the Area B in transition fit, RH Side **CONF 007 Task 573115-832-801-001: Inspection (1) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side (2) Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side (3) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side (4) Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 17 5

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# @A330 SERVICE BULLETIN
Side (5) Do a Rototest Inspection of the Hole of the Area A of the Frame 40, LH Side (6) Do a Rototest Inspection of the Hole of the Area A of the Frame 40, RH Side (7) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side (8) Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side Task 573115-833-801-001: Repair (1) Install New same Fastener of the Area A in transition fit, LH Side (2) Install New same Fastener of the Area A in transition fit, RH Side (3) Install New same Fasteners of the Area B in transition fit, LH Side (4) Install New same Fasteners of the Area B in transition fit, RH Side (5) Oversize the Hole of the Area A to First Oversize in comparison with the current hole diameter, LH Side (6) Oversize the Hole of the Area A to First Oversize in comparison with the current hole diameter, RH Side (7) Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side (8) Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side (9) Install New Fastener of the Area A in transition fit, LH Side (10) Install New Fastener of the Area A in transition fit, RH Side (11) Install New Fasteners of the Area B in transition fit, LH Side (12) Install New Fasteners of the Area B in transition fit, RH Side **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 18 5

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# @A330 SERVICE BULLETIN (2) Accomplishment Timescale **CONF 001 Table 1: Rototest Inspection of the Fastener Hole of the Area A at FR 40, LH and RH Sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Do a Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-003 001 for LH Side and to SUBTASK 573115-832-009 001 for RH Side Refer to Table 3

Or Apply Service Bulletin No. A330-57-3083 and Before next flight None None Config. 001 Pre Service Bulletin No. A330-57-3083

Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

Config. 001 Post Service Bulletin No. A330-57-3083 Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 19 5

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# @A330 SERVICE BULLETIN
Table 2: Rototest Inspection of the Fasteners Holes of the Area B at FR 40, LH and RH Sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval
Config. 001 Do a Rototest Inspection of the Holes on LH and RH Sides, refer to SUBTASK 573115-832-010 002 for LH Side and to SUBTASK 573115-832-011 002 for RH Side Refer to Table 5

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Config. 001 Pre Service Bulletin No. A330-57-3083 Do a Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-003 001 for LH Side and to SUBTASK 573115-832-009 001 for RH Side FC optimized set: 17,400 FC/57,100 FH or FH optimized set: 13,800 FC/93,700 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 20 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New same Fastener Pre SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-001 004 for LH Side and/or to SUBTASK 573115-833-010 002 for RH Side and Before next flight None None

Repeat the Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-003 001 for LH Side and/or to SUBTASK 573115-832-009 001 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

Or Apply Service Bulletin No. A330-57-3083 and Before next flight None None No crack found

Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 21 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the Hole Pre SB No. A330-57-3083 to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-004 001 for LH Side and/or to SUBTASK 573115-833-014 001 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 22 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New Fastener Pre SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-007 001 for LH Side and/or to SUBTASK 573115-833-018 001 for RH Side and Before next flight None None No Crack found after rototest inspection

Repeat the Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-003 001 for LH Side and/or to SUBTASK 573115-832-009 001 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 23 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Config. 001 Post Service Bulletin No. A330-57-3083 Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side FC optimized set: 26,000 FC/85,100 FH or FH optimized set: 20,500 FC/138,700 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

Install New same Fastener Post SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-002 001 for LH Side and/or to SUBTASK 573115-833-011 001 for RH Side and Before next flight None None No crack found

Repeat the Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 24 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the Hole Post SB No. A330-57-3083 to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-005 001 for LH Side and/or to SUBTASK 573115-833-015 001 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 25 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New Fastener Post SB 57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-008 001 for LH Side and/or to SUBTASK 573115-833-019 001 for RH Side and Before next flight None None No Crack found after rototest inspection

Repeat the Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 26 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Config. 001 Do a Rototest Inspection of the Holes on LH and RH Sides, refer to SUBTASK 573115-832-010 002 for LH Side and to SUBTASK 573115-832-011 002 for RH Side FC optimized set: 17,400 FC/57,100 FH or FH optimized set: 13,800 FC/ 93,700 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

Install New same Fasteners in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-022 002 for LH Side and/or to SUBTASK 573115-833-013 002 for RH Side and Before next flight None None No crack found

Repeat the Rototest Inspection of the Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 002 for LH Side and/or to SUBTASK 573115-832-011 002 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 27 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the Holes to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-023 002 for LH Side and/or to SUBTASK 573115-833-017 002 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection Contact Airbus Before next flight None None Install New Fasteners in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-024 002 for LH Side and/or to SUBTASK 573115-833-021 002 for RH Side and Before next flight None None No Crack found after rototest inspection

Repeat the Rototest Inspection of the Fastener Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 002 for LH Side and/or to SUBTASK 573115-832-011 002 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 28 5

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

# @A330 SERVICE BULLETIN 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 and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF 002 Table 1: Rototest Inspection of the Fastener Hole of the Area A at FR 40, LH and RH Sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Do a Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-003 003 for LH Side and to SUBTASK 573115-832-009 003 for RH Side Refer to Table 3

Or Apply Service Bulletin No. A330-57-3083 and Before next flight None None Config. 002 Pre Service Bulletin No. A330-57-3083

Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

Config. 002 Post Service Bulletin No. A330-57-3083 Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 29 5

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# @A330 SERVICE BULLETIN
Table 2: Rototest Inspection of the Fasteners Holes of the Area B at FR 40, LH and RH Sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval
Config. 002 Do a Rototest Inspection of the Holes on LH and RH Sides, refer to SUBTASK 573115-832-010 001 for LH Side and to SUBTASK 573115-832-011 001 for RH Side Refer to Table 5

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Config. 002 Pre Service Bulletin No. A330-57-3083 Do a Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-003 003 for LH Side and to SUBTASK 573115-832-009 003 for RH Side FC optimized set: 17,400 FC/57,100 FH or FH optimized set: 13,800 FC/93,700 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 30 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New same Fastener Pre SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-001 001 for LH Side and/or to SUBTASK 573115-833-010 001 for RH Side and Before next flight None None

Repeat the Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-003 003 for LH Side and/or to SUBTASK 573115-832-009 003 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

Or Apply Service Bulletin No. A330-57-3083 and Before next flight None None No crack found

Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 31 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the Hole Pre SB No. A330-57-3083 to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-004 001 for LH Side and/or to SUBTASK 573115-833-014 001 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 32 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New Fastener Pre SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-007 001 for LH Side and/or to SUBTASK 573115-833-018 001 for RH Side and Before next flight None None No Crack found after rototest inspection

Repeat the Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-003 003 for LH Side and/or to SUBTASK 573115-832-009 003 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 33 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Config. 002 Post Service Bulletin No. A330-57-3083 Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side FC optimized set: 26,000 FC/85,100 FH or FH optimized set: 20,500 FC/138,700 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

Install New same Fastener Post SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-002 001 for LH Side and/or to SUBTASK 573115-833-011 001 for RH Side and Before next flight None None No crack found

Repeat the Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 34 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the Hole Post SB No. A330-57-3083 to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-005 001 for LH Side and/or to SUBTASK 573115-833-015 001 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 35 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New Fastener Post SB 57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-008 001 for LH Side and/or to SUBTASK 573115-833-019 001 for RH Side and Before next flight None None No Crack found after rototest inspection

Repeat the Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 36 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Config. 002 Do a Rototest Inspection of the Holes on LH and RH Sides, refer to SUBTASK 573115-832-010 001 for LH Side and to SUBTASK 573115-832-011 001 for RH Side FC optimized set: 17,400 FC/57,100 FH or FH optimized set: 13,800 FC/ 93,700 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

Install New same Fasteners in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-022 001 for LH Side and/or to SUBTASK 573115-833-013 001 for RH Side and Before next flight None None No crack found

Repeat the Rototest Inspection of the Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 001 for LH Side and/or to SUBTASK 573115-832-011 001 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 37 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the Holes to First Oversize in comparison with the current holes diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-023 001 for LH Side and/or to SUBTASK 573115-833-017 001 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection Contact Airbus Before next flight None None Install New Fasteners in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-024 001 for LH Side and/or to SUBTASK 573115-833-021 001 for RH Side and Before next flight None None No Crack found after rototest inspection

Repeat the Rototest Inspection of the Fastener Holes of the Fasteners Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 001 for LH Side and/or to SUBTASK 573115-832-011 001 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 38 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11). 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 and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF 003 Table 1: Rototest Inspection of the Fastener Hole of the Area A at FR 40, LH and RH Sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Do a Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-003 004 for LH Side and to SUBTASK 573115-832-009 004 for RH Side Refer to Table 3

Or Apply Service Bulletin No. A330-57-3083 and Before next flight None None Config. 003 Pre Service Bulletin No. A330-57-3083

Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 39 5

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# @A330 SERVICE BULLETIN
Table 1: Rototest Inspection of the Fastener Hole of the Area A at FR 40, LH and RH Sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval
Config. 003 Post Service Bulletin No. A330-57-3083 Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

Table 2: Rototest Inspection of the Fasteners Holes of the Area B at FR 40, LH and RH Sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval
Config. 003 Do a Rototest Inspection of the Holes on LH and RH Sides, refer to SUBTASK 573115-832-010 003 for LH Side and to SUBTASK 573115-832-011 003 for RH Side Refer to Table 5

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 40 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Config. 003 Pre Service Bulletin No. A330-57-3083 Do a Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-003 004 for LH Side and to SUBTASK 573115-832-009 004 for RH Side FC optimized set: 17,400 FC/57,100 FH or FH optimized set: 13,800 FC/93,700 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 41 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New same Fastener Pre SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-001 005 for LH Side and/or to SUBTASK 573115-833-010 003 for RH Side and Before next flight None None

Repeat the Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-003 004 for LH Side and/or to SUBTASK 573115-832-009 004 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

Or Apply Service Bulletin No. A330-57-3083 and Before next flight None None No crack found

Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 42 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the Hole Pre SB No. A330-57-3083 to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-004 001 for LH Side and/or to SUBTASK 573115-833-014 001 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 43 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New Fastener Pre SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-007 001 for LH Side and/or to SUBTASK 573115-833-018 001 for RH Side and Before next flight None None No Crack found after rototest inspection

Repeat the Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-003 004 for LH Side and/or to SUBTASK 573115-832-009 004 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 44 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Config. 003 Post Service Bulletin No. A330-57-3083 Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side FC optimized set: 26,000 FC/85,100 FH or FH optimized set: 20,500 FC/138,700 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

Install New same Fastener Post SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-002 001 for LH Side and/or to SUBTASK 573115-833-011 001 for RH Side and Before next flight None None No crack found

Repeat the Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 45 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the Hole Post SB No. A330-57-3083 to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-005 001 for LH Side and/or to SUBTASK 573115-833-015 001 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 46 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New Fastener Post SB 57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-008 001 for LH Side and/or to SUBTASK 573115-833-019 001 for RH Side and Before next flight None None No Crack found after rototest inspection

Repeat the Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 47 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Config. 003 Do a Rototest Inspection of the Holes on LH and RH Sides, refer to SUBTASK 573115-832-010 003 for LH Side and to SUBTASK 573115-832-011 003 for RH Side FC optimized set: 17,400 FC/57,100 FH or FH optimized set: 13,800 FC/ 93,700 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

Install New same Fasteners in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-022 003 for LH Side and/or to SUBTASK 573115-833-013 003 for RH Side and Before next flight None None No crack found

Repeat the Rototest Inspection of the Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 003 for LH Side and/or to SUBTASK 573115-832-011 003 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 48 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the Holes to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-023 003 for LH Side and/or to SUBTASK 573115-833-017 003 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection Contact Airbus Before next flight None None Install New Fasteners in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-024 003 for LH Side and/or to SUBTASK 573115-833-021 003 for RH Side and Before next flight None None No Crack found after rototest inspection

Repeat the Rototest Inspection of the Fastener Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 003 for LH Side and/or to SUBTASK 573115-833-011 003 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 49 5

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

# @A330 SERVICE BULLETIN 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 and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF 004 Table 1: Rototest Inspection of the Fasteners Hole of the Area A at FR 40, LH and RH Sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Do a Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-003 005 for LH Side and to SUBTASK 573115-832-009 005 for RH Side Refer to Table 3

Or Apply Service Bulletin No. A330-57-3083 and Before next flight None None Config. 004 Pre Service Bulletin No. A330-57-3083

Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

Config. 004 Post Service Bulletin No. A330-57-3083 Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 50 5

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# @A330 SERVICE BULLETIN
Table 2: Rototest Inspection of the Fasteners Holes of the Area B at FR 40, LH and RH Sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval
Config. 004 Do a Rototest Inspection of the Holes on LH and RH Sides, refer to SUBTASK 573115-832-010 004 for LH Side and to SUBTASK 573115-832-011 004 for RH Side Refer to Table 5

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Config. 004 Pre Service Bulletin No. A330-57-3083 Do a Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-003 005 for LH Side and to SUBTASK 573115-832-009 005 for RH Side FC optimized set: 17,400 FC/57,100 FH or FH optimized set: 13,800 FC/93,700 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 51 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New same Fastener Pre SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-001 008 for LH Side and/or to SUBTASK 573115-833-010 004 for RH Side and Before next flight None None

Repeat the Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-003 005 for LH Side and/or to SUBTASK 573115-832-009 005 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

Or Apply Service Bulletin No. A330-57-3083 and Before next flight None None No crack found

Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 52 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the Hole Pre SB No. A330-57-3083 to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-004 001 for LH Side and/or to SUBTASK 573115-833-014 001 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 53 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New Fastener Pre SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-007 001 for LH Side and/or to SUBTASK 573115-833-018 001 for RH Side and Before next flight None None No Crack found after rototest inspection

Repeat the Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-003 005 for LH Side and/or to SUBTASK 573115-832-009 005 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 54 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Config. 004 Post Service Bulletin No. A330-57-3083 Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side FC optimized set: 26,000 FC/85,100 FH or FH optimized set: 20,500 FC/138,700 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

Install New same Fastener Post SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-002 001 for LH Side and/or to SUBTASK 573115-833-011 001 for RH Side and Before next flight None None No crack found

Repeat the Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 55 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the Hole Post SB No. A330-57-3083 to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-005 001 for LH Side and/or to SUBTASK 573115-833-015 001 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 56 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New Fastener Post SB 57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-008 001 for LH Side and/or to SUBTASK 573115-833-019 001 for RH Side and Before next flight None None No Crack found after rototest inspection

Repeat the Rototest Inspection Post SB No. A330-57-3083 of the Holes of the Fastener Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 57 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Config. 004 Do a Rototest Inspection of the Holes on LH and RH Sides, refer to SUBTASK 573115-832-010 004 for LH Side and to SUBTASK 573115-832-011 004 for RH Side FC optimized set: 17,400 FC/57,100 FH or FH optimized set: 13,800 FC/ 93,700 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

Install New same Fasteners in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-022 004 for LH Side and/or to SUBTASK 573115-833-013 004 for RH Side and Before next flight None None No crack found

Repeat the Rototest Inspection of the Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 004 for LH Side and/or to SUBTASK 573115-832-011 004 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 58 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the Holes to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-023 004 for LH Side and/or to SUBTASK 573115-833-017 004 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection Contact Airbus Before next flight None None Install New Fasteners in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-024 004 for LH Side and/or to SUBTASK 573115-833-021 004 for RH Side and Before next flight None None No Crack found after rototest inspection

Repeat the Rototest Inspection of the Fastener Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 004 for LH Side and/or to SUBTASK 573115-832-011 004 for RH Side None None FC optimized set: 12,800 FC/41,900 FH or FH optimized set: 10,300 FC/69,700 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 59 5

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

# @A330 SERVICE BULLETIN 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 and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF 005 Table 1: Rototest Inspection of the Fastener Hole of the Area A at FR 40, LH and RH Sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Do a Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-003 006 for LH Side and to SUBTASK 573115-832-009 006 for RH Side Refer to Table 3

Or Apply Service Bulletin No. A330-57-3083 and Before next flight None None Config. 005 Pre Service Bulletin No. A330-57-3083

Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

Config. 005 Post Service Bulletin No. A330-57-3083 Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 60 5

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# @A330 SERVICE BULLETIN
Table 2: Rototest Inspection of the Fasteners Holes of the Area B at FR 40, LH and RH Sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval
Config. 005 Do a Rototest Inspection of the Holes on LH and RH Sides, refer to SUBTASK 573115-832-010 005 for LH Side and to SUBTASK 573115-832-011 005 for RH Side Refer to Table 5

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 61 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

A330-200, WV020 Serie FC optimized set: 16,100 FC/56,600 FH or FH optimized set: 12,600 FC/82,200 FH See NOTE (*) A330-300, WV010 Serie FC optimized set: 16,300 FC/53,200 FH or FH optimized set: 12,900 FC/87,300 FH See NOTE (*) A330-300, WV020 Serie except WV022 FC optimized set: 15,900 FC/52,000 FH or FH optimized set: 12,600 FC/85,300 FH See NOTE (*) Config. 005 Pre Service Bulletin No. A330-57-3083

A330-300, WV022 Do a Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-003 006 for LH Side and to SUBTASK 573115-832-009 006 for RH Side

FC optimized set: 15,500 FC/50,800 FH or FH optimized set: 12,300 FC/83,300 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 62 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

All A330 WV Install New same Fastener Pre SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-001 007 for LH Side and/or to SUBTASK 573115-833-010 005 for RH Side and Before next flight None None

A330-200, WV020 Serie FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*) A330-300, WV010 Serie FC optimized set: 10,000 FC/32,900 FH or FH optimized set: 8,050 FC/54,700 FH See NOTE (*) No crack found

A330-300, WV020 Serie except WV022 Repeat the Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-003 006 for LH Side and/or to SUBTASK 573115-832-009 006 for RH Side None None

FC optimized set: 9,850 FC/32,200 FH or FH optimized set: 7,900 FC/53,500 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 63 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

No crack found A330-300, WV022 Repeat the Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-003 006 for LH Side and/or to SUBTASK 573115-832-009 006 for RH Side None None FC optimized set: 9,600 FC/31,400 FH or FH optimized set: 7,700 FC/52,300 FH See NOTE (*)

Or All A330 WV Apply Service Bulletin No. A330-57-3083 and Before next flight None None No crack found

All A330 WV Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 64 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found All A330 WV Oversize the Hole Pre SB No. A330-57-3083 to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-004 001 for LH Side and/or to SUBTASK 573115-833-014 001 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection All A330 WV Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 65 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

All A330 WV Install New Fastener Pre SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-007 015 for LH Side and/or to SUBTASK 573115-833-018 003 for RH Side and Before next flight None None

A330-200, WV020 Serie FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*) A330-300, WV010 Serie FC optimized set: 10,000 FC/32,900 FH or FH optimized set: 8,050 FC/54,700 FH See NOTE (*) No Crack found after rototest inspection

A330-300, WV020 Serie except WV022 Repeat the Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-003 006 for LH Side and/or to SUBTASK 573115-832-009 006 for RH Side None None

FC optimized set: 9,850 FC/32,200 FH or FH optimized set: 7,900 FC/53,500 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 66 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

No Crack found after rototest inspection A330-300, WV022 Repeat the Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-003 006 for LH Side and/or to SUBTASK 573115-832-009 006 for RH Side None None FC optimized set: 9,600 FC/31,400 FH or FH optimized set: 7,700 FC/52,300 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 67 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

A330-200, WV020 Serie FC optimized set: 24,600 FC/86,200 FH or FH optimized set: 18,900 FC/123,300 FH See NOTE (*) A330-300, WV010 Serie FC optimized set: 24,800 FC/81,300 FH or FH optimized set: 19,500 FC/132,300 FH See NOTE (*) A330-300, WV020 Serie except WV022 FC optimized set: 24,300 FC/79,400 FH or FH optimized set: 19,100 FC/129,200 FH See NOTE (*) Config. 005 Post Service Bulletin No. A330-57-3083

A330-300, WV022 Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side

FC optimized set: 23,700 FC/77,400 FH or FH optimized set: 18,600 FC/126,100 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 68 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

All A330 WV Install New same Fastener Post SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-002 015 for LH Side and/or to SUBTASK 573115-833-011 003 for RH Side and Before next flight None None

A330-200, WV020 Serie FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*) A330-300, WV010 Serie FC optimized set: 10,000 FC/32,900 FH or FH optimized set: 8,050 FC/54,700 FH See NOTE (*) No crack found

A330-300, WV020 Serie except WV022 Repeat the Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side None None

FC optimized set: 9,850 FC/32,200 FH or FH optimized set: 7,900 FC/53,500 FH See NOTE (*)
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 69 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

No crack found A330-300, WV022 Repeat the Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side None None FC optimized set: 9,600 FC/31,400 FH or FH optimized set: 7,700 FC/52,300 FH See NOTE (*)

Crack found All A330 WV Oversize the Hole Post SB No. A330-57-3083 to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-005 001 for LH Side and/or to SUBTASK 573115-833-015 001 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection All A330 WV Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 70 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

All A330 WV Install New Fastener Post SB 57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-008 015 for LH Side and/or to SUBTASK 573115-833-019 003 for RH Side and Before next flight None None

A330-200, WV020 Serie FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*) A330-300, WV010 Serie FC optimized set: 10,000 FC/32,900 FH or FH optimized set: 8,050 FC/54,700 FH See NOTE (*) No Crack found after rototest inspection

A330-300, WV020 Serie except WV022 Repeat the Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side None None

FC optimized set: 9,850 FC/32,200 FH or FH optimized set: 7,900 FC/53,500 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 71 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

No Crack found after rototest inspection A330-300, WV022 Repeat the Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side None None FC optimized set: 9,600 FC/31,400 FH or FH optimized set: 7,700 FC/52,300 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 72 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

A330-200, WV020 Serie FC optimized set: 16,100 FC/56,600 FH or FH optimized set: 12,600 FC/ 82,200 FH See NOTE (*) A330-300, WV010 Serie FC optimized set: 16,300 FC/53,200 FH or FH optimized set: 12,900 FC/ 87,300 FH See NOTE (*) A330-300, WV020 Serie except WV022 FC optimized set: 15,900 FC/52,000 FH or FH optimized set: 12,600 FC/ 85,300 FH See NOTE (*) Config. 005

A330-300, WV022 Do a Rototest Inspection of the Holes on LH and RH Sides, refer to SUBTASK 573115-832-010 005 for LH Side and to SUBTASK 573115-832-011 005 for RH Side

FC optimized set: 15,500 FC/50,800 FH or FH optimized set: 12,300 FC/ 83,300 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 73 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

All A330 WV Install New same Fasteners in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-022 005 for LH Side and/or to SUBTASK 573115-833-013 005 for RH Side and Before next flight None None

A330-200, WV020 Serie FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*) A330-300, WV010 Serie FC optimized set: 10,000 FC/32,900 FH or FH optimized set: 8,050 FC/54,700 FH See NOTE (*) No crack found

A330-300, WV020 Serie except WV022 Repeat the Rototest Inspection of the Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 005 for LH Side and/or to SUBTASK 573115-832-011 005 for RH Side None None

FC optimized set: 9,850 FC/32,200 FH or FH optimized set: 7,900 FC/53,500 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 74 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

No crack found A330-300, WV022 Repeat the Rototest Inspection of the Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 005 for LH Side and/or to SUBTASK 573115-832-011 005 for RH Side None None FC optimized set: 9,600 FC/31,400 FH or FH optimized set: 7,700 FC/52,300 FH See NOTE (*)

Crack found All A330 WV Oversize the Holes to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-023 005 for LH Side and/or to SUBTASK 573115-833-017 005 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection All A330 WV Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 75 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

All A330 WV Install New Fasteners in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-024 005 for LH Side and/or to SUBTASK 573115-833-021 005 for RH Side and Before next flight None None

A330-200, WV020 Serie FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*) A330-300, WV010 Serie FC optimized set: 10,000 FC/32,900 FH or FH optimized set: 8,050 FC/54,700 FH See NOTE (*) No Crack found after rototest inspection

A330-300, WV020 Serie except WV022 Repeat the Rototest Inspection of the Fastener Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 005 for LH Side and/or to SUBTASK 573115-832-011 005 for RH Side None None

FC optimized set: 9,850 FC/32,200 FH or FH optimized set: 7,900 FC/53,500 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 76 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

No Crack found after rototest inspection A330-300, WV022 Repeat the Rototest Inspection of the Fastener Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 005 for LH Side and/or to SUBTASK 573115-832-011 005 for RH Side None None FC optimized set: 9,600 FC/31,400 FH or FH optimized set: 7,700 FC/52,300 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11). 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 and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 77 5

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# @A330 SERVICE BULLETIN
**CONF 006 Table 1: Rototest Inspection of the Fastener Hole of the Area A at FR 40, LH and RH Sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Do a Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-003 006 for LH Side and to SUBTASK 573115-832-009 006 for RH Side Refer to Table 3

Or Apply Service Bulletin No. A330-57-3083 and Before next flight None None Config. 006 Pre Service Bulletin No. A330-57-3083

Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

Config. 006 Post Service Bulletin No. A330-57-3083 Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 78 5

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# @A330 SERVICE BULLETIN
Table 2: Rototest Inspection of the Fasteners Holes of the Area B at FR 40, LH and RH Sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval
Config. 006 Do a Rototest Inspection of the Holes on LH and RH Sides, refer to SUBTASK 573115-832-010 005 for LH Side and to SUBTASK 573115-832-011 005 for RH Side Refer to Table 5

Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Config. 006 Pre Service Bulletin No. A330-57-3083 Do a Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-003 006 for LH Side and to SUBTASK 573115-832-009 006 for RH Side FC optimized set: 16,100 FC/56,600 FH or FH optimized set: 12,600 FC/82,200 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 79 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New same Fastener Pre SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-001 007 for LH Side and/or to SUBTASK 573115-833-010 005 for RH Side and Before next flight None None

Repeat the Rototest Inspection Pre SB No. A330-57-3083 of the Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-003 006 for LH Side and/or to SUBTASK 573115-832-009 006 for RH Side None None FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*)

Or Apply Service Bulletin No. A330-57-3083 and Before next flight None None No crack found

Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side Refer to Table 4 Perform this rototest at the Threshold from SB No.A330-57-3083 embodiment

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 80 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the Hole Pre SB No. A330-57-3083 to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-004 001 for LH Side and/or to SUBTASK 573115-833-014 001 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 81 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New Fastener Pre SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-007 015 for LH Side and/or to SUBTASK 573115-833-018 003 for RH Side and Before next flight None None No Crack found after rototest inspection

Repeat the Rototest Inspection Pre SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-003 006 for LH Side and/or to SUBTASK 573115-832-009 006 for RH Side None None FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 82 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Config. 006 Post Service Bulletin No. A330-57-3083 Do a Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and to SUBTASK 573115-832-005 001 for RH Side FC optimized set: 24,600 FC/86,200 FH or FH optimized set: 18,900 FC/123,300 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

Install New same Fastener Post SB No. A330-57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-002 015 for LH Side and/or to SUBTASK 573115-833-011 003 for RH Side and Before next flight None None No crack found

Repeat the Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side None None FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 83 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the Hole Post SB No. A330-57-3083 to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-005 001 for LH Side and/or to SUBTASK 573115-833-015 001 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 84 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from SB A330-57-3083 embodiment (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Install New Fastener Post SB 57-3083 in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-008 015 for LH Side and/or to SUBTASK 573115-833-019 003 for RH Side and Before next flight None None No Crack found after rototest inspection

Repeat the Rototest Inspection Post SB No. A330-57-3083 of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-004 001 for LH Side and/or to SUBTASK 573115-832-005 001 for RH Side None None FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 85 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval
Config. 006 Do a Rototest Inspection of the Holes on LH and RH Sides, refer to SUBTASK 573115-832-010 005 for LH Side and to SUBTASK 573115-832-011 005 for RH Side FC optimized set: 16,100 FC/56,600 FH or FH optimized set: 12,600 FC/ 82,200 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

Install New same Fasteners in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-022 005 for LH Side and/or to SUBTASK 573115-833-013 005 for RH Side and Before next flight None None No crack found

Repeat the Rototest Inspection of the Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 005 for LH Side and/or to SUBTASK 573115-832-011 005 for RH Side None None FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 86 5

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# @A330 SERVICE BULLETIN
Table 5: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found Oversize the Holes to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-023 005 for LH Side and/or to SUBTASK 573115-833-017 005 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection Contact Airbus Before next flight None None Install New Fasteners in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-024 005 for LH Side and/or to SUBTASK 573115-833-021 005 for RH Side and Before next flight None None No Crack found after rototest inspection

Repeat the Rototest Inspection of the Fastener Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 005 for LH Side and/or to SUBTASK 573115-832-011 005 for RH Side None None FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*)

NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 87 5

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

# @A330 SERVICE BULLETIN 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 and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF 007 Table 1: Rototest Inspection of the Fastener Hole of the Area A at FR 40, LH and RH Sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval
Config. 007 Do a Rototest Inspection of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-006 001 for LH Side and to SUBTASK 573115-832-012 001 for RH Side Refer to Table 3

Table 2: Rototest Inspection of the Fasteners Holes of the Area B at FR 40, LH and RH Sides Compliance Time Condition Action Threshold (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval
Config. 007 Do a Rototest Inspection of the Holes on LH and RH Sides, refer to SUBTASK 573115-832-010 005 for LH Side and to SUBTASK 573115-832-011 005 for RH Side Refer to Table 4

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 88 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

A330-200, WV020 and WV050 Series FC optimized set: 24,600 FC/86,200 FH or FH optimized set: 18,900 FC/123,300 FH See NOTE (*) A330-300, WV020 Serie except WV022 FC optimized set: 24,300 FC/79,400 FH or FH optimized set: 19,100 FC/129,200 FH See NOTE (*) Config. 007

A330-300, WV022 and WV050 Series Do a Rototest Inspection of the Hole on LH and RH Sides, refer to SUBTASK 573115-832-006 001 for LH Side and to SUBTASK 573115-832-012 001 for RH Side

FC optimized set: 23,700 FC/77,400 FH or FH optimized set: 18,600 FC/126,100 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 89 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

All A330 WV Install New same Fastener in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-003 001 for LH Side and/or to SUBTASK 573115-833-012 001 for RH Side and Before next flight None None

A330-200, WV020 and WV050 Series FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*) A330-300, WV020 Serie except WV022 FC optimized set: 9,850 FC/32,200 FH or FH optimized set: 7,900 FC/53,500 FH See NOTE (*) No crack found

A330-300, WV022 and WV050 Series Repeat the Rototest Inspection of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-006 001 for LH Side and/or to SUBTASK 573115-832-012 001 for RH Side None None

FC optimized set: 9,600 FC/31,400 FH or FH optimized set: 7,700 FC/52,300 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 90 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found All A330 WV Oversize the Hole to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-006 001 for LH Side and/or to SUBTASK 573115-833-016 001 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection All A330 WV Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 91 5

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# @A330 SERVICE BULLETIN
Table 3: Rototest Inspection of the Fastener Hole of the Area A of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

All A330 WV Install New Fastener in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-009 001 for LH Side and/or to SUBTASK 573115-833-020 001 for RH Side and Before next flight None None

A330-200, WV020 and WV050 Series FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*) A330-300, WV020 Serie except WV022 FC optimized set: 9,850 FC/32,200 FH or FH optimized set: 7,900 FC/53,500 FH See NOTE (*) No Crack found after rototest inspection

A330-300, WV022 and WV050 Series Repeat the Rototest Inspection of the Hole on LH and/or RH Sides, refer to SUBTASK 573115-832-006 001 for LH Side and/or to SUBTASK 573115-832-012 001 for RH Side None None

FC optimized set: 9,600 FC/31,400 FH or FH optimized set: 7,700 FC/52,300 FH See NOTE (*) NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 92 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

A330-200, WV020 and WV050 Series FC optimized set: 16,100 FC/56,600 FH or FH optimized set: 12,600 FC/ 82,200 FH See NOTE (*) A330-300, WV020 Serie except WV022 FC optimized set: 15,900 FC/52,000 FH or FH optimized set: 12,600 FC/ 85,300 FH See NOTE (*) Config. 007

A330-300, WV022 and WV050 Series Do a Rototest Inspection of the Holes on LH and RH Sides, refer to SUBTASK 573115-832-010 005 for LH Side and to SUBTASK 573115-832-011 005 for RH Side

FC optimized set: 15,500 FC/50,800 FH or FH optimized set: 12,300 FC/ 83,300 FH See NOTE (*) 2,400 FC or 24 months from SB issuance date None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 93 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

All A330 WV Install New same Fasteners in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-022 005 for LH Side and/or to SUBTASK 573115-833-013 005 for RH Side and Before next flight None None

A330-200, WV020 and WV050 Series FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*) A330-300, WV020 Serie except WV022 FC optimized set: 9,850 FC/32,200 FH or FH optimized set: 7,900 FC/53,500 FH See NOTE (*) No crack found

A330-300, WV022 and WV050 Series Repeat the Rototest Inspection of the Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 005 for LH Side and/or to SUBTASK 573115-832-011 005 for RH Side None None

FC optimized set: 9,600 FC/31,400 FH or FH optimized set: 7,700 FC/52,300 FH See NOTE (*)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 94 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

Crack found All A330 WV Oversize the Holes to First Oversize in comparison with the current hole diameter on LH and/or RH Sides, refer to SUBTASK 573115-833-023 005 for LH Side and/or to SUBTASK 573115-833-017 005 for RH Side and do a rototest inspection Before next flight None None

Crack found after rototest inspection All A330 WV Contact Airbus Before next flight None None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 95 5

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# @A330 SERVICE BULLETIN
Table 4: Rototest Inspection of the Fastener Holes of the Area B of the Frame 40, LH and RH Sides Compliance Time Condition Action Threshold to be counted from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval

All A330 WV Install New Fasteners in transition fit on LH and/or RH Sides, refer to SUBTASK 573115-833-024 005 for LH Side and/or to SUBTASK 573115-833-021 005 for RH Side and Before next flight None None

A330-200, WV020 and WV050 Series FC optimized set: 10,000 FC/35,100 FH or FH optimized set: 8,100 FC/52,700 FH See NOTE (*) A330-300, WV020 Serie except WV022 FC optimized set: 9,850 FC/32,200 FH or FH optimized set: 7,900 FC/53,500 FH See NOTE (*) No Crack found after rototest inspection

A330-300, WV022 and WV050 Series Repeat the Rototest Inspection of the Fastener Holes on LH and/or RH Sides, refer to SUBTASK 573115-832-010 005 for LH Side and/or to SUBTASK 573115-832-011 005 for RH Side None None

FC optimized set: 9,600 FC/31,400 FH or FH optimized set: 7,700 FC/52,300 FH See NOTE (*) NOTE (*): For FH and FC optimization on A330 aircraft, operators shall select threshold/interval that better suits aircraft operation and utilization (Refer to OIT 999.0086/11).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 96 5

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# @A330 SERVICE BULLETIN 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 and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF ALL 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. **CONF 001 Task 573115-832-801-001: Inspection Get Access 12.00 On Aircraft Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side 0.25 Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side 0.25 Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side 0.25 Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side 0.25 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side 0.50 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side 0.50 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side 0.50

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 97 5

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# @A330 SERVICE BULLETIN
Task 573115-832-801-001: Inspection Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side 0.50 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side 5.00 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side 5.00 Tests 2.00 Close-Up 12.00 TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the manhours stating post Service Bulletin No.A330-57-3083 apply. For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the manhours stating pre Service Bulletin No.A330-57-3083 apply. NOTE: The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. Task 573115-833-801-001: Repair Get Access 12.00 On Aircraft Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New same Fasteners of the Area B in transition fit, LH Side 2.50 Install New same Fasteners of the Area B in transition fit, RH Side 2.50 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side 0.25
Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side 0.25
Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side 0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 98 5

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# @A330 SERVICE BULLETIN
Task 573115-833-801-001: Repair Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side 0.25
Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side 2.50 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side 2.50 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New Fasteners of the Area B in transition fit, LH Side 2.50 Install New Fasteners of the Area B in transition fit, RH Side 2.50 Tests 2.00 Close-Up 12.00 TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the manhours stating post Service Bulletin No.A330-57-3083 apply. For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the manhours stating pre Service Bulletin No.A330-57-3083 apply. **CONF 002 Task 573115-832-801-001: Inspection Get Access 12.00 On Aircraft Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side 0.25 Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side 0.25 Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side 0.25 Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side 0.25 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side 0.50

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 99 5

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# @A330 SERVICE BULLETIN
Task 573115-832-801-001: Inspection Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side 0.50 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side 0.50 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side 0.50 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side 5.00 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side 5.00 Tests 2.00 Close-Up 12.00 TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the manhours stating post Service Bulletin No.A330-57-3083 apply. For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the manhours stating pre Service Bulletin No.A330-57-3083 apply. NOTE: The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. Task 573115-833-801-001: Repair Get Access 12.00 On Aircraft Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New same Fasteners of the Area B in transition fit, LH Side 2.50 Install New same Fasteners of the Area B in transition fit, RH Side 2.50 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side 0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 100 5

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# @A330 SERVICE BULLETIN
Task 573115-833-801-001: Repair Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side 0.25
Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side 0.25
Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side 0.25
Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side 2.50 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side 2.50 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New Fasteners of the Area B in transition fit, LH Side 2.50 Install New Fasteners of the Area B in transition fit, RH Side 2.50 Tests 2.00 Close-Up 12.00 TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the manhours stating post Service Bulletin No.A330-57-3083 apply. For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the manhours stating pre Service Bulletin No.A330-57-3083 apply. **CONF 003 Task 573115-832-801-001: Inspection Get Access 12.00 On Aircraft Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side 0.25 Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side 0.25 Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side 0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 101 5

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# @A330 SERVICE BULLETIN
Task 573115-832-801-001: Inspection Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side 0.25 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side 0.50 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side 0.50 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side 0.50 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side 0.50 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side 5.00 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side 5.00 Tests 2.00 Close-Up 12.00 TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the manhours stating post Service Bulletin No.A330-57-3083 apply. For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the manhours stating pre Service Bulletin No.A330-57-3083 apply. NOTE: The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. Task 573115-833-801-001: Repair Get Access 12.00 On Aircraft Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New same Fasteners of the Area B in transition fit, LH Side 2.50 Install New same Fasteners of the Area B in transition fit, RH Side 2.50
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 102 5

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# @A330 SERVICE BULLETIN
Task 573115-833-801-001: Repair Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side 0.25
Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side 0.25
Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side 0.25
Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side 0.25
Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side 2.50 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side 2.50 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New Fasteners of the Area B in transition fit, LH Side 2.50 Install New Fasteners of the Area B in transition fit, RH Side 2.50 Tests 2.00 Close-Up 12.00 TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the manhours stating post Service Bulletin No.A330-57-3083 apply. For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the manhours stating pre Service Bulletin No.A330-57-3083 apply. **CONF 004 Task 573115-832-801-001: Inspection Get Access 12.00 On Aircraft Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side 0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 103 5

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# @A330 SERVICE BULLETIN
Task 573115-832-801-001: Inspection Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side 0.25 Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side 0.25 Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side 0.25 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side 0.50 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side 0.50 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side 0.50 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side 0.50 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side 5.00 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side 5.00 Tests 2.00 Close-Up 12.00 TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the manhours stating post Service Bulletin No.A330-57-3083 apply. For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the manhours stating pre Service Bulletin No.A330-57-3083 apply. NOTE: The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. Task 573115-833-801-001: Repair Get Access 12.00 On Aircraft Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 104 5

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# @A330 SERVICE BULLETIN
Task 573115-833-801-001: Repair Install New same Fasteners of the Area B in transition fit, LH Side 2.50 Install New same Fasteners of the Area B in transition fit, RH Side 2.50 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side 0.25
Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side 0.25
Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side 0.25
Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side 0.25
Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side 2.50 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side 2.50 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New Fasteners of the Area B in transition fit, LH Side 2.50 Install New Fasteners of the Area B in transition fit, RH Side 2.50 Tests 2.00 Close-Up 12.00 TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the manhours stating post Service Bulletin No.A330-57-3083 apply. For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the manhours stating pre Service Bulletin No.A330-57-3083 apply. **CONF 005 Task 573115-832-801-001: Inspection Get Access 12.00 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 105 5

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# @A330 SERVICE BULLETIN
Task 573115-832-801-001: Inspection On Aircraft Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side 0.25 Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side 0.25 Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side 0.25 Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side 0.25 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side 0.50 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side 0.50 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side 0.50 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side 0.50 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side 5.00 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side 5.00 Tests 2.00 Close-Up 12.00 TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the manhours stating post Service Bulletin No.A330-57-3083 apply. For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the manhours stating pre Service Bulletin No.A330-57-3083 apply. NOTE: The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. Task 573115-833-801-001: Repair Get Access 12.00 On Aircraft Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 106 5

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# @A330 SERVICE BULLETIN
Task 573115-833-801-001: Repair Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New same Fasteners of the Area B in transition fit, LH Side 2.50 Install New same Fasteners of the Area B in transition fit, RH Side 2.50 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side 0.25
Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side 0.25
Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side 0.25
Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side 0.25
Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side 2.50 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side 2.50 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New Fasteners of the Area B in transition fit, LH Side 2.50 Install New Fasteners of the Area B in transition fit, RH Side 2.50 Tests 2.00 Close-Up 12.00 TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the manhours stating post Service Bulletin No.A330-57-3083 apply. For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the manhours stating pre Service Bulletin No.A330-57-3083 apply.
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 107 5

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# @A330 SERVICE BULLETIN
**CONF 006 Task 573115-832-801-001: Inspection Get Access 12.00 On Aircraft Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side 0.25 Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side 0.25 Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side 0.25 Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side 0.25 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side 0.50 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side 0.50 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side 0.50 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side 0.50 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side 5.00 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side 5.00 Tests 2.00 Close-Up 12.00 TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the manhours stating post Service Bulletin No.A330-57-3083 apply. For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the manhours stating pre Service Bulletin No.A330-57-3083 apply. NOTE: The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. Task 573115-833-801-001: Repair Get Access 12.00 On Aircraft Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 108 5

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# @A330 SERVICE BULLETIN
Task 573115-833-801-001: Repair Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New same Fasteners of the Area B in transition fit, LH Side 2.50 Install New same Fasteners of the Area B in transition fit, RH Side 2.50 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side 0.25
Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side 0.25
Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side 0.25
Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side 0.25
Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side 2.50 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side 2.50 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side 0.25 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side 0.25 Install New Fasteners of the Area B in transition fit, LH Side 2.50 Install New Fasteners of the Area B in transition fit, RH Side 2.50 Tests 2.00 Close-Up 12.00 TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the manhours stating post Service Bulletin No.A330-57-3083 apply. For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 109 5

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# @A330 SERVICE BULLETIN manhours stating pre Service Bulletin No.A330-57-3083 apply. **CONF 007 Task 573115-832-801-001: Inspection Get Access 12.00 On Aircraft Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side 0.25 Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side 0.25 Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side 0.25 Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side 0.25 Do a Rototest Inspection of the Hole of the Area A of the Frame 40, LH Side 0.50 Do a Rototest Inspection of the Hole of the Area A of the Frame 40, RH Side 0.50 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side 5.00 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side 5.00 Tests 2.00 Close-Up 12.00 TOTAL MANHOURS 38.00 ELAPSED TIME (HOURS) 38.00 NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the manhours stating post Service Bulletin No.A330-57-3083 apply. For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the manhours stating pre Service Bulletin No.A330-57-3083 apply. NOTE: The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. Task 573115-833-801-001: Repair Get Access 12.00 On Aircraft Install New same Fastener of the Area A in transition fit, LH Side 0.25 Install New same Fastener of the Area A in transition fit, RH Side 0.25 Install New same Fasteners of the Area B in transition fit, LH Side 2.50 Install New same Fasteners of the Area B in transition fit, RH Side 2.50
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 110 5

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# @A330 SERVICE BULLETIN
Task 573115-833-801-001: Repair Oversize the Hole of the Area A to First Oversize in comparison with the current hole diameter, LH Side 0.25 Oversize the Hole of the Area A to First Oversize in comparison with the current hole diameter, RH Side 0.25 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side 2.50 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side 2.50 Install New Fastener of the Area A in transition fit, LH Side 0.25 Install New Fastener of the Area A in transition fit, RH Side 0.25 Install New Fasteners of the Area B in transition fit, LH Side 2.50 Install New Fasteners of the Area B in transition fit, RH Side 2.50 Tests 2.00 Close-Up 12.00 TOTAL MANHOURS 42.50 ELAPSED TIME (HOURS) 42.50 NOTE: For Area A, if Service Bulletin No.A330-57-3083 is accomplished, only the manhours stating post Service Bulletin No.A330-57-3083 apply. For Area A, if Service Bulletin No.A330-57-3083 is not accomplished, only the manhours stating pre Service Bulletin No.A330-57-3083 apply. **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24 20-21-11 21-20-00 21-52-41 24-41-00 25-52-00 25-80-00 27-84-41 36-22-19 52-30-00 53-35-13 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 111 5

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# @A330 SERVICE BULLETIN
Service Bulletin (SB) A330-57-3083 Standards Manual (SM) Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-44-11 **CONF 002 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24 20-21-11 21-20-00 21-52-41 24-41-00 25-52-00 25-80-00 27-84-41 36-22-19 52-30-00 53-35-13 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Standards Manual (SM) Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-44-11 **CONF 003 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24 20-21-11 21-20-00 21-52-41 24-41-00 25-52-00 25-80-00 27-84-41 36-22-19 52-30-00 53-35-13 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Standards Manual (SM) Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-44-11 **CONF 004 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24 20-21-11 21-20-00 21-52-41 24-41-00 25-52-00 25-80-00 27-84-41 36-22-19 52-30-00 53-35-13 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Standards Manual (SM)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 112 5

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# @A330 SERVICE BULLETIN
Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-44-11 **CONF 005 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24 20-21-11 21-20-00 21-52-41 24-41-00 25-52-00 25-80-00 27-84-41 36-22-19 52-30-00 53-35-13 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Standards Manual (SM) Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-44-11 **CONF 006 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24 20-21-11 21-20-00 21-52-41 24-41-00 25-52-00 25-80-00 27-84-41 28-80-00 36-22-19 52-30-00 53-35-13 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Standards Manual (SM) Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-44-11 **CONF 007 Aircraft Maintenance Manual (AMM) 06-31-53 06-41-53 12-34-24 20-21-11 21-20-00 21-52-41 24-41-00 25-52-00 25-80-00 27-84-41 36-22-19 52-30-00 53-35-13 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Standards Manual (SM) Structural Repair Manual (SRM) 51-11-00 51-22-00 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-44-11
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 113 5

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# @A330 SERVICE BULLETIN
**CONF ALL K. PUBLICATION AFFECTED Airworthiness Limitation Section (ALS) Airworthiness Limitation Section (ALS) Part 2 Maintenance Planning Document (MPD) 571102 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 114 5

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# @A330 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is: Kit 573115A01R02 Kit 573115A02R02 Kit 573115A03R02 Kit 573115A04R03 Kit 573115A05R02 Kit 573115A06R03 AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 Hamburg Germany For ordering by internet: http://spares.airbus.com For ordering modification kits by fax: +49 40 50 76 25 90 For ordering of single spares by fax: +49 40 50 76 40 13 (2) Price and Availability

Kit 573115A01R02 Cost 2,050.00 USD Availability 120 calendar days from receipt of order The MH and parts required for ISB are not subject to any specific commercial policy. However, in case of significant repair, Airbus may provide an industry support. A dedicated sentence is included is next paragraph to refer to CSD in such a case. Kit 573115A02R02 Cost 1,800.00 USD Availability 120 calendar days from receipt of order The MH and parts required for ISB are not subject to any specific commercial policy. However, in case of significant repair, Airbus may provide an industry support. A dedicated sentence is included is next paragraph to refer to CSD in such a case. Kit 573115A03R02 Cost 1,550.00 USD Availability 120 calendar days from receipt of order The MH and parts required for ISB are not subject to any specific commercial policy. However, in case of significant repair, Airbus may provide an industry support. A dedicated sentence is included is next paragraph to refer to CSD in such a case. Kit 573115A04R03 Cost 1,050.00 USD Availability 120 calendar days from receipt of order DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 115 5

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# @A330 SERVICE BULLETIN The MH and parts required for ISB are not subject to any specific commercial policy. However, in case of significant repair, Airbus may provide an industry support. A dedicated sentence is included is next paragraph to refer to CSD in such a case. Kit 573115A05R02 Cost 2,250.00 USD Availability 120 calendar days from receipt of order The MH and parts required for ISB are not subject to any specific commercial policy. However, in case of significant repair, Airbus may provide an industry support. A dedicated sentence is included is next paragraph to refer to CSD in such a case. Kit 573115A06R03 Cost 2,950.00 USD Availability 120 calendar days from receipt of order The MH and parts required for ISB are not subject to any specific commercial policy. However, in case of significant repair, Airbus may provide an industry support. A dedicated sentence is included is next paragraph to refer to CSD in such a case. B. INDUSTRY SUPPORT INFORMATION This Service Bulletin is subject to a specific support provided by AIRBUS. For more details regarding the applicable commercial policy, please contact your Customer Support Director. C. LIST OF COMPONENTS Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 EN6115V6-16 3 SCREW 2 ASNA2531-6 8 NUT 3 EN6115V6X16 3 SCREW 4 EN6115V6-18 1 SCREW 5 EN6115V6X18 1 SCREW 6 EN6115V6-20 4 SCREW 7 EN6115V6X20 4 SCREW 78 ASNA2531-7 1 NUT 79 EN6115V7X16 1 SCREW 94 EN6115V7-16 1 SCREW 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 573115A02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 9 ASNA2531-5 1 NUT DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 116 5

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# @A330 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 50 NSA5399-6-18A 1 SCREW 52 ASNA0094-6 2 NUT 53 MS21250-07018 1 SCREW 57 EN6115-5Y18 1 SCREW 58 ASNA2394EW6 2 WASHER 59 NSA5399-6-22A 1 SCREW 60 MS21250-07022 1 BOLT 82 ASNA2394EW7 2 WASHER 90 NSA5057-7 2 NUT 91 EN6115-5X18 1 SCREW 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 573115A03R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115-5X19 1 SCREW 9 ASNA2531-5 1 NUT 10 EN6115-5Y19 1 SCREW 50 NSA5399-6-18A 1 SCREW 51 NSA5372EW616B 2 WASHER 52 ASNA0094-6 2 NUT 53 MS21250-07018 1 SCREW 54 NSA5399-6-16A 1 SCREW 55 MS21250-07016 1 SCREW 80 NSA5372EW716B 2 WASHER 90 NSA5057-7 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. Kit 573115A04R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 8 EN6115-5X19 1 SCREW 9 ASNA2531-5 1 NUT 52 ASNA0094-6 2 NUT 61 MS21250-06018 1 SCREW 62 MS20002C6 2 WASHER 63 NSA5057-6 2 NUT 64 MS21250-06016 1 SCREW DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 117 5

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# @A330 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 65 NSA5398-6-18A 1 SCREW 66 NSA5398-6-16A 1 SCREW 88 EN6115-5-19 1 SCREW 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 573115A05R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 51 NSA5372EW616B 2 WASHER 52 ASNA0094-6 2 NUT 57 EN6115-5Y18 1 SCREW 58 ASNA2394EW6 2 WASHER 67 NSA5368PD516B 1 WASHER 80 NSA5372EW716B 2 WASHER 82 ASNA2394EW7 2 WASHER 83 NSA5050-5 1 NUT 84 NSA5399-6-23A 1 SCREW 85 MS21250-07023 1 SCREW 86 NSA5399-6-25A 1 SCREW 87 MS21250-07025 1 SCREW 90 NSA5057-7 2 NUT 91 EN6115-5X18 1 SCREW 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 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 EN6115V6-16 3 SCREW 2 ASNA2531-6 9 NUT 3 EN6115V6X16 3 SCREW 9 ASNA2531-5 1 NUT 52 ASNA0094-6 1 NUT 61 MS21250-06018 1 SCREW 62 MS20002C6 1 WASHER 63 NSA5057-6 1 NUT 65 NSA5398-6-18A 1 SCREW 73 EN6115V5-20 1 SCREW 74 EN6115V5X20 1 SCREW DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 118 5

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# @A330 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 75 EN6115V6-24 4 SCREW 76 EN6115V6X24 4 SCREW 78 ASNA2531-7 1 NUT 79 EN6115V7X16 1 SCREW 91 EN6115V6-19 1 SCREW 92 EN6115V6X19 1 SCREW 93 EN6115V6-22 1 SCREW 94 EN6115V7-16 1 SCREW 95 EN6115V6X22 1 SCREW NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required trichloroethane (methyl Chloroform) 11-004 As required Lint-Free Cotton Cloth 19-003 As required (2) Components NOTE: To accomplish this Service Bulletin it is necessary to use the expendable parts listed in the AMM Task 21-52-41-400-801 mentioned in paragraph close-up. (3) Equipment 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 the tools listed DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 119 5

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# @A330 SERVICE BULLETIN in the AMM Task 21-52-41-000-801 mentioned in paragraph job set-upand in the AMM Task 21-52-41-400-801 mentioned in paragraph closeup. (3) Special Tools None

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 120 5

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# @A330 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 573115-832-801-001 - Inspection WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR : - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR. 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. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. Task Associated Data **CONF 001 Zone 130 137 138 192 Manpower TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 121 5

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# @A330 SERVICE BULLETIN
**CONF 002 Zone 130 137 138 192 Manpower TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 **CONF 003 Zone 130 137 138 192 Manpower TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 **CONF 004 Zone 130 137 138 192 Manpower TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 **CONF 005 Zone 130 137 138 192 Manpower TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 **CONF 006 Zone 130 137 138 192 Manpower TOTAL MANHOURS 39.00 ELAPSED TIME (HOURS) 39.00 **CONF 007 Zone 130 137 138 192 Manpower TOTAL MANHOURS 38.00 ELAPSED TIME (HOURS) 38.00
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 122 5

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# @A330 SERVICE BULLETIN
**CONF ALL A. GENERAL CAUTION: To accomplish this Service Bulletin it is not necessary to put the aircraft under zero stress jacking. No zero stress jacking is required also in case of concurrent accomplishment of maintenance tasks or SBs in frame 40 area. However this is applicable only for the accomplishment of these tasks/SBs without deviation. Indeed, in case of heavy repair, a temporary re-installation of fasteners and/or zero stress jacking procedure could be anticipated. NOTE: The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. NOTE: The purpose of flow charts are for information only to show the various Inspection/Repair phases described in this Service Bulletin. **CONF 001 (1) Subtask 573115-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-40-00 51-42-00 51-44-11 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001. (c) For the specification of the material numbers (Mat. No.), refer to the Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant and clean the surfaces. (e) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00. (f) 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. (g) Remove and install the fasteners in accordance with SRM 51-42-00. DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 123 5

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# @A330 SERVICE BULLETIN (2) Subtask 573115-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 573115-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-40-00 51-42-00 51-44-11 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001. (c) For the specification of the material numbers (Mat. No.), refer to the Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant and clean the surfaces. (e) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00. (f) 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. (g) Remove and install the fasteners in accordance with SRM 51-42-00. (2) Subtask 573115-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 124 5

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# @A330 SERVICE BULLETIN
**CONF 003 (1) Subtask 573115-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-40-00 51-42-00 51-44-11 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001. (c) For the specification of the material numbers (Mat. No.), refer to the Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant and clean the surfaces. (e) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00. (f) 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. (g) Remove and install the fasteners in accordance with SRM 51-42-00. (2) Subtask 573115-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 004 (1) Subtask 573115-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 125 5

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# @A330 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-40-00 51-42-00 51-44-11 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001. (c) For the specification of the material numbers (Mat. No.), refer to the Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant and clean the surfaces. (e) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00. (f) 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. (g) Remove and install the fasteners in accordance with SRM 51-42-00. (2) Subtask 573115-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 005 (1) Subtask 573115-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-40-00 51-42-00 51-44-11 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 126 5

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# @A330 SERVICE BULLETIN (b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001. (c) For the specification of the material numbers (Mat. No.), refer to the Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant and clean the surfaces. (e) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00. (f) 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. (g) Remove and install the fasteners in accordance with SRM 51-42-00. (2) Subtask 573115-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 006 (1) Subtask 573115-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-40-00 51-42-00 51-44-11 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001. (c) For the specification of the material numbers (Mat. No.), refer to the Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant and clean the surfaces. (e) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00.
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 127 5

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# @A330 SERVICE BULLETIN (f) 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. (g) Remove and install the fasteners in accordance with SRM 51-42-00. (2) Subtask 573115-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 007 (1) Subtask 573115-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-40-00 51-42-00 51-44-11 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001. (c) For the specification of the material numbers (Mat. No.), refer to the Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant and clean the surfaces. (e) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00. (f) 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. (g) Remove and install the fasteners in accordance with SRM 51-42-00.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 128 5

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# @A330 SERVICE BULLETIN (2) Subtask 573115-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 573115-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position at doors 821 and 822. (2) Subtask 573115-861-001-001 - Energize Electrical Network Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801 (a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801). (3) Subtask 573115-865-001-001 - C/B Opening/Closing Manpower Resources Skills NON SPECIFIC (a) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 721 PACK 1 L1 115VAC 1HH1 02 F 721 PACK 1 L2 115VAC 3HH1 04 K 721 PACK 1 L2 28VDC 4HH1 07 R 721 PACK 1 L1 28VDC 2HH1 08 T 722 PACK 2 L2 115VAC 3HH2 44 E 722 PACK 2 L1 115VAC 1HH2 48 H 722 PACK 2 L2 28VDC 4HH2 41 U DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 129 5

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# @A330 SERVICE BULLETIN

PANEL DESIGNATION FIN LOCATION SEE NOTES 722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-002-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU: 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbutton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source.(5) Subtask 573115-010-001-001 - Remove/Open for Access in the FWD CargoCompartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 130 5

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# @A330 SERVICE BULLETIN (c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain
2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573115-010-002-001 - Remove/Open for Access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 27-84-41-000-802 Task 53-35-13-000-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. (a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-000-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 131 5

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# @A330 SERVICE BULLETIN (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) On the RH side, remove and retain the universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802). (7) Subtask 573115-110-001-001 - Cleaning of the Structure Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES trichloroethane (methyl Chloroform) 11-004 Lint-Free Cotton Cloth 19-003 As required WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH THE WORK AREA. THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN IRRITANTS. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 132 5

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# @A330 SERVICE BULLETIN
WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK. (a) Clean the inspection surface with trichloroethane (methyl Chloroform) 11-004 As required

and (if necessary) Lint-Free Cotton Cloth 19-003 As required (8) Subtask 573115-210-001-001 - Preparation of the Inspection Area Manpower Resources Skills NON SPECIFIC References Structural Repair Manual (SRM) 51-11-00, Page Block 001 51-22-00, Page Block 001 (a) Use a FLASHLIGHT to do this inspection if necessary. (b) Make sure that the surface of the inspection area is clean and smooth. (c) Do a visual check of the inspection area for damage or discontinuities. (d) Make sure that there is no : 1 Corrosion damage : - If you find corrosion damage, work In accordance with SRM 51-22-00, Page Block 001 for types, inspection, removal and corrosion protection. 2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) : - If you find this type of damage, work In accordance with SRM 51-11-00, Page Block 001 for damage classification and corrective action. **CONF 002 (1) Subtask 573115-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 133 5

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# @A330 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position at doors 821 and 822. (2) Subtask 573115-861-001-001 - Energize Electrical Network Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801 (a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801). (3) Subtask 573115-865-001-001 - C/B Opening/Closing Manpower Resources Skills NON SPECIFIC (a) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 721 PACK 1 L1 115VAC 1HH1 02 F 721 PACK 1 L2 115VAC 3HH1 04 K 721 PACK 1 L2 28VDC 4HH1 07 R 721 PACK 1 L1 28VDC 2HH1 08 T 722 PACK 2 L2 115VAC 3HH2 44 E 722 PACK 2 L1 115VAC 1HH2 48 H 722 PACK 2 L2 28VDC 4HH2 41 U 722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-002-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU: 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbutton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 134 5

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# @A330 SERVICE BULLETIN(5) Subtask 573115-010-001-001 - Remove/Open for Access in the FWD CargoCompartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801). (c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain
2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573115-010-002-001 - Remove/Open for Access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 135 5

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

# @A330 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 27-84-41-000-802 Task 53-35-13-000-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. (a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-000-802). (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) On the RH side, remove and retain the universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802). (7) Subtask 573115-110-001-001 - Cleaning of the Structure Manpower Resources Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 136 5

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

# @A330 SERVICE BULLETIN
Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES trichloroethane (methyl Chloroform) 11-004 Lint-Free Cotton Cloth 19-003 As required WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH THE WORK AREA. THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN IRRITANTS. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK. (a) Clean the inspection surface with trichloroethane (methyl Chloroform) 11-004 As required

and (if necessary) Lint-Free Cotton Cloth 19-003 As required (8) Subtask 573115-210-001-001 - Preparation of the Inspection Area Manpower Resources Skills NON SPECIFIC References Structural Repair Manual (SRM) 51-11-00, Page Block 001 51-22-00, Page Block 001 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 137 5

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

# @A330 SERVICE BULLETIN (a) Use a FLASHLIGHT to do this inspection if necessary. (b) Make sure that the surface of the inspection area is clean and smooth. (c) Do a visual check of the inspection area for damage or discontinuities. (d) Make sure that there is no : 1 Corrosion damage : - If you find corrosion damage, work In accordance with SRM 51-22-00, Page Block 001 for types, inspection, removal and corrosion protection. 2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) : - If you find this type of damage, work In accordance with SRM 51-11-00, Page Block 001 for damage classification and corrective action. **CONF 003 (1) Subtask 573115-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position at doors 821 and 822. (2) Subtask 573115-861-001-001 - Energize Electrical Network Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801 (a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801). (3) Subtask 573115-865-001-001 - C/B Opening/Closing Manpower Resources Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 138 5

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

# @A330 SERVICE BULLETIN (a) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 721 PACK 1 L1 115VAC 1HH1 02 F 721 PACK 1 L2 115VAC 3HH1 04 K 721 PACK 1 L2 28VDC 4HH1 07 R 721 PACK 1 L1 28VDC 2HH1 08 T 722 PACK 2 L2 115VAC 3HH2 44 E 722 PACK 2 L1 115VAC 1HH2 48 H 722 PACK 2 L2 28VDC 4HH2 41 U 722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-002-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU: 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbutton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source.(5) Subtask 573115-010-001-001 - Remove/Open for Access in the FWD CargoCompartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 139 5

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# @A330 SERVICE BULLETIN (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801). (c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain
2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573115-010-002-001 - Remove/Open for Access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 27-84-41-000-802 Task 53-35-13-000-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. (a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-000-802). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 140 5

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

# @A330 SERVICE BULLETIN (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) On the RH side, remove and retain the universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802). (7) Subtask 573115-110-001-001 - Cleaning of the Structure Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES trichloroethane (methyl Chloroform) 11-004 Lint-Free Cotton Cloth 19-003 As required WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH THE WORK AREA. THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN IRRITANTS. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 141 5

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

# @A330 SERVICE BULLETIN
WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK. (a) Clean the inspection surface with trichloroethane (methyl Chloroform) 11-004 As required

and (if necessary) Lint-Free Cotton Cloth 19-003 As required (8) Subtask 573115-210-001-001 - Preparation of the Inspection Area Manpower Resources Skills NON SPECIFIC References Structural Repair Manual (SRM) 51-11-00, Page Block 001 51-22-00, Page Block 001 (a) Use a FLASHLIGHT to do this inspection if necessary. (b) Make sure that the surface of the inspection area is clean and smooth. (c) Do a visual check of the inspection area for damage or discontinuities. (d) Make sure that there is no : 1 Corrosion damage : - If you find corrosion damage, work In accordance with SRM 51-22-00, Page Block 001 for types, inspection, removal and corrosion protection. 2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) : - If you find this type of damage, work In accordance with SRM 51-11-00, Page Block 001 for damage classification and corrective action. **CONF 004 (1) Subtask 573115-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 142 5

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

# @A330 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position at doors 821 and 822. (2) Subtask 573115-861-001-001 - Energize Electrical Network Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801 (a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801). (3) Subtask 573115-865-001-001 - C/B Opening/Closing Manpower Resources Skills NON SPECIFIC (a) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 721 PACK 1 L1 115VAC 1HH1 02 F 721 PACK 1 L2 115VAC 3HH1 04 K 721 PACK 1 L2 28VDC 4HH1 07 R 721 PACK 1 L1 28VDC 2HH1 08 T 722 PACK 2 L2 115VAC 3HH2 44 E 722 PACK 2 L1 115VAC 1HH2 48 H 722 PACK 2 L2 28VDC 4HH2 41 U 722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-002-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU: 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbutton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 143 5

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

# @A330 SERVICE BULLETIN(5) Subtask 573115-010-001-001 - Remove/Open for Access in the FWD CargoCompartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801). (c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain
2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573115-010-002-001 - Remove/Open for Access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 144 5

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

# @A330 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 27-84-41-000-802 Task 53-35-13-000-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. (a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-000-802). (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) On the RH side, remove and retain the universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802). (7) Subtask 573115-110-001-001 - Cleaning of the Structure Manpower Resources Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 145 5

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

# @A330 SERVICE BULLETIN
Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES trichloroethane (methyl Chloroform) 11-004 Lint-Free Cotton Cloth 19-003 As required WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH THE WORK AREA. THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN IRRITANTS. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK. (a) Clean the inspection surface with trichloroethane (methyl Chloroform) 11-004 As required

and (if necessary) Lint-Free Cotton Cloth 19-003 As required (8) Subtask 573115-210-001-001 - Preparation of the Inspection Area Manpower Resources Skills NON SPECIFIC References Structural Repair Manual (SRM) 51-11-00, Page Block 001 51-22-00, Page Block 001 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 146 5

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

# @A330 SERVICE BULLETIN (a) Use a FLASHLIGHT to do this inspection if necessary. (b) Make sure that the surface of the inspection area is clean and smooth. (c) Do a visual check of the inspection area for damage or discontinuities. (d) Make sure that there is no : 1 Corrosion damage : - If you find corrosion damage, work In accordance with SRM 51-22-00, Page Block 001 for types, inspection, removal and corrosion protection. 2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) : - If you find this type of damage, work In accordance with SRM 51-11-00, Page Block 001 for damage classification and corrective action. **CONF 005 (1) Subtask 573115-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position at doors 821 and 822. (2) Subtask 573115-861-001-001 - Energize Electrical Network Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801 (a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801). (3) Subtask 573115-865-001-001 - C/B Opening/Closing Manpower Resources Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 147 5

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

# @A330 SERVICE BULLETIN (a) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 721 PACK 1 L1 115VAC 1HH1 02 F 721 PACK 1 L2 115VAC 3HH1 04 K 721 PACK 1 L2 28VDC 4HH1 07 R 721 PACK 1 L1 28VDC 2HH1 08 T 722 PACK 2 L2 115VAC 3HH2 44 E 722 PACK 2 L1 115VAC 1HH2 48 H 722 PACK 2 L2 28VDC 4HH2 41 U 722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-002-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU: 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbutton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source.(5) Subtask 573115-010-001-001 - Remove/Open for Access in the FWD CargoCompartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 148 5

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

# @A330 SERVICE BULLETIN (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801). (c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain
2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573115-010-002-001 - Remove/Open for Access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 27-84-41-000-802 Task 53-35-13-000-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. (a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-000-802). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 149 5

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

# @A330 SERVICE BULLETIN (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) On the RH side, remove and retain the universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802). (7) Subtask 573115-110-001-001 - Cleaning of the Structure Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES trichloroethane (methyl Chloroform) 11-004 Lint-Free Cotton Cloth 19-003 As required WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH THE WORK AREA. THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN IRRITANTS. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 150 5

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

# @A330 SERVICE BULLETIN
WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK. (a) Clean the inspection surface with trichloroethane (methyl Chloroform) 11-004 As required

and (if necessary) Lint-Free Cotton Cloth 19-003 As required (8) Subtask 573115-210-001-001 - Preparation of the Inspection Area Manpower Resources Skills NON SPECIFIC References Structural Repair Manual (SRM) 51-11-00, Page Block 001 51-22-00, Page Block 001 (a) Use a FLASHLIGHT to do this inspection if necessary. (b) Make sure that the surface of the inspection area is clean and smooth. (c) Do a visual check of the inspection area for damage or discontinuities. (d) Make sure that there is no : 1 Corrosion damage : - If you find corrosion damage, work In accordance with SRM 51-22-00, Page Block 001 for types, inspection, removal and corrosion protection. 2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) : - If you find this type of damage, work In accordance with SRM 51-11-00, Page Block 001 for damage classification and corrective action. **CONF 006 (1) Subtask 573115-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 151 5

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

# @A330 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position at doors 821 and 822. (2) Subtask 573115-861-001-001 - Energize Electrical Network Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801 (a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801). (3) Subtask 573115-865-001-001 - C/B Opening/Closing Manpower Resources Skills NON SPECIFIC (a) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 721 PACK 1 L1 115VAC 1HH1 02 F 721 PACK 1 L2 115VAC 3HH1 04 K 721 PACK 1 L2 28VDC 4HH1 07 R 721 PACK 1 L1 28VDC 2HH1 08 T 722 PACK 2 L2 115VAC 3HH2 44 E 722 PACK 2 L1 115VAC 1HH2 48 H 722 PACK 2 L2 28VDC 4HH2 41 U 722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-002-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU: 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbutton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 152 5

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# @A330 SERVICE BULLETIN(5) Subtask 573115-010-001-001 - Remove/Open for Access in the FWD CargoCompartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801). (c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain
2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573115-010-002-001 - Remove/Open for Access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 153 5

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# @A330 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 27-84-41-000-802 Task 53-35-13-000-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. (a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-000-802). (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) On the RH side, remove and retain the universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802). (7) Subtask 573115-110-001-001 - Cleaning of the Structure Manpower Resources Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 154 5

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# @A330 SERVICE BULLETIN
Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES trichloroethane (methyl Chloroform) 11-004 Lint-Free Cotton Cloth 19-003 As required WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH THE WORK AREA. THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN IRRITANTS. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK. (a) Clean the inspection surface with trichloroethane (methyl Chloroform) 11-004 As required

and (if necessary) Lint-Free Cotton Cloth 19-003 As required (8) Subtask 573115-210-001-001 - Preparation of the Inspection Area Manpower Resources Skills NON SPECIFIC References Structural Repair Manual (SRM) 51-11-00, Page Block 001 51-22-00, Page Block 001 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 155 5

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# @A330 SERVICE BULLETIN (a) Use a FLASHLIGHT to do this inspection if necessary. (b) Make sure that the surface of the inspection area is clean and smooth. (c) Do a visual check of the inspection area for damage or discontinuities. (d) Make sure that there is no : 1 Corrosion damage : - If you find corrosion damage, work In accordance with SRM 51-22-00, Page Block 001 for types, inspection, removal and corrosion protection. 2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) : - If you find this type of damage, work In accordance with SRM 51-11-00, Page Block 001 for damage classification and corrective action. **CONF 007 (1) Subtask 573115-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position at doors 821 and 822. (2) Subtask 573115-861-001-001 - Energize Electrical Network Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801 (a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801). (3) Subtask 573115-865-001-001 - C/B Opening/Closing Manpower Resources Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 156 5

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# @A330 SERVICE BULLETIN (a) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 721 PACK 1 L1 115VAC 1HH1 02 F 721 PACK 1 L2 115VAC 3HH1 04 K 721 PACK 1 L2 28VDC 4HH1 07 R 721 PACK 1 L1 28VDC 2HH1 08 T 722 PACK 2 L2 115VAC 3HH2 44 E 722 PACK 2 L1 115VAC 1HH2 48 H 722 PACK 2 L2 28VDC 4HH2 41 U 722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-002-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU: 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbutton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source.(5) Subtask 573115-010-001-001 - Remove/Open for Access in the FWD CargoCompartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 157 5

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# @A330 SERVICE BULLETIN (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801). (c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain
2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573115-010-002-001 - Remove/Open for Access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 27-84-41-000-802 Task 53-35-13-000-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. (a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-000-802). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 158 5

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# @A330 SERVICE BULLETIN (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) On the RH side, remove and retain the universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802). (7) Subtask 573115-110-001-001 - Cleaning of the Structure Manpower Resources Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES trichloroethane (methyl Chloroform) 11-004 Lint-Free Cotton Cloth 19-003 As required WARNING: USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH THE WORK AREA. THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN IRRITANTS. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 159 5

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# @A330 SERVICE BULLETIN
WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE THIS/THESE MATERIAL/S. USE PROTECTIVE CLOTHING, RUBBER GLOVES, GOGGLES AND A MASK. (a) Clean the inspection surface with trichloroethane (methyl Chloroform) 11-004 As required

and (if necessary) Lint-Free Cotton Cloth 19-003 As required (8) Subtask 573115-210-001-001 - Preparation of the Inspection Area Manpower Resources Skills NON SPECIFIC References Structural Repair Manual (SRM) 51-11-00, Page Block 001 51-22-00, Page Block 001 (a) Use a FLASHLIGHT to do this inspection if necessary. (b) Make sure that the surface of the inspection area is clean and smooth. (c) Do a visual check of the inspection area for damage or discontinuities. (d) Make sure that there is no : 1 Corrosion damage : - If you find corrosion damage, work In accordance with SRM 51-22-00, Page Block 001 for types, inspection, removal and corrosion protection. 2 Other damage (cracks, scratches, stress, marks, dents, bumps, ...) : - If you find this type of damage, work In accordance with SRM 51-11-00, Page Block 001 for damage classification and corrective action.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 160 5

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# @A330 SERVICE BULLETIN
**CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 573115-832-001-001 - Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Service Bulletin (SB) A330-57-3083 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) If Service Bulletin No. A330-57-3083 is accomplished: 1 Do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). (b) If Service Bulletin No. A330-57-3083 is not accomplished: 1 Do SUBTASK 573115-832-003 001 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 3 of the Planning Information Paragraph E.(2).
or Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 161 5

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# @A330 SERVICE BULLETIN (2) Subtask 573115-832-007-001 - Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Service Bulletin (SB) A330-57-3083 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) If Service Bulletin No. A330-57-3083 is accomplished: 1 Do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). (b) If Service Bulletin No. A330-57-3083 is not accomplished: 1 Do SUBTASK 573115-832-009 001 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 3 of the Planning Information Paragraph E.(2).
or Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. (3) Subtask 573115-832-002-001 - Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 162 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) Do SUBTASK 573115-832-010 002 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the threshold given in the table 5 of the Planning Information Paragraph E.(2). (4) Subtask 573115-832-008-001 - Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) Do SUBTASK 573115-832-011 002 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the threshold given in the table 5 of the Planning Information Paragraph E.(2). (5) Subtask 573115-832-003-001 - Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 163 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCCAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, LH side. - Remove the fastener from hole H260, LH side: 1 Screw Item (6) Discard 1 Nut Item (2) Discard - Do a rototest inspection at the hole H260, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-001 004 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-003 001 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2).
or
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 164 5

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# @A330 SERVICE BULLETIN
b Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. 2 If crack is found:
a Apply SUBTASK 573115-833-004 001 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-007 001 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-003 001 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (6) Subtask 573115-832-009-001 - Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 165 5

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# @A330 SERVICE BULLETIN

References Service Bulletin (SB) A330-57-3083 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, RH side. - Remove the fastener from hole H260, RH side: 1 Screw Item (6) Discard 1 Nut Item (2) Discard - Do a rototest inspection at the hole H260, RH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-010 002 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-009 001 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2).
or b Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 166 5

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# @A330 SERVICE BULLETIN

2 If crack is found:
a Apply SUBTASK 573115-833-014 001 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-018 001 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-009 001 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (7) Subtask 573115-832-004-001 - Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 167 5

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# @A330 SERVICE BULLETIN
Refer toFig. A-FCDAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, LH side. - Remove fastener from hole H260, LH side: 1 Screw Item (77) Discard 1 Nut Item (78) Discard - Do a rototest inspection at the hole H260, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-002 001 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-005 001 Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-008 001 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2).
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 168 5

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# @A330 SERVICE BULLETIN <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (8) Subtask 573115-832-005-001 - Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, RH side. - Remove fastener from hole H260, RH side: 1 Screw Item (77) Discard 1 Nut Item (78) Discard - Do a rototest inspection at the hole H260, RH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 169 5

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# @A330 SERVICE BULLETIN

1 If no crack is found:
a Apply SUBTASK 573115-833-011 001 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-015 001 Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-019 001 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (9) Subtask 573115-832-010-002 - Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 170 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAB Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the holes of the area B of the frame 40, LH side. - Remove fasteners from hole H12 and H14, LH side: 2 Screw Item (1) Discard 2 Nut Item (2) Discard - Remove fastener from hole H13, LH side: 1 Screw Item (4) Discard 1 Nut Item (2) Discard - Remove fasteners from holes H21, H22, H23 and H24, LH side: 4 Screw Item (6) Discard 4 Nut Item (2) Discard - Remove fastener from hole H261, LH side: 1 Screw Item (56) Discard 1 Nut Item (9) Discard - Remove fastener from hole H262, LH side: 1 Screw Item (59) Discard
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 171 5

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# @A330 SERVICE BULLETIN
1 Washer Item (58) Discard 1 Nut Item (52) Discard - Remove fastener from hole H263, LH side: 1 Screw Item (50) Discard 1 Washer Item (58) Discard 1 Nut Item (52) Discard - Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-022 002 Install New same Fasteners of the Area B in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-010 002 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-023 002 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-024 002 Install New Fasteners of the Area B in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-010 002 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 172 5

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# @A330 SERVICE BULLETIN (b) For the inspection report, refer to Appendix 01. (10) Subtask 573115-832-011-002 - Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAB Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the holes of the area B of the frame 40, RH side. - Remove fasteners from hole H12 and H14, RH side: 2 Screw Item (1) Discard 2 Nut Item (2) Discard - Remove fastener from hole H13, RH side: 1 Screw Item (4) Discard 1 Nut Item (2) Discard - Remove fasteners from holes H21, H22, H23 and H24, RH side: 4 Screw Item (6) Discard 4 Nut Item (2) Discard - Remove fastener from hole H261, RH side: DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 173 5

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# @A330 SERVICE BULLETIN
1 Screw Item (56) Discard 1 Nut Item (9) Discard - Remove fastener from hole H262, RH side: 1 Screw Item (59) Discard 1 Washer Item (58) Discard 1 Nut Item (52) Discard - Remove fastener from hole H263, RH side: 1 Screw Item (50) Discard 1 Washer Item (58) Discard 1 Nut Item (52) Discard - Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-013 002 Install New same Fasteners of the Area B in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-011 002 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-017 002 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-021 002 Install New Fasteners of the Area B in transition fit, RH Side before next flight and
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 174 5

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# @A330 SERVICE BULLETIN Repeat the rototest inspection as described in SUBTASK 573115-832-011 002 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. **CONF 002 (1) Subtask 573115-832-001-001 - Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Service Bulletin (SB) A330-57-3083 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) If Service Bulletin No. A330-57-3083 is accomplished: 1 Do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). (b) If Service Bulletin No. A330-57-3083 is not accomplished: 1 Do SUBTASK 573115-832-003 003 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 3 of the Planning Information Paragraph E.(2).
or

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 175 5

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# @A330 SERVICE BULLETIN Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. (2) Subtask 573115-832-007-001 - Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Service Bulletin (SB) A330-57-3083 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) If Service Bulletin No. A330-57-3083 is accomplished: 1 Do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). (b) If Service Bulletin No. A330-57-3083 is not accomplished: 1 Do SUBTASK 573115-832-009 003 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 3 of the Planning Information Paragraph E.(2).
or Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 176 5

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# @A330 SERVICE BULLETIN (3) Subtask 573115-832-002-009 - Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC References Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) Do SUBTASK 573115-832-010 001 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the threshold given in the table 5 of the Planning Information Paragraph E.(2). (4) Subtask 573115-832-008-002 - Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) Do SUBTASK 573115-832-011 001 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the threshold given in the table 5 of the Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 177 5

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# @A330 SERVICE BULLETIN (5) Subtask 573115-832-003-003 - Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, LH side. - Remove the fastener from hole H260, LH side: 1 Screw Item (6) Discard 1 Nut Item (2) Discard - Do a rototest inspection at the hole H260, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-001 001 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 178 5

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# @A330 SERVICE BULLETIN Repeat the rototest inspection as described in SUBTASK 573115-832-003 003 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2).
or b Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. 2 If crack is found:
a Apply SUBTASK 573115-833-004 001 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-007 001 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-003 003 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (6) Subtask 573115-832-009-003 - Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 179 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, RH side. - Remove the fastener from hole H260, RH side: 1 Screw Item (6) Discard 1 Nut Item (2) Discard - Do a rototest inspection at the hole H260, RH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-010 001 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-009 003 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2).
or
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 180 5

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# @A330 SERVICE BULLETIN
b Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. 2 If crack is found:
a Apply SUBTASK 573115-833-014 001 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-018 001 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-009 003 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (7) Subtask 573115-832-004-001 - Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 181 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCDAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, LH side. - Remove fastener from hole H260, LH side: 1 Screw Item (77) Discard 1 Nut Item (78) Discard - Do a rototest inspection at the hole H260, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-002 001 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 182 5

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# @A330 SERVICE BULLETIN

2 If crack is found:
a Apply SUBTASK 573115-833-005 001 Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-008 001 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (8) Subtask 573115-832-005-001 - Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 183 5

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# @A330 SERVICE BULLETIN
Refer toFig. A-FCDAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, RH side. - Remove fastener from hole H260, RH side: 1 Screw Item (77) Discard 1 Nut Item (78) Discard - Do a rototest inspection at the hole H260, RH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-011 001 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-015 001 Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-019 001 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2).
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 184 5

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# @A330 SERVICE BULLETIN <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (9) Subtask 573115-832-010-001 - Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAA Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the holes of the area B of the frame 40, LH side. - Remove fasteners from hole H12 and H14, LH side: 2 Screw Item (1) Discard 2 Nut Item (2) Discard - Remove fastener from hole H13, LH side: 1 Screw Item (4) Discard 1 Nut Item (2) Discard - Remove fasteners from holes H21, H22, H23 and H24, LH side: 4 Screw Item (6) Discard DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 185 5

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# @A330 SERVICE BULLETIN
4 Nut Item (2) Discard - Remove fastener from hole H261, LH side: 1 Screw Item (8) Discard 1 Nut Item (9) Discard - Remove fastener from hole H262, LH side: 1 Screw Item (50) Discard 1 Washer Item (51) Discard 1 Nut Item (52) Discard - Remove fastener from hole H263, LH side: 1 Screw Item (54) Discard 1 Washer Item (51) Discard 1 Nut Item (52) Discard - Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-022 001 Install New same Fasteners of the Area B in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-010 001 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 186 5

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# @A330 SERVICE BULLETIN

2 If crack is found:
a Apply SUBTASK 573115-833-023 001 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-024 001 Install New Fasteners of the Area B in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-010 001 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (10) Subtask 573115-832-011-001 - Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAA Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAA At the threshold given in the Planning Information Paragraph E.(2): DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 187 5

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# @A330 SERVICE BULLETIN (a) Do a rototest inspection of the holes of the area B of the frame 40, RH side. - Remove fasteners from hole H12 and H14, RH side: 2 Screw Item (1) Discard 2 Nut Item (2) Discard - Remove fastener from hole H13, RH side: 1 Screw Item (4) Discard 1 Nut Item (2) Discard - Remove fasteners from holes H21, H22, H23 and H24, RH side: 4 Screw Item (6) Discard 4 Nut Item (2) Discard - Remove fastener from hole H261, RH side: 1 Screw Item (8) Discard 1 Nut Item (9) Discard - Remove fastener from hole H262, RH side: 1 Screw Item (50) Discard 1 Washer Item (51) Discard 1 Nut Item (52) Discard - Remove fastener from hole H263, RH side: 1 Screw Item (54) Discard 1 Washer Item (51) Discard 1 Nut Item (52) Discard - Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 188 5

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# @A330 SERVICE BULLETIN

1 If no crack is found:
a Apply SUBTASK 573115-833-013 001 Install New same Fasteners of the Area B in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-011 001 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-017 001 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-021 001 Install New Fasteners of the Area B in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-011 001 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. **CONF 003 (1) Subtask 573115-832-001-001 - Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 189 5

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# @A330 SERVICE BULLETIN

References Service Bulletin (SB) A330-57-3083 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) If Service Bulletin No. A330-57-3083 is accomplished: 1 Do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). (b) If Service Bulletin No. A330-57-3083 is not accomplished: 1 Do SUBTASK 573115-832-003 004 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 3 of the Planning Information Paragraph E.(2).
or Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. (2) Subtask 573115-832-007-001 - Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Service Bulletin (SB) A330-57-3083 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 190 5

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# @A330 SERVICE BULLETIN
Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) If Service Bulletin No. A330-57-3083 is accomplished: 1 Do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). (b) If Service Bulletin No. A330-57-3083 is not accomplished: 1 Do SUBTASK 573115-832-009 004 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 3 of the Planning Information Paragraph E.(2).
or Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. (3) Subtask 573115-832-002-010 - Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC References Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) Do SUBTASK 573115-832-010 003 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the threshold given in the table 5 of the Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 191 5

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# @A330 SERVICE BULLETIN (4) Subtask 573115-832-008-003 - Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) Do SUBTASK 573115-832-011 003 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the threshold given in the table 5 of the Planning Information Paragraph E.(2). (5) Subtask 573115-832-003-004 - Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCCAA Sheet 01
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 192 5

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# @A330 SERVICE BULLETIN At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, LH side. - Remove the fastener from hole H260, LH side: 1 Screw Item (6) Discard 1 Nut Item (2) Discard - Do a rototest inspection at the hole H260, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-001 005 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-003 004 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2).
or b Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. 2 If crack is found:
a Apply SUBTASK 573115-833-004 001 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 193 5

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# @A330 SERVICE BULLETIN <2> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-007 001 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-003 004 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (6) Subtask 573115-832-009-004 - Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, RH side. - Remove the fastener from hole H260, RH side:
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 194 5

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# @A330 SERVICE BULLETIN
1 Screw Item (6) Discard 1 Nut Item (2) Discard - Do a rototest inspection at the hole H260, RH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-010 003 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-009 004 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2).
or b Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. 2 If crack is found:
a Apply SUBTASK 573115-833-014 001 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-018 001 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 195 5

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# @A330 SERVICE BULLETIN Repeat the rototest inspection as described in SUBTASK 573115-832-009 004 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (7) Subtask 573115-832-004-001 - Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCDAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, LH side. - Remove fastener from hole H260, LH side: 1 Screw Item (77) Discard 1 Nut Item (78) Discard - Do a rototest inspection at the hole H260, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 196 5

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# @A330 SERVICE BULLETIN

1 If no crack is found:
a Apply SUBTASK 573115-833-002 001 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-005 001 Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-008 001 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (8) Subtask 573115-832-005-001 - Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 197 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, RH side. - Remove fastener from hole H260, RH side: 1 Screw Item (77) Discard 1 Nut Item (78) Discard - Do a rototest inspection at the hole H260, RH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-011 001 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 198 5

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# @A330 SERVICE BULLETIN

2 If crack is found:
a Apply SUBTASK 573115-833-015 001 Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-019 001 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (9) Subtask 573115-832-010-003 - Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAC Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 199 5

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# @A330 SERVICE BULLETIN At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the holes of the area B of the frame 40, LH side. - Remove fasteners from hole H12 and H14, LH side: 2 Screw Item (1) Discard 2 Nut Item (2) Discard - Remove fastener from hole H13, LH side: 1 Screw Item (4) Discard 1 Nut Item (2) Discard - Remove fasteners from holes H21, H22, H23 and H24, LH side: 4 Screw Item (6) Discard 4 Nut Item (2) Discard - Remove fastener from hole H261, LH side: 1 Screw Item (88) Discard 1 Nut Item (9) Discard - Remove fastener from hole H262, LH side: 1 Screw Item (61) Discard 1 Washer Item (62) Discard 1 Nut Item (63) Discard - Remove fastener from hole H263, LH side: 1 Screw Item (64) Discard 1 Washer Item (62) Discard 1 Nut Item (63) Discard - Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 200 5

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# @A330 SERVICE BULLETIN

1 If no crack is found:
a Apply SUBTASK 573115-833-022 003 Install New same Fasteners of the Area B in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-010 003 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-023 003 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-024 003 Install New Fasteners of the Area B in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-010 003 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (10) Subtask 573115-832-011-003 - Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 201 5

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# @A330 SERVICE BULLETIN

References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAC Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the holes of the area B of the frame 40, RH side. - Remove fasteners from hole H12 and H14, RH side: 2 Screw Item (1) Discard 2 Nut Item (2) Discard - Remove fastener from hole H13, RH side: 1 Screw Item (4) Discard 1 Nut Item (2) Discard - Remove fasteners from holes H21, H22, H23 and H24, RH side: 4 Screw Item (6) Discard 4 Nut Item (2) Discard - Remove fastener from hole H261, RH side: 1 Screw Item (88) Discard 1 Nut Item (9) Discard - Remove fastener from hole H262, RH side: 1 Screw Item (61) Discard 1 Washer Item (62) Discard 1 Nut Item (63) Discard - Remove fastener from hole H263, RH side:
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 202 5

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# @A330 SERVICE BULLETIN
1 Screw Item (64) Discard 1 Washer Item (62) Discard 1 Nut Item (63) Discard - Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-013 003 Install New same Fasteners of the Area B in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-011 003 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-017 003 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-021 003 Install New Fasteners of the Area B in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-011 003 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 203 5

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# @A330 SERVICE BULLETIN
**CONF 004 (1) Subtask 573115-832-001-001 - Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Service Bulletin (SB) A330-57-3083 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) If Service Bulletin No. A330-57-3083 is accomplished: 1 Do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). (b) If Service Bulletin No. A330-57-3083 is not accomplished: 1 Do SUBTASK 573115-832-003 005 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 3 of the Planning Information Paragraph E.(2).
or Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 204 5

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# @A330 SERVICE BULLETIN (2) Subtask 573115-832-007-001 - Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Service Bulletin (SB) A330-57-3083 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) If Service Bulletin No. A330-57-3083 is accomplished: 1 Do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). (b) If Service Bulletin No. A330-57-3083 is not accomplished: 1 Do SUBTASK 573115-832-009 005 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 3 of the Planning Information Paragraph E.(2).
or Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. (3) Subtask 573115-832-002-011 - Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 205 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC References Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) Do SUBTASK 573115-832-010 004 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the threshold given in the table 5 of the Planning Information Paragraph E.(2). (4) Subtask 573115-832-008-004 - Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) Do SUBTASK 573115-832-011 004 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the threshold given in the table 5 of the Planning Information Paragraph E.(2). (5) Subtask 573115-832-003-005 - Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 206 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, LH side. - Remove the fastener from hole H260, LH side: 1 Screw Item (6) Discard 1 Nut Item (2) Discard - Do a rototest inspection at the hole H260, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-001 008 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-003 005 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2).
or
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 207 5

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# @A330 SERVICE BULLETIN
b Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. 2 If crack is found:
a Apply SUBTASK 573115-833-004 001 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-007 001 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-003 005 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (6) Subtask 573115-832-009-005 - Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 208 5

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# @A330 SERVICE BULLETIN

References Service Bulletin (SB) A330-57-3083 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, RH side. - Remove the fastener from hole H260, RH side: 1 Screw Item (6) Discard 1 Nut Item (2) Discard - Do a rototest inspection at the hole H260, RH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-010 004 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-009 005 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2).
or b Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 209 5

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# @A330 SERVICE BULLETIN

2 If crack is found:
a Apply SUBTASK 573115-833-014 001 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-018 001 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-009 005 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (7) Subtask 573115-832-004-001 - Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 210 5

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# @A330 SERVICE BULLETIN
Refer toFig. A-FCDAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, LH side. - Remove fastener from hole H260, LH side: 1 Screw Item (77) Discard 1 Nut Item (78) Discard - Do a rototest inspection at the hole H260, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-002 001 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-005 001 Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-008 001 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2).
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 211 5

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# @A330 SERVICE BULLETIN <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (8) Subtask 573115-832-005-001 - Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, RH side. - Remove fastener from hole H260, RH side: 1 Screw Item (77) Discard 1 Nut Item (78) Discard - Do a rototest inspection at the hole H260, RH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 212 5

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# @A330 SERVICE BULLETIN

1 If no crack is found:
a Apply SUBTASK 573115-833-011 001 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-015 001 Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-019 001 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (9) Subtask 573115-832-010-004 - Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 213 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAD Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAD Sheet 01 toFig. A-FCAAD Sheet 03 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the holes of the area B of the frame 40, LH side. - Remove fasteners from hole H12 and H14, LH side: 2 Screw Item (1) Discard 2 Nut Item (2) Discard - Remove fastener from hole H13, LH side: 1 Screw Item (4) Discard 1 Nut Item (2) Discard - Remove fasteners from holes H21, H22, H23 and H24, LH side: 4 Screw Item (6) Discard 4 Nut Item (2) Discard - Remove fastener from hole H261, LH side: 1 Screw Item (91) Discard 1 Washer Item (67) Discard 1 Nut Item (83) Discard - Remove fastener from hole H262, LH side: DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 214 5

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# @A330 SERVICE BULLETIN
1 Screw Item (84) Discard 1 Washer Item (88) Discard 1 Washer Item (51) Discard 1 Nut Item (52) Discard - Remove fastener from hole H263, LH side: 1 Screw Item (86) Discard 1 Washer Item (58) Discard 1 Washer Item (51) Discard 1 Nut Item (52) Discard - Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-022 004 Install New same Fasteners of the Area B in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-010 004 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-023 004 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-024 004 Install New Fasteners of the Area B in transition fit, LH Side before next flight and

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 215 5

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# @A330 SERVICE BULLETIN Repeat the rototest inspection as described in SUBTASK 573115-832-010 004 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (10) Subtask 573115-832-011-004 - Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAD Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Sheet 03 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAD Sheet 01 toFig. A-FCAAD Sheet 03 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the holes of the area B of the frame 40, RH side. - Remove fasteners from hole H12 and H14, LH side: 2 Screw Item (1) Discard 2 Nut Item (2) Discard - Remove fastener from hole H13, LH side: 1 Screw Item (4) Discard
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 216 5

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# @A330 SERVICE BULLETIN
1 Nut Item (2) Discard - Remove fasteners from holes H21, H22, H23 and H24, LH side: 4 Screw Item (6) Discard 4 Nut Item (2) Discard - Remove fastener from hole H261, LH side: 1 Screw Item (91) Discard 1 Washer Item (67) Discard 1 Nut Item (83) Discard - Remove fastener from hole H262, LH side: 1 Screw Item (84) Discard 1 Washer Item (88) Discard 1 Washer Item (51) Discard 1 Nut Item (52) Discard - Remove fastener from hole H263, LH side: 1 Screw Item (86) Discard 1 Washer Item (58) Discard 1 Washer Item (51) Discard 1 Nut Item (52) Discard - Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-013 004 Install New same Fasteners of the Area B in transition fit, RH Side before next flight and

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 217 5

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# @A330 SERVICE BULLETIN Repeat the rototest inspection as described in SUBTASK 573115-832-011 004 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-017 004 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-021 004 Install New Fasteners of the Area B in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-011 004 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. **CONF 005 (1) Subtask 573115-832-001-001 - Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Service Bulletin (SB) A330-57-3083 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 218 5

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# @A330 SERVICE BULLETIN
Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) If Service Bulletin No. A330-57-3083 is accomplished: 1 Do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). (b) If Service Bulletin No. A330-57-3083 is not accomplished: 1 Do SUBTASK 573115-832-003 006 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 3 of the Planning Information Paragraph E.(2).
or Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. (2) Subtask 573115-832-007-001 - Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Service Bulletin (SB) A330-57-3083 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 219 5

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# @A330 SERVICE BULLETIN (a) If Service Bulletin No. A330-57-3083 is accomplished: 1 Do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). (b) If Service Bulletin No. A330-57-3083 is not accomplished: 1 Do SUBTASK 573115-832-009 006 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 3 of the Planning Information Paragraph E.(2).
or Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. (3) Subtask 573115-832-002-012 - Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC References Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) Do SUBTASK 573115-832-010 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the threshold given in the table 5 of the Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 220 5

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# @A330 SERVICE BULLETIN (4) Subtask 573115-832-008-005 - Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) Do SUBTASK 573115-832-011 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the threshold given in the table 5 of the Planning Information Paragraph E.(2). (5) Subtask 573115-832-003-006 - Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 221 5

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# @A330 SERVICE BULLETIN
Refer toFig. A-FCCAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, LH side. - Remove the fastener from hole H260, LH side: 1 Screw Item (6) Discard 1 Nut Item (2) Discard - Do a rototest inspection at the hole H260, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-001 007 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-003 006 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2).
or b Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. 2 If crack is found:
a Apply SUBTASK 573115-833-004 001 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 222 5

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# @A330 SERVICE BULLETIN <2> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-007 015 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-003 006 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (6) Subtask 573115-832-009-006 - Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, RH side. - Remove the fastener from hole H260, RH side:
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 223 5

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# @A330 SERVICE BULLETIN
1 Screw Item (6) Discard 1 Nut Item (2) Discard - Do a rototest inspection at the hole H260, RH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-010 005 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-009 006 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2).
or b Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. 2 If crack is found:
a Apply SUBTASK 573115-833-014 001 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-018 003 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 224 5

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# @A330 SERVICE BULLETIN Repeat the rototest inspection as described in SUBTASK 573115-832-009 006 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (7) Subtask 573115-832-004-001 - Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCDAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, LH side. - Remove fastener from hole H260, LH side: 1 Screw Item (77) Discard 1 Nut Item (78) Discard - Do a rototest inspection at the hole H260, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 225 5

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# @A330 SERVICE BULLETIN

1 If no crack is found:
a Apply SUBTASK 573115-833-002 015 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-005 001 Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-008 015 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (8) Subtask 573115-832-005-001 - Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 226 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, RH side. - Remove fastener from hole H260, RH side: 1 Screw Item (77) Discard 1 Nut Item (78) Discard - Do a rototest inspection at the hole H260, RH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-011 003 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 227 5

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# @A330 SERVICE BULLETIN

2 If crack is found:
a Apply SUBTASK 573115-833-015 001 Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-019 003 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (9) Subtask 573115-832-010-005 - Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 228 5

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# @A330 SERVICE BULLETIN At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the holes of the area B of the frame 40, LH side. - Remove fasteners from hole H12 and H14, LH side: 2 Screw Item (1) Discard 2 Nut Item (2) Discard - Remove fastener from hole H13, LH side: 1 Screw Item (91) Discard 1 Nut Item (2) Discard - Remove fasteners from holes H21, H22, H23 and H24, LH side: 4 Screw Item (75) Discard 4 Nut Item (2) Discard - Remove fastener from hole H261, LH side: 1 Screw Item (73) Discard 1 Nut Item (9) Discard - Remove fastener from hole H262, LH side: 1 Screw Item (93) Discard 1 Nut Item (2) Discard - Remove fastener from hole H263, LH side: 1 Screw Item (61) Discard 1 Washer Item (62) Discard 1 Nut Item (63) Discard - Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 229 5

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# @A330 SERVICE BULLETIN

1 If no crack is found:
a Apply SUBTASK 573115-833-022 005 Install New same Fasteners of the Area B in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-010 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-023 005 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-024 005 Install New Fasteners of the Area B in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-010 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (10) Subtask 573115-832-011-005 - Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 230 5

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# @A330 SERVICE BULLETIN

References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the holes of the area B of the frame 40, RH side. - Remove fasteners from hole H12 and H14, RH side: 2 Screw Item (1) Discard 2 Nut Item (2) Discard - Remove fastener from hole H13, RH side: 1 Screw Item (91) Discard 1 Nut Item (2) Discard - Remove fasteners from holes H21, H22, H23 and H24, RH side: 4 Screw Item (75) Discard 4 Nut Item (2) Discard - Remove fastener from hole H261, RH side: 1 Screw Item (73) Discard 1 Nut Item (9) Discard - Remove fastener from hole H262, RH side: 1 Screw Item (93) Discard 1 Nut Item (2) Discard - Remove fastener from hole H263, RH side: 1 Screw Item (61) Discard

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 231 5

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# @A330 SERVICE BULLETIN
1 Washer Item (62) Discard 1 Nut Item (63) Discard - Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-013 005 Install New same Fasteners of the Area B in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-011 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-017 005 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-021 005 Install New Fasteners of the Area B in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-011 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 232 5

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# @A330 SERVICE BULLETIN
**CONF 006 (1) Subtask 573115-832-001-001 - Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Service Bulletin (SB) A330-57-3083 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) If Service Bulletin No. A330-57-3083 is accomplished: 1 Do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). (b) If Service Bulletin No. A330-57-3083 is not accomplished: 1 Do SUBTASK 573115-832-003 006 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 3 of the Planning Information Paragraph E.(2).
or Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 233 5

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# @A330 SERVICE BULLETIN (2) Subtask 573115-832-007-001 - Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Service Bulletin (SB) A330-57-3083 Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) If Service Bulletin No. A330-57-3083 is accomplished: 1 Do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). (b) If Service Bulletin No. A330-57-3083 is not accomplished: 1 Do SUBTASK 573115-832-009 006 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 3 of the Planning Information Paragraph E.(2).
or Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. (3) Subtask 573115-832-002-012 - Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 234 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC References Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) Do SUBTASK 573115-832-010 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the threshold given in the table 5 of the Planning Information Paragraph E.(2). (4) Subtask 573115-832-008-005 - Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Fig. A-FFAAA Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer toFig. A-FFAAA Sheet 01 toFig. A-FFAAA Sheet 03 (a) Do SUBTASK 573115-832-011 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the threshold given in the table 5 of the Planning Information Paragraph E.(2). (5) Subtask 573115-832-003-006 - Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 235 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A330-57-3083 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, LH side. - Remove the fastener from hole H260, LH side: 1 Screw Item (6) Discard 1 Nut Item (2) Discard - Do a rototest inspection at the hole H260, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-001 007 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-003 006 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2).
or
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 236 5

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# @A330 SERVICE BULLETIN
b Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. 2 If crack is found:
a Apply SUBTASK 573115-833-004 001 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-007 015 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-003 006 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (6) Subtask 573115-832-009-006 - Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 237 5

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# @A330 SERVICE BULLETIN

References Service Bulletin (SB) A330-57-3083 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection pre Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, RH side. - Remove the fastener from hole H260, RH side: 1 Screw Item (6) Discard 1 Nut Item (2) Discard - Do a rototest inspection at the hole H260, RH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-010 005 Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-009 006 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2).
or b Apply Service Bulletin No. A330-57-3083 before next flight and do SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 4 of the Planning Information Paragraph E.(2). NOTE: The threshold is to be counted from Service Bulletin No. A330-57-3083 embodiment. DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 238 5

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# @A330 SERVICE BULLETIN

2 If crack is found:
a Apply SUBTASK 573115-833-014 001 Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. <2> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-018 003 Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-009 006 Do a Rototest Inspection Pre Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 3 of the Planning Information Paragraph E.(2). (b) For the inspection report, refer to Appendix 01. (7) Subtask 573115-832-004-001 - Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 239 5

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# @A330 SERVICE BULLETIN
Refer toFig. A-FCDAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, LH side. - Remove fastener from hole H260, LH side: 1 Screw Item (77) Discard 1 Nut Item (78) Discard - Do a rototest inspection at the hole H260, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-002 015 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-005 001 Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-008 015 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-004 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2).
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 240 5

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# @A330 SERVICE BULLETIN <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (8) Subtask 573115-832-005-001 - Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection post Service Bulletin No. A330-57-3083 of the hole of the area A of the frame 40, RH side. - Remove fastener from hole H260, RH side: 1 Screw Item (77) Discard 1 Nut Item (78) Discard - Do a rototest inspection at the hole H260, RH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 241 5

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# @A330 SERVICE BULLETIN

1 If no crack is found:
a Apply SUBTASK 573115-833-011 003 Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-015 001 Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-019 003 Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-005 001 Do a Rototest Inspection Post Service Bulletin No. A330-57-3083 of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (9) Subtask 573115-832-010-005 - Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 242 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the holes of the area B of the frame 40, LH side. - Remove fasteners from hole H12 and H14, LH side: 2 Screw Item (1) Discard 2 Nut Item (2) Discard - Remove fastener from hole H13, LH side: 1 Screw Item (91) Discard 1 Nut Item (2) Discard - Remove fasteners from holes H21, H22, H23 and H24, LH side: 4 Screw Item (75) Discard 4 Nut Item (2) Discard - Remove fastener from hole H261, LH side: 1 Screw Item (73) Discard 1 Nut Item (9) Discard - Remove fastener from hole H262, LH side: 1 Screw Item (93) Discard
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 243 5

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# @A330 SERVICE BULLETIN
1 Nut Item (2) Discard - Remove fastener from hole H263, LH side: 1 Screw Item (61) Discard 1 Washer Item (62) Discard 1 Nut Item (63) Discard - Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-022 005 Install New same Fasteners of the Area B in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-010 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-023 005 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-024 005 Install New Fasteners of the Area B in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-010 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01.
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 244 5

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# @A330 SERVICE BULLETIN (10) Subtask 573115-832-011-005 - Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the holes of the area B of the frame 40, RH side. - Remove fasteners from hole H12 and H14, RH side: 2 Screw Item (1) Discard 2 Nut Item (2) Discard - Remove fastener from hole H13, RH side: 1 Screw Item (91) Discard 1 Nut Item (2) Discard - Remove fasteners from holes H21, H22, H23 and H24, RH side: 4 Screw Item (75) Discard 4 Nut Item (2) Discard - Remove fastener from hole H261, RH side: 1 Screw Item (73) Discard DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 245 5

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# @A330 SERVICE BULLETIN
1 Nut Item (9) Discard - Remove fastener from hole H262, RH side: 1 Screw Item (93) Discard 1 Nut Item (2) Discard - Remove fastener from hole H263, RH side: 1 Screw Item (61) Discard 1 Washer Item (62) Discard 1 Nut Item (63) Discard - Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-013 005 Install New same Fasteners of the Area B in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-011 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-017 005 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-021 005 Install New Fasteners of the Area B in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-011 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 246 5

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# @A330 SERVICE BULLETIN <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. **CONF 007 (1) Subtask 573115-832-001-008 - Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Service Bulletin (SB) A330-57-3083 Fig. A-FFAAB Flow Chart Sheet 01 Sheet 02 Refer toFig. A-FFAAB Sheet 01 and Fig. A-FFAAB Sheet 02 (a) Do SUBTASK 573115-832-006 001 Do a Rototest Inspection of the Hole of the Area A of the Frame 40, LH Side at the threshold given in the table 3 of the Planning Information Paragraph E.(2). (2) Subtask 573115-832-007-002 - Do a Special Detailed Inspection of the Fastener Hole of the Area A at FR 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Fig. A-FFAAB Flow Chart Sheet 01 Sheet 02 Refer toFig. A-FFAAB Sheet 01 and Fig. A-FFAAB Sheet 02 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 247 5

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# @A330 SERVICE BULLETIN (a) Do SUBTASK 573115-832-012 001 Do a Rototest Inspection of the Hole of the Area A of the Frame 40, RH Side at the threshold given in the table 3 of the Planning Information Paragraph E.(2). (3) Subtask 573115-832-002-013 - Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC References Fig. A-FFAAB Flow Chart Sheet 01 Sheet 02 Refer toFig. A-FFAAB Sheet 01 and Fig. A-FFAAB Sheet 02 (a) Do SUBTASK 573115-832-010 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the threshold given in the table 5 of the Planning Information Paragraph E.(2). (4) Subtask 573115-832-008-006 - Do a Special Detailed Inspection of the Fastener Holes of the Area B at FR 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC References Fig. A-FFAAB Flow Chart Sheet 01 Sheet 02 Refer toFig. A-FFAAB Sheet 01 and Fig. A-FFAAB Sheet 02 (a) Do SUBTASK 573115-832-011 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the threshold given in the table 5 of the Planning Information Paragraph E.(2).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 248 5

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# @A330 SERVICE BULLETIN (5) Subtask 573115-832-006-001 - Do a Rototest Inspection of the Hole of the Area A of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCEAA Removal/Installation of the Fastener of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCEAA Sheet 01 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the hole of the area A of the frame 40, LH side. - Remove fastener from hole H260, LH side: 1 Screw Item (77) Discard 1 Nut Item (78) Discard - Do a rototest inspection at the hole H260, LH side. Refer to Fig. A-FCBAA Sheet 01 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-003 001 Install New same Fastener of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-006 001 Do a Rototest Inspection of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 249 5

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# @A330 SERVICE BULLETIN
b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-006 001 Oversize the Hole of the Area A to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-009 001 Install New Fastener of the Area A in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-006 001 Do a Rototest Inspection of the Hole of the Area A of the Frame 40, LH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (6) Subtask 573115-832-012-001 - Do a Rototest Inspection of the Hole of the Area A of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCEAA Removal/Installation of the Fastener of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCEAA Sheet 01 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 250 5

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# @A330 SERVICE BULLETIN At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the hole of the area A of the frame 40, RH side. - Remove fastener from hole H260, RH side: 1 Screw Item (77) Discard 1 Nut Item (78) Discard - Do a rototest inspection at the hole H260, RH side. Refer to Fig. A-FCBAA Sheet 01 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-012 001 Install New same Fastener of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-012 001 Do a Rototest Inspection of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-016 001 Oversize the Hole of the Area A to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-020 001 Install New Fastener of the Area A in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-012 001 Do a Rototest Inspection of the Hole of the Area A of the Frame 40, RH Side at the interval given in the table 4 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 251 5

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# @A330 SERVICE BULLETIN (7) Subtask 573115-832-010-005 - Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the holes of the area B of the frame 40, LH side. - Remove fasteners from hole H12 and H14, LH side: 2 Screw Item (1) Discard 2 Nut Item (2) Discard - Remove fastener from hole H13, LH side: 1 Screw Item (91) Discard 1 Nut Item (2) Discard - Remove fasteners from holes H21, H22, H23 and H24, LH side: 4 Screw Item (75) Discard 4 Nut Item (2) Discard - Remove fastener from hole H261, LH side: 1 Screw Item (73) Discard DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 252 5

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# @A330 SERVICE BULLETIN
1 Nut Item (9) Discard - Remove fastener from hole H262, LH side: 1 Screw Item (93) Discard 1 Nut Item (2) Discard - Remove fastener from hole H263, LH side: 1 Screw Item (61) Discard 1 Washer Item (62) Discard 1 Nut Item (63) Discard - Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-022 005 Install New same Fasteners of the Area B in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-010 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-023 005 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-024 005 Install New Fasteners of the Area B in transition fit, LH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-010 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, LH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 253 5

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# @A330 SERVICE BULLETIN <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. (8) Subtask 573115-832-011-005 - Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 5.00 Minimum number of person 1 Subtask elapsed time 5.00 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Fig. A-FCBAA Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 At the threshold given in the Planning Information Paragraph E.(2): (a) Do a rototest inspection of the holes of the area B of the frame 40, RH side. - Remove fasteners from hole H12 and H14, RH side: 2 Screw Item (1) Discard 2 Nut Item (2) Discard - Remove fastener from hole H13, RH side: 1 Screw Item (91) Discard 1 Nut Item (2) Discard - Remove fasteners from holes H21, H22, H23 and H24, RH side: 4 Screw Item (75) Discard DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 254 5

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# @A330 SERVICE BULLETIN
4 Nut Item (2) Discard - Remove fastener from hole H261, RH side: 1 Screw Item (73) Discard 1 Nut Item (9) Discard - Remove fastener from hole H262, RH side: 1 Screw Item (93) Discard 1 Nut Item (2) Discard - Remove fastener from hole H263, RH side: 1 Screw Item (61) Discard 1 Washer Item (62) Discard 1 Nut Item (63) Discard - Do a rototest inspection of holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263, LH side. Refer to Fig. A-FCBAA Sheet 01 and Fig. A-FCBAA Sheet 02 Refer to NTM 51-10-01 1 If no crack is found:
a Apply SUBTASK 573115-833-013 005 Install New same Fasteners of the Area B in transition fit, RH Side before next flight and Repeat the rototest inspection as described in SUBTASK 573115-832-011 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). b For the inspection report, refer to Appendix 01. 2 If crack is found:
a Apply SUBTASK 573115-833-017 005 Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side and check if crack is found with a rototest inspection before next flight. <1> If no crack is found after the rototest inspection: <a> Apply SUBTASK 573115-833-021 005 Install New Fasteners of the Area B in transition fit, RH Side before next flight and DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 255 5

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# @A330 SERVICE BULLETIN Repeat the rototest inspection as described in SUBTASK 573115-832-011 005 Do a Rototest Inspection of the Holes of the Area B of the Frame 40, RH Side at the interval given in the table 5 of the Planning Information Paragraph E.(2). <2> If crack is found after the rototest inspection: <a> Contact Airbus before next flight. (b) For the inspection report, refer to Appendix 01. **CONF ALL D. TEST **CONF 001 (1) Subtask 573115-700-001-002 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access SUBTASK 573115-010-001 001 Remove/Open for Access in the FWD Cargo-Compartment and SUBTASK 573115-010-002 001 Remove/Open for Access in the Belly Fairing Area . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802). 2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 256 5

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# @A330 SERVICE BULLETIN

5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). **CONF 002 (1) Subtask 573115-700-001-001 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access SUBTASK 573115-010-001 001 Remove/Open for Access in the FWD Cargo-Compartment and SUBTASK 573115-010-002 001 Remove/Open for Access in the Belly Fairing Area . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802). 2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 257 5

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# @A330 SERVICE BULLETIN

5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). **CONF 003 (1) Subtask 573115-700-001-003 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access SUBTASK 573115-010-001 001 Remove/Open for Access in the FWD Cargo-Compartment and SUBTASK 573115-010-002 001 Remove/Open for Access in the Belly Fairing Area . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802). 2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 258 5

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# @A330 SERVICE BULLETIN

5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). **CONF 004 (1) Subtask 573115-700-001-004 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access SUBTASK 573115-010-001 001 Remove/Open for Access in the FWD Cargo-Compartment and SUBTASK 573115-010-002 001 Remove/Open for Access in the Belly Fairing Area . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802). 2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 259 5

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# @A330 SERVICE BULLETIN

5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). **CONF 005 (1) Subtask 573115-700-001-006 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access SUBTASK 573115-010-001 001 Remove/Open for Access in the FWD Cargo-Compartment and SUBTASK 573115-010-002 001 Remove/Open for Access in the Belly Fairing Area . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802). 2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 260 5

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# @A330 SERVICE BULLETIN

5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). **CONF 006 (1) Subtask 573115-700-001-007 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access SUBTASK 573115-010-001 001 Remove/Open for Access in the FWD Cargo-Compartment and SUBTASK 573115-010-002 001 Remove/Open for Access in the Belly Fairing Area . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802). 2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 261 5

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# @A330 SERVICE BULLETIN

5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). **CONF 007 (1) Subtask 573115-700-001-008 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access SUBTASK 573115-010-001 001 Remove/Open for Access in the FWD Cargo-Compartment and SUBTASK 573115-010-002 001 Remove/Open for Access in the Belly Fairing Area . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802). 2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 262 5

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# @A330 SERVICE BULLETIN

5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). **CONF ALL E. CLOSE-UP NOTE: This paragraph is only applicable if no crack found after the inspection of the holes. **CONF 001 (1) Subtask 573115-410-001-002 - Install/Close Items Removed/Opened for access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 27-84-41-400-802 Task 53-35-13-400-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 263 5

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# @A330 SERVICE BULLETIN
CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 002 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) On the RH side, install the retained universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-400-802). (c) On the RH side, install the air ventilation duct (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBCAA Sheet 01). 1 Install: 1 Duct Item (41) Retained at removal (d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-400-802). (2) Subtask 573115-410-002-002 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 25-80-00-400-801 Task 52-30-00-410-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 264 5

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# @A330 SERVICE BULLETIN
WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 002 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801). (c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retained at removal (d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801). (e) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (3) Subtask 573115-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 265 5

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# @A330 SERVICE BULLETIN
**CONF 002 (1) Subtask 573115-410-001-001 - Install/Close Items Removed/Opened for access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 27-84-41-400-802 Task 53-35-13-400-802 Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 001 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) On the RH side, install the retained universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-400-802). (c) On the RH side, install the air ventilation duct (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBCAA Sheet 01). 1 Install: 1 Duct Item (41) Retained at removal

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 266 5

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# @A330 SERVICE BULLETIN (d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-400-802). (2) Subtask 573115-410-002-001 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 25-80-00-400-801 Task 52-30-00-410-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 001 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 267 5

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# @A330 SERVICE BULLETIN (c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retained at removal (d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801). (e) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (3) Subtask 573115-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition. **CONF 003 (1) Subtask 573115-410-001-003 - Install/Close Items Removed/Opened for access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 27-84-41-400-802 Task 53-35-13-400-802
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 268 5

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# @A330 SERVICE BULLETIN

References Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 003 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) On the RH side, install the retained universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-400-802). (c) On the RH side, install the air ventilation duct (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBCAA Sheet 01). 1 Install: 1 Duct Item (41) Retained at removal (d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-400-802). (2) Subtask 573115-410-002-003 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 269 5

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# @A330 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 25-80-00-400-801 Task 52-30-00-410-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: This paragraph is apply only if no crack found after result the holes inspection. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 003 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801). (c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retained at removal (d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801).
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 270 5

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# @A330 SERVICE BULLETIN (e) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (3) Subtask 573115-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition. **CONF 004 (1) Subtask 573115-410-001-004 - Install/Close Items Removed/Opened for access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 27-84-41-400-802 Task 53-35-13-400-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 004 Testing .

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 271 5

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# @A330 SERVICE BULLETIN (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) On the RH side, install the retained universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-400-802). (c) On the RH side, install the air ventilation duct (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBCAA Sheet 01). 1 Install: 1 Duct Item (41) Retained at removal (d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-400-802). (2) Subtask 573115-410-002-004 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 25-80-00-400-801 Task 52-30-00-410-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE.
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 272 5

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# @A330 SERVICE BULLETIN
NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 004 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801). (c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retained at removal (d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801). (e) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (3) Subtask 573115-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition. **CONF 005 (1) Subtask 573115-410-001-006 - Install/Close Items Removed/Opened for access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 273 5

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# @A330 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 27-84-41-400-802 Task 53-35-13-400-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 006 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) On the RH side, install the retained universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-400-802). (c) On the RH side, install the air ventilation duct (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBCAA Sheet 01). 1 Install: 1 Duct Item (41) Retained at removal (d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 274 5

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# @A330 SERVICE BULLETIN (2) Subtask 573115-410-002-006 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 25-80-00-400-801 Task 52-30-00-410-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 006 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801). (c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retained at removal DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 275 5

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# @A330 SERVICE BULLETIN (d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801). (e) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (3) Subtask 573115-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition. **CONF 006 (1) Subtask 573115-410-001-007 - Install/Close Items Removed/Opened for access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 27-84-41-400-802 Task 53-35-13-400-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 276 5

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# @A330 SERVICE BULLETIN SUBTASK 573115-700-001 007 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) On the RH side, install the retained universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-400-802). (c) On the RH side, install the air ventilation duct (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBCAA Sheet 01). 1 Install: 1 Duct Item (41) Retained at removal (d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-400-802). (2) Subtask 573115-410-002-007 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 28-80-00-400-801 Task 52-30-00-410-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 277 5

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# @A330 SERVICE BULLETIN
CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 007 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the insulation back in position (Refer to AMM Task 28-80-00-400-801). (c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retained at removal (d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801). (e) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (3) Subtask 573115-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition. **CONF 007 (1) Subtask 573115-410-001-008 - Install/Close Items Removed/Opened for access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 278 5

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# @A330 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 27-84-41-400-802 Task 53-35-13-400-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 008 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) On the RH side, install the retained universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-400-802). (c) On the RH side, install the air ventilation duct (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBCAA Sheet 01). 1 Install: 1 Duct Item (41) Retained at removal (d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 279 5

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# @A330 SERVICE BULLETIN (2) Subtask 573115-410-002-008 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 25-80-00-400-801 Task 52-30-00-410-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 008 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the insulation back in position (Refer to AMM Task 25-80-00-400-801). (c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retained at removal DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 280 5

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# @A330 SERVICE BULLETIN (d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801). (e) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (3) Subtask 573115-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 281 5

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# @A330 SERVICE BULLETIN

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DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 282 5

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# @A330 SERVICE BULLETIN Task 573115-833-801-001 - Repair **CONF ALL WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR : - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR. 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. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. Task Associated Data **CONF 001 Zone 130 137 138 192 Manpower TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 283 5

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# @A330 SERVICE BULLETIN
**CONF 002 Zone 130 137 138 192 Manpower TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 **CONF 003 Zone 130 137 138 192 Manpower TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 **CONF 004 Zone 130 137 138 192 Manpower TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 **CONF 005 Zone 130 137 138 192 Manpower TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 **CONF 006 Zone 130 137 138 192 Manpower TOTAL MANHOURS 44.00 ELAPSED TIME (HOURS) 44.00 **CONF 007 Zone 130 137 138 192 Manpower TOTAL MANHOURS 42.50 ELAPSED TIME (HOURS) 42.50
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 284 5

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# @A330 SERVICE BULLETIN
**CONF ALL A. GENERAL **CONF 001 (1) Subtask 573115-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-801 Consumable Material List (CML) Structural Repair Manual (SRM) 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-11 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001. (c) For the specification of the material numbers (Mat. No.), refer to the Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant and clean the surfaces. (e) Remove and install the fasteners in accordance with SRM 51-42-00. (f) Torque the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (g) Apply the sealant In accordance with SRM 51-24-00. (h) Drill and deburr the holes in accordance with SRM 51-44-11. (i) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00. (j) 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. (k) For alternative and substitute fasteners (Refer to SRM 51-43-00).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 285 5

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

# @A330 SERVICE BULLETIN
**CONF 002 (1) Subtask 573115-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-801 Consumable Material List (CML) Structural Repair Manual (SRM) 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-11 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001. (c) For the specification of the material numbers (Mat. No.), refer to the Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant and clean the surfaces. (e) Remove and install the fasteners in accordance with SRM 51-42-00. (f) Torque the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (g) Apply the sealant In accordance with SRM 51-24-00. (h) Drill and deburr the holes in accordance with SRM 51-44-11. (i) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00. (j) 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. (k) For alternative and substitute fasteners (Refer to SRM 51-43-00). **CONF 003 (1) Subtask 573115-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 286 5

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

# @A330 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-801 Consumable Material List (CML) Structural Repair Manual (SRM) 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-11 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001. (c) For the specification of the material numbers (Mat. No.), refer to the Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant and clean the surfaces. (e) Remove and install the fasteners in accordance with SRM 51-42-00. (f) Torque the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (g) Apply the sealant In accordance with SRM 51-24-00. (h) Drill and deburr the holes in accordance with SRM 51-44-11. (i) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00. (j) 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. (k) For alternative and substitute fasteners (Refer to SRM 51-43-00). **CONF 004 (1) Subtask 573115-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-801 Consumable Material List (CML) DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 287 5

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

# @A330 SERVICE BULLETIN

References Structural Repair Manual (SRM) 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-11 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001. (c) For the specification of the material numbers (Mat. No.), refer to the Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant and clean the surfaces. (e) Remove and install the fasteners in accordance with SRM 51-42-00. (f) Torque the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (g) Apply the sealant In accordance with SRM 51-24-00. (h) Drill and deburr the holes in accordance with SRM 51-44-11. (i) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00. (j) 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. (k) For alternative and substitute fasteners (Refer to SRM 51-43-00). **CONF 005 (1) Subtask 573115-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-801 Consumable Material List (CML)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 288 5

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

# @A330 SERVICE BULLETIN

References Structural Repair Manual (SRM) 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-11 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001. (c) For the specification of the material numbers (Mat. No.), refer to the Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant and clean the surfaces. (e) Remove and install the fasteners in accordance with SRM 51-42-00. (f) Torque the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (g) Apply the sealant In accordance with SRM 51-24-00. (h) Drill and deburr the holes in accordance with SRM 51-44-11. (i) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00. (j) 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. (k) For alternative and substitute fasteners (Refer to SRM 51-43-00). **CONF 006 (1) Subtask 573115-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-801 Consumable Material List (CML)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 289 5

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

# @A330 SERVICE BULLETIN

References Structural Repair Manual (SRM) 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-11 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001. (c) For the specification of the material numbers (Mat. No.), refer to the Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant and clean the surfaces. (e) Remove and install the fasteners in accordance with SRM 51-42-00. (f) Torque the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (g) Apply the sealant In accordance with SRM 51-24-00. (h) Drill and deburr the holes in accordance with SRM 51-44-11. (i) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00. (j) 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. (k) For alternative and substitute fasteners (Refer to SRM 51-43-00). **CONF 007 (1) Subtask 573115-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-801 Consumable Material List (CML)

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 290 5

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

# @A330 SERVICE BULLETIN

References Structural Repair Manual (SRM) 51-23-11 51-24-00 51-40-00 51-42-00 51-43-00 51-44-11 (a) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (b) For the identification of Access Panels, refer to AMM 06-41-53, Page Block 001. (c) For the specification of the material numbers (Mat. No.), refer to the Consumable Material List (CML). (d) Use a non-metallic spatula to remove the sealant and clean the surfaces. (e) Remove and install the fasteners in accordance with SRM 51-42-00. (f) Torque the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (g) Apply the sealant In accordance with SRM 51-24-00. (h) Drill and deburr the holes in accordance with SRM 51-44-11. (i) In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00. (j) 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. (k) For alternative and substitute fasteners (Refer to SRM 51-43-00). **CONF ALL B. PREPARATION NOTE: This PREPARATION procedure is already done in the INSPECTION task. **CONF 001 (1) Subtask 573115-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 291 5

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

# @A330 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position at doors 821 and 822. (2) Subtask 573115-861-002-001 - Energize Electrical Network Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801 (a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801). (3) Subtask 573115-865-003-001 - C/B Opening/Closing Manpower Resources Skills NON SPECIFIC (a) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 721 PACK 1 L1 115VAC 1HH1 02 F 721 PACK 1 L2 115VAC 3HH1 04 K 721 PACK 1 L2 28VDC 4HH1 07 R 721 PACK 1 L1 28VDC 2HH1 08 T 722 PACK 2 L2 115VAC 3HH2 44 E 722 PACK 2 L1 115VAC 1HH2 48 H 722 PACK 2 L2 28VDC 4HH2 41 U 722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-004-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU : 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbutton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 292 5

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

# @A330 SERVICE BULLETIN(5) Subtask 573115-010-003-001 - Remove/Open for Access in the FWD CargoCompartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801). (c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain
2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573115-010-004-001 - Remove/Open for Access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 293 5

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

# @A330 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 27-84-41-000-802 Task 53-35-13-000-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. (a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-000-802). (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) On the RH side, remove and retain the universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802). **CONF 002 (1) Subtask 573115-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 294 5

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

# @A330 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position at doors 821 and 822. (2) Subtask 573115-861-002-001 - Energize Electrical Network Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801 (a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801). (3) Subtask 573115-865-003-001 - C/B Opening/Closing Manpower Resources Skills NON SPECIFIC (a) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 721 PACK 1 L1 115VAC 1HH1 02 F 721 PACK 1 L2 115VAC 3HH1 04 K 721 PACK 1 L2 28VDC 4HH1 07 R 721 PACK 1 L1 28VDC 2HH1 08 T 722 PACK 2 L2 115VAC 3HH2 44 E 722 PACK 2 L1 115VAC 1HH2 48 H 722 PACK 2 L2 28VDC 4HH2 41 U 722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-004-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU : 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbutton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 295 5

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

# @A330 SERVICE BULLETIN(5) Subtask 573115-010-003-001 - Remove/Open for Access in the FWD CargoCompartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801). (c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain
2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573115-010-004-001 - Remove/Open for Access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 296 5

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

# @A330 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 27-84-41-000-802 Task 53-35-13-000-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. (a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-000-802). (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) On the RH side, remove and retain the universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802). **CONF 003 (1) Subtask 573115-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 297 5

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

# @A330 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position at doors 821 and 822. (2) Subtask 573115-861-002-001 - Energize Electrical Network Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801 (a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801). (3) Subtask 573115-865-003-001 - C/B Opening/Closing Manpower Resources Skills NON SPECIFIC (a) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 721 PACK 1 L1 115VAC 1HH1 02 F 721 PACK 1 L2 115VAC 3HH1 04 K 721 PACK 1 L2 28VDC 4HH1 07 R 721 PACK 1 L1 28VDC 2HH1 08 T 722 PACK 2 L2 115VAC 3HH2 44 E 722 PACK 2 L1 115VAC 1HH2 48 H 722 PACK 2 L2 28VDC 4HH2 41 U 722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-004-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU : 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbutton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 298 5

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

# @A330 SERVICE BULLETIN(5) Subtask 573115-010-003-001 - Remove/Open for Access in the FWD CargoCompartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801). (c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain
2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573115-010-004-001 - Remove/Open for Access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 299 5

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

# @A330 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 27-84-41-000-802 Task 53-35-13-000-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. (a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-000-802). (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) On the RH side, remove and retain the universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802). **CONF 004 (1) Subtask 573115-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 300 5

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

# @A330 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position at doors 821 and 822. (2) Subtask 573115-861-002-001 - Energize Electrical Network Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801 (a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801). (3) Subtask 573115-865-003-001 - C/B Opening/Closing Manpower Resources Skills NON SPECIFIC (a) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 721 PACK 1 L1 115VAC 1HH1 02 F 721 PACK 1 L2 115VAC 3HH1 04 K 721 PACK 1 L2 28VDC 4HH1 07 R 721 PACK 1 L1 28VDC 2HH1 08 T 722 PACK 2 L2 115VAC 3HH2 44 E 722 PACK 2 L1 115VAC 1HH2 48 H 722 PACK 2 L2 28VDC 4HH2 41 U 722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-004-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU : 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbutton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 301 5

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

# @A330 SERVICE BULLETIN(5) Subtask 573115-010-003-001 - Remove/Open for Access in the FWD CargoCompartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801). (c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain
2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573115-010-004-001 - Remove/Open for Access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 302 5

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

# @A330 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 27-84-41-000-802 Task 53-35-13-000-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. (a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-000-802). (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) On the RH side, remove and retain the universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802). **CONF 005 (1) Subtask 573115-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 303 5

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

# @A330 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position at doors 821 and 822. (2) Subtask 573115-861-002-001 - Energize Electrical Network Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801 (a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801). (3) Subtask 573115-865-003-001 - C/B Opening/Closing Manpower Resources Skills NON SPECIFIC (a) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 721 PACK 1 L1 115VAC 1HH1 02 F 721 PACK 1 L2 115VAC 3HH1 04 K 721 PACK 1 L2 28VDC 4HH1 07 R 721 PACK 1 L1 28VDC 2HH1 08 T 722 PACK 2 L2 115VAC 3HH2 44 E 722 PACK 2 L1 115VAC 1HH2 48 H 722 PACK 2 L2 28VDC 4HH2 41 U 722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-004-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU : 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbutton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 304 5

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

# @A330 SERVICE BULLETIN(5) Subtask 573115-010-003-001 - Remove/Open for Access in the FWD CargoCompartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801). (c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain
2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573115-010-004-001 - Remove/Open for Access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 305 5

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

# @A330 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 27-84-41-000-802 Task 53-35-13-000-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. (a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-000-802). (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) On the RH side, remove and retain the universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802). **CONF 006 (1) Subtask 573115-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 306 5

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

# @A330 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position at doors 821 and 822. (2) Subtask 573115-861-002-001 - Energize Electrical Network Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801 (a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801). (3) Subtask 573115-865-003-001 - C/B Opening/Closing Manpower Resources Skills NON SPECIFIC (a) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 721 PACK 1 L1 115VAC 1HH1 02 F 721 PACK 1 L2 115VAC 3HH1 04 K 721 PACK 1 L2 28VDC 4HH1 07 R 721 PACK 1 L1 28VDC 2HH1 08 T 722 PACK 2 L2 115VAC 3HH2 44 E 722 PACK 2 L1 115VAC 1HH2 48 H 722 PACK 2 L2 28VDC 4HH2 41 U 722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-004-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU : 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbutton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 307 5

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

# @A330 SERVICE BULLETIN(5) Subtask 573115-010-003-001 - Remove/Open for Access in the FWD CargoCompartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801). (c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain
2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573115-010-004-001 - Remove/Open for Access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 308 5

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

# @A330 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 27-84-41-000-802 Task 53-35-13-000-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. (a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-000-802). (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) On the RH side, remove and retain the universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802). **CONF 007 (1) Subtask 573115-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 309 5

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

# @A330 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802). (b) Put the access platform(s) in position at doors 821 and 822. (2) Subtask 573115-861-002-001 - Energize Electrical Network Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-41-00-861-801 (a) Energize the aircraft electrical circuits (Refer to AMM Task 24-41-00-861-801). (3) Subtask 573115-865-003-001 - C/B Opening/Closing Manpower Resources Skills NON SPECIFIC (a) Open, safety and tag this (these) circuit breaker(s) : PANEL DESIGNATION FIN LOCATION SEE NOTES 721 PACK 1 L1 115VAC 1HH1 02 F 721 PACK 1 L2 115VAC 3HH1 04 K 721 PACK 1 L2 28VDC 4HH1 07 R 721 PACK 1 L1 28VDC 2HH1 08 T 722 PACK 2 L2 115VAC 3HH2 44 E 722 PACK 2 L1 115VAC 1HH2 48 H 722 PACK 2 L2 28VDC 4HH2 41 U 722 PACK 2 L1 28VDC 2HH2 40 U

(4) Subtask 573115-941-004-001 - Safety Precautions Manpower Resources Skills NON SPECIFIC (a) On the AIR control panel 225VU : 1 Make sure that the APU BLEED, the ENG BLEED 1(2) and the PACK 1(2) pushbutton switches are released. 2 Put a WARNING NOTICE in position to tell persons not to operate these pushbutton switches. (b) On the HP ground connectors, put a WARNING NOTICE in position to tell persons not to supply the ground air source.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 310 5

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

# @A330 SERVICE BULLETIN(5) Subtask 573115-010-003-001 - Remove/Open for Access in the FWD CargoCompartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 25-52-00-000-801 Task 25-80-00-000-801 Task 52-30-00-010-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. (a) Open the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-010-801). (b) Remove the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-000-801). (c) On the LH and RH sides, remove the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBAAA Sheet 01). 1 Remove: 2 Duct Item (11) Retain 2 Duct Item (12) Retain2 Recirculation filterhousing Item (13) Retain
2 Recirculation fan Item (14) Retain (d) Remove the insulation blankets if necessary (Refer to AMM Task 25-80-00-000-801). (6) Subtask 573115-010-004-001 - Remove/Open for Access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 311 5

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

# @A330 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-801 Task 27-84-41-000-802 Task 53-35-13-000-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. (a) Remove the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-000-802). (b) On the RH side, remove and retain the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBBAA Sheet 01). 1 Remove: 1 Duct Item (26) Retain (c) On the RH side, remove and retain the air ventilation duct as follows (Refer to AMM Task 21-20-00-010-801 and Fig. A-FBCAA Sheet 01). 1 Remove: 1 Duct Item (41) Retain (d) On the RH side, remove and retain the universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-000-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 312 5

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

# @A330 SERVICE BULLETIN
**CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 573115-833-001-004 - Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 1 SCREW 2 ASNA2531-6 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 313 5

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

# @A330 SERVICE BULLETIN (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V6-16 Item 1 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (2) Subtask 573115-833-010-002 - Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 1 SCREW 2 ASNA2531-6 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 314 5

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

# @A330 SERVICE BULLETIN
Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V6-16 Item 1 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (3) Subtask 573115-833-002-001 - Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 94 EN6115V7-16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 315 5

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

# @A330 SERVICE BULLETIN

References Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V7-16 Item 94 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (4) Subtask 573115-833-011-001 - Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 94 EN6115V7-16 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 316 5

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

# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V7-16 Item 94 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (5) Subtask 573115-833-022-002 - Install New same Fasteners of the Area B in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 317 5

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

# @A330 SERVICE BULLETIN
Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 2 SCREW 2 ASNA2531-6 7 NUT 4 EN6115V6-18 1 SCREW 6 EN6115V6-20 4 SCREW Kit 573115A02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2531-5 1 NUT 50 NSA5399-6-18A 1 SCREW 52 ASNA0094-6 2 NUT 58 ASNA2394EW6 2 WASHER 59 NSA5399-6-22A 1 SCREW 91 EN6115-5X18 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAB Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found, install the fasteners. 1 Install the fasteners at holes H12 and H14: 2 Screw EN6115V6-16 Item 1 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 318 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

2 Install the fastener at hole H13: 1 Screw EN6115V6-18 Item 4 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6-20 Item 6 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the fastener at hole H261: 1 Screw EN6115-5X18 Item 91 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the fastener at hole H262: 1 Screw NSA5399-6-22A Item 59 1 Washer ASNA2394EW6 Item 58 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the fastener at hole H263: 1 Screw NSA5399-6-18A Item 50 1 Washer ASNA2394EW6 Item 58 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 319 5

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# @A330 SERVICE BULLETIN

1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (6) Subtask 573115-833-013-002 - Install New same Fasteners of the Area B in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 2 SCREW 2 ASNA2531-6 7 NUT 4 EN6115V6-18 1 SCREW 6 EN6115V6-20 4 SCREW Kit 573115A02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2531-5 1 NUT 50 NSA5399-6-18A 1 SCREW 52 ASNA0094-6 2 NUT 58 ASNA2394EW6 2 WASHER 59 NSA5399-6-22A 1 SCREW 91 EN6115-5X18 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 320 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCAAB Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found, install the fasteners. 1 Install the fasteners at holes H12 and H14: 2 Screw EN6115V6-16 Item 1 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the fastener at hole H13: 1 Screw EN6115V6-18 Item 4 1 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6-20 Item 6 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the fastener at hole H261: 1 Screw EN6115-5X18 Item 91 1 Nut ASNA2531-5 Item 9 Wet install the fasteners with: DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 321 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

5 Install the fastener at hole H262: 1 Screw NSA5399-6-22A Item 59 1 Washer ASNA2394EW6 Item 58 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the fastener at hole H263: 1 Screw NSA5399-6-18A Item 50 1 Washer ASNA2394EW6 Item 58 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (7) Subtask 573115-833-004-001 - Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 322 5

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# @A330 SERVICE BULLETIN
Refer toFig. A-FCCAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCCAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (8) Subtask 573115-833-014-001 - Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCCAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 323 5

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# @A330 SERVICE BULLETIN (9) Subtask 573115-833-005-001 - Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCDAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (10) Subtask 573115-833-015-001 - Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 324 5

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# @A330 SERVICE BULLETIN

References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCDAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (11) Subtask 573115-833-023-002 - Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAB Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02 In accordance with SRM 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 325 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the areas B, if crack is found, oversize the holes.
a Drill to the first oversize diameter in comparison with the current hole diameter the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the dimension given in Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

. b Do a rototest inspection of the drilled holes to check if the crack is still present. Refer to NTM 51-10-01 (12) Subtask 573115-833-017-002 - Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAB Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02 In accordance with SRM 51-44-00 (a) Depending on inspection results of the areas B, if crack is found, oversize the holes.
a Drill to the first oversize diameter in comparison with the current hole diameter the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the dimension given in Fig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02

. b Do a rototest inspection of the drilled holes to check if the crack is still present. Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 326 5

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# @A330 SERVICE BULLETIN (13) Subtask 573115-833-007-001 - Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 1 NUT 3 EN6115V6X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V6X16 Item 3 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 327 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required (14) Subtask 573115-833-018-001 - Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 1 NUT 3 EN6115V6X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V6X16 Item 3 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 328 5

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# @A330 SERVICE BULLETIN

1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (15) Subtask 573115-833-008-001 - Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 79 EN6115V7X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 329 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V7X16 Item 79 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (16) Subtask 573115-833-019-001 - Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 79 EN6115V7X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 330 5

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# @A330 SERVICE BULLETIN
Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V7X16 Item 79 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (17) Subtask 573115-833-024-002 - Install New Fasteners of the Area B in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 7 NUT 3 EN6115V6X16 2 SCREW 5 EN6115V6X18 1 SCREW 7 EN6115V6X20 4 SCREW Kit 573115A02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2531-5 1 NUT 53 MS21250-07018 1 SCREW 57 EN6115-5Y18 1 SCREW 60 MS21250-07022 1 BOLT 82 ASNA2394EW7 2 WASHER 90 NSA5057-7 2 NUT

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 331 5

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# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAB Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found: 1 Install the first oversize fasteners at holes H12 and H14: 2 Screw EN6115V6X16 Item 3 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the first oversize fastener at hole H13: 1 Screw EN6115V6X18 Item 5 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6X20 Item 7 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 332 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

4 Install the second oversize fastener at hole H261: 1 Screw EN6115-5Y18 Item 57 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the next nominal fastener at hole H262: 1 Bolt MS21250-07022 Item 60 1 Washer ASNA2394EW7 Item 82 1 Nut NSA5057-7 Item 90 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the next nominal fastener at hole H263: 1 Screw MS21250-07018 Item 53 1 Washer ASNA2394EW7 Item 82 1 Nut NSA5057-7 Item 90 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (18) Subtask 573115-833-021-002 - Install New Fasteners of the Area B in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 333 5

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# @A330 SERVICE BULLETIN
Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 7 NUT 3 EN6115V6X16 2 SCREW 5 EN6115V6X18 1 SCREW 7 EN6115V6X20 4 SCREW Kit 573115A02R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2531-5 1 NUT 53 MS21250-07018 1 SCREW 57 EN6115-5Y18 1 SCREW 60 MS21250-07022 1 BOLT 82 ASNA2394EW7 2 WASHER 90 NSA5057-7 2 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAB Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAB Sheet 01 and Fig. A-FCAAB Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found: 1 Install the first oversize fasteners at holes H12 and H14: 2 Screw EN6115V6X16 Item 3 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 334 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

2 Install the first oversize fastener at hole H13: 1 Screw EN6115V6X18 Item 5 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6X20 Item 7 4 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

4 Install the second oversize fastener at hole H261: 1 Screw EN6115-5Y18 Item 57 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the next nominal fastener at hole H262: 1 Bolt MS21250-07022 Item 60 1 Washer ASNA2394EW7 Item 82 1 Nut NSA5057-7 Item 90 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the next nominal fastener at hole H263: 1 Screw MS21250-07018 Item 53 1 Washer ASNA2394EW7 Item 82 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 335 5

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# @A330 SERVICE BULLETIN

1 Nut NSA5057-7 Item 90 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required
**CONF 002 (1) Subtask 573115-833-001-001 - Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 1 SCREW 2 ASNA2531-6 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 336 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V6-16 Item 1 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (2) Subtask 573115-833-010-001 - Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 1 SCREW 2 ASNA2531-6 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 337 5

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# @A330 SERVICE BULLETIN
Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V6-16 Item 1 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (3) Subtask 573115-833-002-001 - Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 94 EN6115V7-16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 338 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V7-16 Item 94 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (4) Subtask 573115-833-011-001 - Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 94 EN6115V7-16 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 339 5

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# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V7-16 Item 94 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (5) Subtask 573115-833-022-001 - Install New same Fasteners of the Area B in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 340 5

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# @A330 SERVICE BULLETIN
Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 2 SCREW 2 ASNA2531-6 7 NUT 4 EN6115V6-18 1 SCREW 6 EN6115V6-20 4 SCREW Kit 573115A03R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115-5X19 1 SCREW 9 ASNA2531-5 1 NUT 50 NSA5399-6-18A 1 SCREW 51 NSA5372EW616B 2 WASHER 52 ASNA0094-6 2 NUT 54 NSA5399-6-16A 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAA Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found, install the fasteners. 1 Install the fasteners at holes H12 and H14: 2 Screw EN6115V6-16 Item 1 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 341 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

2 Install the fastener at hole H13: 1 Screw EN6115V6-18 Item 4 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6-20 Item 6 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the fastener at hole H261: 1 Screw EN6115-5X19 Item 8 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the fastener at hole H262: 1 Screw NSA5399-6-18A Item 50 1 Washer NSA5372EW616B Item 51 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the fastener at hole H263: 1 Screw NSA5399-6-16A Item 54 1 Washer NSA5372EW616B Item 51 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 342 5

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# @A330 SERVICE BULLETIN

1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (6) Subtask 573115-833-013-001 - Install New same Fasteners of the Area B in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 2 SCREW 2 ASNA2531-6 7 NUT 4 EN6115V6-18 1 SCREW 6 EN6115V6-20 1 SCREW Kit 573115A03R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115-5X19 1 SCREW 9 ASNA2531-5 1 NUT 50 NSA5399-6-18A 1 SCREW 51 NSA5372EW616B 2 WASHER 52 ASNA0094-6 2 NUT 54 NSA5399-6-16A 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 343 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCAAA Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found, install the fasteners. 1 Install the fasteners at holes H12 and H14: 2 Screw EN6115V6-16 Item 1 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the fastener at hole H13: 1 Screw EN6115V6-18 Item 4 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24: 1 Screw EN6115V6-20 Item 6 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the fastener at hole H261: 1 Screw EN6115-5X19 Item 8 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 344 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

5 Install the fastener at hole H262: 1 Screw NSA5399-6-18A Item 50 1 Washer NSA5372EW616B Item 51 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the fastener at hole H263: 1 Screw NSA5399-6-16A Item 54 1 Washer NSA5372EW616B Item 51 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (7) Subtask 573115-833-004-001 - Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 345 5

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# @A330 SERVICE BULLETIN
Refer toFig. A-FCCAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCCAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (8) Subtask 573115-833-014-001 - Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCCAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 346 5

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# @A330 SERVICE BULLETIN (9) Subtask 573115-833-005-001 - Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCDAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (10) Subtask 573115-833-015-001 - Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 347 5

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# @A330 SERVICE BULLETIN

References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCDAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (11) Subtask 573115-833-023-001 - Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAA Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 In accordance with SRM 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 348 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the areas B, if crack is found, oversize the holes.
a Drill to the first oversize diameter in comparison with the current hole diameter the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the dimension given in Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

. b Do a rototest inspection of the drilled holes to check if the crack is still present. Refer to NTM 51-10-01 (12) Subtask 573115-833-017-001 - Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAA Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 In accordance with SRM 51-44-00 (a) Depending on inspection results of the areas B, if crack is found, oversize the holes.
a Drill to the first oversize diameter in comparison with the current hole diameter the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the dimension given in Fig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02

. b Do a rototest inspection of the drilled holes to check if the crack is still present. Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 349 5

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# @A330 SERVICE BULLETIN (13) Subtask 573115-833-007-001 - Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 1 NUT 3 EN6115V6X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V6X16 Item 3 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 350 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required (14) Subtask 573115-833-018-001 - Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 1 NUT 3 EN6115V6X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V6X16 Item 3 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 351 5

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# @A330 SERVICE BULLETIN

1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (15) Subtask 573115-833-008-001 - Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 79 EN6115V7X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 352 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V7X16 Item 79 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (16) Subtask 573115-833-019-001 - Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 79 EN6115V7X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 353 5

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# @A330 SERVICE BULLETIN
Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V7X16 Item 79 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (17) Subtask 573115-833-024-001 - Install New Fasteners of the Area B in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 6 NUT 3 EN6115V6X16 2 SCREW 5 EN6115V6X18 1 SCREW 7 EN6115V6X20 4 SCREW Kit 573115A03R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2531-5 1 NUT 10 EN6115-5Y19 1 SCREW 53 MS21250-07018 1 SCREW 55 MS21250-07016 1 SCREW 80 NSA5372EW716B 2 WASHER 90 NSA5057-7 2 NUT

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 354 5

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# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAA Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found: 1 Install the first oversize fasteners at holes H12 and H14: 2 Screw EN6115V6X16 Item 3 1 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the first oversize fastener at hole H13: 1 Screw EN6115V6X18 Item 5 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6X20 Item 7 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 355 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

4 Install the second oversize fastener at hole H261: 1 Screw EN6115-5Y19 Item 10 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the next nominal fastener at hole H262: 1 Screw MS21250-07018 Item 53 1 Washer NSA5372EW716B Item 80 1 Nut NSA5057-7 Item 90 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the next nominal fastener at hole H263: 1 Screw MS21250-07016 Item 55 1 Washer NSA5372EW716B Item 80 1 Nut NSA5057-7 Item 90 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (18) Subtask 573115-833-021-001 - Install New Fasteners of the Area B in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 356 5

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# @A330 SERVICE BULLETIN
Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 6 NUT 3 EN6115V6X16 1 SCREW 5 EN6115V6X18 1 SCREW 7 EN6115V6X20 4 SCREW Kit 573115A03R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2531-5 1 NUT 10 EN6115-5Y19 1 SCREW 53 MS21250-07018 1 SCREW 55 MS21250-07016 1 SCREW 80 NSA5372EW716B 2 WASHER 90 NSA5057-7 2 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAA Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAA Sheet 01 and Fig. A-FCAAA Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found: 1 Install the first oversize fasteners at holes H12 and H14: 1 Screw EN6115V6X16 Item 3 1 Nut ASNA2531-6 Item 2 Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 357 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

2 Install the first oversize fastener at hole H13: 1 Screw EN6115V6X18 Item 5 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6X20 Item 7 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the second oversize fastener at hole H261: 1 Screw EN6115-5Y19 Item 10 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the next nominal fastener at hole H262: 1 Screw MS21250-07018 Item 53 1 Washer NSA5372EW716B Item 80 1 Nut NSA5057-7 Item 90 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the next nominal fastener at hole H263: 1 Screw MS21250-07016 Item 55 1 Washer NSA5372EW716B Item 80 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 358 5

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# @A330 SERVICE BULLETIN

1 Nut NSA5057-7 Item 90 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required
**CONF 003 (1) Subtask 573115-833-001-005 - Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 1 SCREW 2 ASNA2531-6 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 359 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V6-16 Item 1 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (2) Subtask 573115-833-010-003 - Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 1 SCREW 2 ASNA2531-6 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 360 5

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# @A330 SERVICE BULLETIN
Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V6-16 Item 1 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (3) Subtask 573115-833-002-001 - Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 94 EN6115V7-16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 361 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V7-16 Item 94 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (4) Subtask 573115-833-011-001 - Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 94 EN6115V7-16 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 362 5

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# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V7-16 Item 94 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (5) Subtask 573115-833-022-003 - Install New same Fasteners of the Area B in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 363 5

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# @A330 SERVICE BULLETIN
Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 2 SCREW 2 ASNA2531-6 7 NUT 4 EN6115V6-18 1 SCREW 6 EN6115V6-20 4 SCREW Kit 573115A04R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2531-5 1 NUT 61 MS21250-06018 1 SCREW 62 MS20002C6 2 WASHER 63 NSA5057-6 2 NUT 64 MS21250-06016 1 SCREW 88 EN6115-5-19 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAC Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found, install the fasteners. 1 Install the fasteners at holes H12 and H14: 2 Screw EN6115V6-16 Item 1 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 364 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

2 Install the fastener at hole H13: 1 Screw EN6115V6-18 Item 4 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6-20 Item 6 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the fastener at hole H261: 1 Screw EN6115-5-19 Item 88 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the fastener at hole H262: 1 Screw MS21250-06016 Item 64 1 Washer MS20002C6 Item 62 1 Nut NSA5057-6 Item 63 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the fastener at hole H263: 1 Screw MS21250-06018 Item 61 1 Washer MS20002C6 Item 62 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 365 5

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# @A330 SERVICE BULLETIN

1 Nut NSA5057-6 Item 63 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (6) Subtask 573115-833-013-003 - Install New same Fasteners of the Area B in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 2 SCREW 2 ASNA2531-6 7 NUT 4 EN6115V6-18 1 SCREW 6 EN6115V6-20 4 SCREW Kit 573115A04R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 ASNA2531-5 1 NUT 61 MS21250-06018 1 SCREW 62 MS20002C6 2 WASHER 63 NSA5057-6 2 NUT 64 MS21250-06016 1 SCREW 88 EN6115-5-19 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 366 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCAAC Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found, install the fasteners. 1 Install the fasteners at holes H12 and H14: 2 Screw EN6115V6-16 Item 1 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the fastener at hole H13: 1 Screw EN6115V6-18 Item 4 1 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6-20 Item 6 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the fastener at hole H261: 1 Screw EN6115-5-19 Item 88 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 367 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

5 Install the fastener at hole H262: 1 Screw MS21250-06016 Item 64 1 Washer MS20002C6 Item 62 1 Nut NSA5057-6 Item 63 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the fastener at hole H263: 1 Screw MS21250-06018 Item 61 1 Washer MS20002C6 Item 62 1 Nut NSA5057-6 Item 63 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (7) Subtask 573115-833-004-001 - Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 368 5

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# @A330 SERVICE BULLETIN
Refer toFig. A-FCCAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCCAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (8) Subtask 573115-833-014-001 - Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCCAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 369 5

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# @A330 SERVICE BULLETIN (9) Subtask 573115-833-005-001 - Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCDAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (10) Subtask 573115-833-015-001 - Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 370 5

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# @A330 SERVICE BULLETIN

References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCDAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (11) Subtask 573115-833-023-003 - Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAC Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02 In accordance with SRM 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 371 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the areas B, if crack is found, oversize the holes.
a Drill to the first oversize diameter in comparison with the current hole diameter the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the dimension given in Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

. b Do a rototest inspection of the drilled holes to check if the crack is still present. Refer to NTM 51-10-01 (12) Subtask 573115-833-017-003 - Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAC Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02 In accordance with SRM 51-44-00 (a) Depending on inspection results of the areas B, if crack is found, oversize the holes.
a Drill to the first oversize diameter in comparison with the current hole diameter the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the dimension given in Fig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02

. b Do a rototest inspection of the drilled holes to check if the crack is still present. Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 372 5

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# @A330 SERVICE BULLETIN (13) Subtask 573115-833-007-001 - Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 1 NUT 3 EN6115V6X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V6X16 Item 3 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 373 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required (14) Subtask 573115-833-018-001 - Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 1 NUT 3 EN6115V6X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V6X16 Item 3 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 374 5

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# @A330 SERVICE BULLETIN

1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (15) Subtask 573115-833-008-001 - Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 79 EN6115V7X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 375 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V7X16 Item 79 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (16) Subtask 573115-833-019-001 - Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 79 EN6115V7X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 376 5

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# @A330 SERVICE BULLETIN
Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V7X16 Item 79 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (17) Subtask 573115-833-024-003 - Install New Fasteners of the Area B in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 7 NUT 3 EN6115V6X16 2 SCREW 5 EN6115V6X18 1 SCREW 7 EN6115V6X20 4 SCREW Kit 573115A04R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115-5X19 1 SCREW 9 ASNA2531-5 1 NUT 52 ASNA0094-6 2 NUT 62 MS20002C6 2 WASHER 65 NSA5398-6-18A 1 SCREW 66 NSA5398-6-16A 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 377 5

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# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAC Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found: 1 Install the first oversize fasteners at holes H12 and H14: 2 Screw EN6115V6X16 Item 3 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the first oversize fastener at hole H13: 1 Screw EN6115V6X18 Item 5 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6X20 Item 7 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 378 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

4 Install the first oversize fastener at hole H261: 1 Screw EN6115-5X19 Item 8 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the first oversize fastener at hole H262: 1 Screw NSA5398-6-16A Item 66 1 Washer MS20002C6 Item 62 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the first oversize fastener at hole H263: 1 Screw NSA5398-6-18A Item 65 1 Washer MS20002C6 Item 62 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (18) Subtask 573115-833-021-003 - Install New Fasteners of the Area B in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 379 5

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# @A330 SERVICE BULLETIN
Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 7 NUT 3 EN6115V6X16 2 SCREW 5 EN6115V6X18 1 SCREW 7 EN6115V6X20 4 SCREW Kit 573115A04R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 8 EN6115-5X19 1 SCREW 9 ASNA2531-5 1 NUT 62 MS20002C6 2 WASHER 65 NSA5398-6-18A 1 SCREW 66 NSA5398-6-16A 1 SCREW Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 ASNA0094-6 2 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAC Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAC Sheet 01 and Fig. A-FCAAC Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found: 1 Install the first oversize fasteners at holes H12 and H14: 2 Screw EN6115V6X16 Item 3
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 380 5

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# @A330 SERVICE BULLETIN

2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the first oversize fastener at hole H13: 1 Screw EN6115V6X18 Item 5 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6X20 Item 7 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the first oversize fastener at hole H261: 1 Screw EN6115-5X19 Item 8 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the first oversize fastener at hole H262: 1 Screw NSA5398-6-16A Item 66 1 Washer MS20002C6 Item 62 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 381 5

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# @A330 SERVICE BULLETIN

6 Install the first oversize fastener at hole H263: 1 Screw NSA5398-6-18A Item 65 1 Washer MS20002C6 Item 62 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required
**CONF 004 (1) Subtask 573115-833-001-008 - Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 1 SCREW 2 ASNA2531-6 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 382 5

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# @A330 SERVICE BULLETIN
Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V6-16 Item 1 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (2) Subtask 573115-833-010-004 - Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 1 SCREW 2 ASNA2531-6 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 383 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V6-16 Item 1 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (3) Subtask 573115-833-002-001 - Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 94 EN6115V7-16 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 384 5

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# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V7-16 Item 94 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (4) Subtask 573115-833-011-001 - Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 385 5

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# @A330 SERVICE BULLETIN
Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 94 EN6115V7-16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V7-16 Item 94 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (5) Subtask 573115-833-022-004 - Install New same Fasteners of the Area B in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 386 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 2 SCREW 2 ASNA2531-6 7 NUT 4 EN6115V6-18 1 SCREW 6 EN6115V6-20 1 SCREW Kit 573115A05R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 51 NSA5372EW616B 2 WASHER 52 ASNA0094-6 2 NUT 58 ASNA2394EW6 2 WASHER 67 NSA5368PD516B 1 WASHER 83 NSA5050-5 1 NUT 84 NSA5399-6-23A 1 SCREW 86 NSA5399-6-25A 1 SCREW 91 EN6115-5X18 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAD Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Sheet 03
Refer toFig. A-FCAAD Sheet 01 and Fig. A-FCAAD Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 387 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the area B, if no crack is found, install the fasteners. 1 Install the fasteners at holes H12 and H14: 2 Screw EN6115V6-16 Item 1 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the fastener at hole H13: 1 Screw EN6115V6-18 Item 4 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24: 1 Screw EN6115V6-20 Item 6 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the fastener at hole H261: 1 Screw EN6115-5X18 Item 91 1 Washer NSA5368PD516B Item 67 1 Nut NSA5050-5 Item 83 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the fastener at hole H262: 1 Screw NSA5399-6-23A Item 84 1 Washer ASNA2394EW6 Item 58 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 388 5

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# @A330 SERVICE BULLETIN

1 Washer NSA5372EW616B Item 51 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the fastener at hole H263: 1 Screw NSA5399-6-25A Item 86 1 Washer ASNA2394EW6 Item 58 1 Washer NSA5372EW616B Item 51 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (6) Subtask 573115-833-013-004 - Install New same Fasteners of the Area B in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 2 SCREW 2 ASNA2531-6 7 NUT 4 EN6115V6-18 1 SCREW 6 EN6115V6-20 1 SCREW Kit 573115A05R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 51 NSA5372EW616B 2 WASHER DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 389 5

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# @A330 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 ASNA0094-6 2 NUT 58 ASNA2394EW6 2 WASHER 67 NSA5368PD516B 1 WASHER 83 NSA5050-5 1 NUT 84 NSA5399-6-23A 1 SCREW 86 NSA5399-6-25A 1 SCREW 91 EN6115-5X18 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAD Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Sheet 03
Refer toFig. A-FCAAD Sheet 01 and Fig. A-FCAAD Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found, install the fasteners. 1 Install the fasteners at holes H12 and H14: 2 Screw EN6115V6-16 Item 1 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the fastener at hole H13: 1 Screw EN6115V6-18 Item 4 1 Nut ASNA2531-6 Item 2 Wet install the fastener with:
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 390 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24: 1 Screw EN6115V6-20 Item 6 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the fastener at hole H261: 1 Screw EN6115-5X18 Item 91 1 Washer NSA5368PD516B Item 67 1 Nut NSA5050-5 Item 83 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the fastener at hole H262: 1 Screw NSA5399-6-23A Item 84 1 Washer ASNA2394EW6 Item 58 1 Washer NSA5372EW616B Item 51 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the fastener at hole H263: 1 Screw NSA5399-6-25A Item 86 1 Washer ASNA2394EW6 Item 58 1 Washer NSA5372EW616B Item 51 1 Nut ASNA0094-6 Item 52 Wet install the fastener with:
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 391 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required (7) Subtask 573115-833-004-001 - Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCCAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (8) Subtask 573115-833-014-001 - Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 392 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCCAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (9) Subtask 573115-833-005-001 - Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 393 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCDAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (10) Subtask 573115-833-015-001 - Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCDAA Sheet 01

. DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 394 5

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# @A330 SERVICE BULLETIN
b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (11) Subtask 573115-833-023-004 - Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAD Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Sheet 03
Refer toFig. A-FCAAD Sheet 01 toFig. A-FCAAD Sheet 03 In accordance with SRM 51-44-00 (a) Depending on inspection results of the areas B, if crack is found, oversize the holes.
a Drill to the first oversize diameter in comparison with the current hole diameter the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the dimension given in Fig. A-FCAAD Sheet 01 toFig. A-FCAAD Sheet 03

. b Do a rototest inspection of the drilled holes to check if the crack is still present. Refer to NTM 51-10-01 (12) Subtask 573115-833-017-004 - Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 395 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAD Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Sheet 03
Refer toFig. A-FCAAD Sheet 01 toFig. A-FCAAD Sheet 03 In accordance with SRM 51-44-00 (a) Depending on inspection results of the areas B, if crack is found, oversize the holes.
a Drill to the first oversize diameter in comparison with the current hole diameter the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the dimension given in Fig. A-FCAAD Sheet 01 toFig. A-FCAAD Sheet 03

. b Do a rototest inspection of the drilled holes to check if the crack is still present. Refer to NTM 51-10-01 (13) Subtask 573115-833-007-001 - Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 1 NUT 3 EN6115V6X16 1 SCREW DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 396 5

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# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V6X16 Item 3 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (14) Subtask 573115-833-018-001 - Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 397 5

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# @A330 SERVICE BULLETIN
Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 1 NUT 3 EN6115V6X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V6X16 Item 3 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (15) Subtask 573115-833-008-001 - Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 398 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 79 EN6115V7X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V7X16 Item 79 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 399 5

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# @A330 SERVICE BULLETIN (16) Subtask 573115-833-019-001 - Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 79 EN6115V7X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V7X16 Item 79 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 400 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required (17) Subtask 573115-833-024-004 - Install New Fasteners of the Area B in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 7 NUT 3 EN6115V6X16 2 SCREW 5 EN6115V6X18 1 SCREW 7 EN6115V6X20 4 SCREW Kit 573115A05R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 57 EN6115-5Y18 1 SCREW 67 NSA5368PD516B 1 WASHER 80 NSA5372EW716B 2 WASHER 82 ASNA2394EW7 2 WASHER 83 NSA5050-5 1 NUT 85 MS21250-07023 1 SCREW 87 MS21250-07025 1 SCREW 90 NSA5057-7 2 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 401 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCAAD Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Sheet 03
Refer toFig. A-FCAAD Sheet 01 and Fig. A-FCAAD Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found: 1 Install the first oversize fasteners at holes H12 and H14: 2 Screw EN6115V6X16 Item 3 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the first oversize fastener at hole H13: 1 Screw EN6115V6X18 Item 5 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6X20 Item 7 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the second oversize fastener at hole H261: 1 Screw EN6115-5Y18 Item 57 1 Washer NSA5368PD516B Item 67 1 Nut NSA5050-5 Item 83 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 402 5

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# @A330 SERVICE BULLETIN
Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the first oversize fastener at hole H262: 1 Screw MS21250-07023 Item 85 1 Washer ASNA2394EW7 Item 82 1 Washer NSA5372EW716B Item 80 1 Nut NSA5057-7 Item 90 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the first oversize fastener at hole H263: 1 Screw MS21250-07025 Item 87 1 Washer ASNA2394EW7 Item 82 1 Washer NSA5372EW716B Item 80 1 Nut NSA5057-7 Item 90 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (18) Subtask 573115-833-021-004 - Install New Fasteners of the Area B in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 403 5

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# @A330 SERVICE BULLETIN
Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 7 NUT 3 EN6115V6X16 2 SCREW 5 EN6115V6X18 1 SCREW 7 EN6115V6X20 4 SCREW Kit 573115A05R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 57 EN6115-5Y18 1 SCREW 67 NSA5368PD516B 1 WASHER 80 NSA5372EW716B 2 WASHER 82 ASNA2394EW7 2 WASHER 83 NSA5050-5 1 NUT 85 MS21250-07023 1 SCREW 87 MS21250-07025 1 SCREW 90 NSA5057-7 2 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAD Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02 Sheet 03
Refer toFig. A-FCAAD Sheet 01 and Fig. A-FCAAD Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found: 1 Install the first oversize fasteners at holes H12 and H14: 2 Screw EN6115V6X16 Item 3 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 404 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

2 Install the first oversize fastener at hole H13: 1 Screw EN6115V6X18 Item 5 1 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6X20 Item 7 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the second oversize fastener at hole H261: 1 Screw EN6115-5Y18 Item 57 1 Washer NSA5368PD516B Item 67 1 Nut NSA5050-5 Item 83 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the first oversize fastener at hole H262: 1 Screw MS21250-07023 Item 85 1 Washer ASNA2394EW7 Item 82 1 Washer NSA5372EW716B Item 80 1 Nut NSA5057-7 Item 90 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 405 5

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# @A330 SERVICE BULLETIN

6 Install the first oversize fastener at hole H263: 1 Screw MS21250-07025 Item 87 1 Washer ASNA2394EW7 Item 82 1 Washer NSA5372EW716B Item 80 1 Nut NSA5057-7 Item 90 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required
**CONF 005 (1) Subtask 573115-833-001-007 - Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 1 SCREW 2 ASNA2531-6 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 406 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V6-16 Item 1 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (2) Subtask 573115-833-010-005 - Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 1 SCREW 2 ASNA2531-6 1 NUT

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 407 5

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# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V6-16 Item 1 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (3) Subtask 573115-833-002-015 - Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 408 5

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# @A330 SERVICE BULLETIN
Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 94 EN6115V7-16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V7-16 Item 94 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (4) Subtask 573115-833-011-003 - Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 409 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 94 EN6115V7-16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V7-16 Item 94 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 410 5

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# @A330 SERVICE BULLETIN (5) Subtask 573115-833-022-005 - Install New same Fasteners of the Area B in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 2 SCREW 2 ASNA2531-6 8 NUT 9 ASNA2531-5 1 NUT 61 MS21250-06018 1 SCREW 62 MS20002C6 1 WASHER 63 NSA5057-6 1 NUT 73 EN6115V5-20 1 SCREW 75 EN6115V6-24 4 SCREW 91 EN6115V6-19 1 SCREW 93 EN6115V6-22 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 411 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the area B, if no crack is found, install the fasteners. 1 Install the fasteners at holes H12 and H14: 2 Screw EN6115V6-16 Item 1 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the fastener at hole H13: 1 Screw EN6115V6-19 Item 91 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6-24 Item 75 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the fastener at hole H261: 1 Screw EN6115V5-20 Item 73 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the fastener at hole H262: 1 Screw EN6115V6-22 Item 93 1 Nut ASNA2531-6 Item 2 Wet install the fastener with:
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 412 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

6 Install the fastener at hole H263: 1 Screw MS21250-06018 Item 61 1 Washer MS20002C6 Item 62 1 Nut NSA5057-6 Item 63 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (6) Subtask 573115-833-013-005 - Install New same Fasteners of the Area B in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 2 SCREW 2 ASNA2531-6 8 NUT 9 ASNA2531-5 1 NUT 61 MS21250-06018 1 SCREW 62 MS20002C6 1 WASHER 63 NSA5057-6 1 NUT 73 EN6115V5-20 1 SCREW 75 EN6115V6-24 4 SCREW 91 EN6115V6-19 1 SCREW 93 EN6115V6-22 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 413 5

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# @A330 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found, install the fasteners. 1 Install the fasteners at holes H12 and H14: 2 Screw EN6115V6-16 Item 1 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the fastener at hole H13: 1 Screw EN6115V6-19 Item 91 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6-24 Item 75 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the fastener at hole H261: 1 Screw EN6115V5-20 Item 73 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 414 5

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# @A330 SERVICE BULLETIN

1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the fastener at hole H262: 1 Screw EN6115V6-22 Item 93 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the fastener at hole H263: 1 Screw MS21250-06018 Item 61 1 Washer MS20002C6 Item 62 1 Nut NSA5057-6 Item 63 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (7) Subtask 573115-833-004-001 - Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 415 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCCAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (8) Subtask 573115-833-014-001 - Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCCAA Sheet 01

. DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 416 5

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# @A330 SERVICE BULLETIN
b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (9) Subtask 573115-833-005-001 - Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCDAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (10) Subtask 573115-833-015-001 - Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 417 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCDAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (11) Subtask 573115-833-023-005 - Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 418 5

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# @A330 SERVICE BULLETIN
In accordance with SRM 51-44-00 (a) Depending on inspection results of the areas B, if crack is found, oversize the holes.
a Drill to the first oversize diameter in comparison with the current hole diameter the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

. b Do a rototest inspection of the drilled holes to check if the crack is still present. Refer to NTM 51-10-01 (12) Subtask 573115-833-017-005 - Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 In accordance with SRM 51-44-00 (a) Depending on inspection results of the areas B, if crack is found, oversize the holes.
a Drill to the first oversize diameter in comparison with the current hole diameter the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

. b Do a rototest inspection of the drilled holes to check if the crack is still present. Refer to NTM 51-10-01
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 419 5

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# @A330 SERVICE BULLETIN (13) Subtask 573115-833-007-015 - Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 1 NUT 3 EN6115V6X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V6X16 Item 3 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 420 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required (14) Subtask 573115-833-018-003 - Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 1 NUT Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 EN6115V6X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 421 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V6X16 Item 3 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (15) Subtask 573115-833-008-015 - Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 79 EN6115V7X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 422 5

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# @A330 SERVICE BULLETIN
Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V7X16 Item 79 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (16) Subtask 573115-833-019-003 - Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 79 EN6115V7X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 423 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V7X16 Item 79 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (17) Subtask 573115-833-024-005 - Install New Fasteners of the Area B in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 8 NUT 3 EN6115V6X16 2 SCREW 9 ASNA2531-5 1 NUT 52 ASNA0094-6 1 NUT 62 MS20002C6 1 WASHER 65 NSA5398-6-18A 1 SCREW 74 EN6115V5X20 1 SCREW DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 424 5

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# @A330 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 76 EN6115V6X24 4 SCREW 92 EN6115V6X19 1 SCREW 95 EN6115V6X22 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found: 1 Install the first oversize fasteners at holes H12 and H14: 2 Screw EN6115V6X16 Item 3 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the first oversize fastener at hole H13: 1 Screw EN6115V6X19 Item 92 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6X24 Item 76 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 425 5

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# @A330 SERVICE BULLETIN

4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the first oversize fastener at hole H261: 1 Screw EN6115V5X20 Item 74 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the first oversize fastener at hole H262: 1 Screw EN6115V6X22 Item 95 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the first oversize fastener at hole H263: 1 Screw NSA5398-6-18A Item 65 1 Washer MS20002C6 Item 62 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (18) Subtask 573115-833-021-005 - Install New Fasteners of the Area B in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 426 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 8 NUT 3 EN6115V6X16 2 SCREW 9 ASNA2531-5 1 NUT 52 ASNA0094-6 1 NUT 62 MS20002C6 1 WASHER 65 NSA5398-6-18A 1 SCREW 74 EN6115V5X20 1 SCREW 76 EN6115V6X24 4 SCREW 92 EN6115V6X19 1 SCREW 95 EN6115V6X22 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found: 1 Install the first oversize fasteners at holes H12 and H14: 2 Screw EN6115V6X16 Item 3 2 Nut ASNA2531-6 Item 2 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 427 5

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# @A330 SERVICE BULLETIN
Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the first oversize fastener at hole H13: 1 Screw EN6115V6X19 Item 92 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6X24 Item 76 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the first oversize fastener at hole H261: 1 Screw EN6115V5X20 Item 74 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the first oversize fastener at hole H262: 1 Screw EN6115V6X22 Item 95 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the first oversize fastener at hole H263: 1 Screw NSA5398-6-18A Item 65 1 Washer MS20002C6 Item 62
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 428 5

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# @A330 SERVICE BULLETIN

1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required
**CONF 006 (1) Subtask 573115-833-001-007 - Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 1 SCREW 2 ASNA2531-6 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 429 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V6-16 Item 1 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (2) Subtask 573115-833-010-005 - Install New same Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 1 SCREW 2 ASNA2531-6 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 430 5

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# @A330 SERVICE BULLETIN
Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V6-16 Item 1 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (3) Subtask 573115-833-002-015 - Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 94 EN6115V7-16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 431 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V7-16 Item 94 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (4) Subtask 573115-833-011-003 - Install New same Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 94 EN6115V7-16 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 432 5

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# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V7-16 Item 94 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (5) Subtask 573115-833-022-005 - Install New same Fasteners of the Area B in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 433 5

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# @A330 SERVICE BULLETIN
Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 2 SCREW 2 ASNA2531-6 8 NUT 9 ASNA2531-5 1 NUT 61 MS21250-06018 1 SCREW 62 MS20002C6 1 WASHER 63 NSA5057-6 1 NUT 73 EN6115V5-20 1 SCREW 75 EN6115V6-24 4 SCREW 91 EN6115V6-19 1 SCREW 93 EN6115V6-22 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found, install the fasteners. 1 Install the fasteners at holes H12 and H14: 2 Screw EN6115V6-16 Item 1 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 434 5

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# @A330 SERVICE BULLETIN

2 Install the fastener at hole H13: 1 Screw EN6115V6-19 Item 91 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6-24 Item 75 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the fastener at hole H261: 1 Screw EN6115V5-20 Item 73 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the fastener at hole H262: 1 Screw EN6115V6-22 Item 93 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the fastener at hole H263: 1 Screw MS21250-06018 Item 61 1 Washer MS20002C6 Item 62 1 Nut NSA5057-6 Item 63 Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 435 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required (6) Subtask 573115-833-013-005 - Install New same Fasteners of the Area B in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 2 SCREW 2 ASNA2531-6 8 NUT 9 ASNA2531-5 1 NUT 61 MS21250-06018 1 SCREW 62 MS20002C6 1 WASHER 63 NSA5057-6 1 NUT 73 EN6115V5-20 1 SCREW 75 EN6115V6-24 4 SCREW 91 EN6115V6-19 1 SCREW 93 EN6115V6-22 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 Refer to AMM Task 20-21-11-911-801 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 436 5

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# @A330 SERVICE BULLETIN
In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found, install the fasteners. 1 Install the fasteners at holes H12 and H14: 2 Screw EN6115V6-16 Item 1 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the fastener at hole H13: 1 Screw EN6115V6-19 Item 91 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6-24 Item 75 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the fastener at hole H261: 1 Screw EN6115V5-20 Item 73 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the fastener at hole H262: 1 Screw EN6115V6-22 Item 93 1 Nut ASNA2531-6 Item 2
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 437 5

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# @A330 SERVICE BULLETIN
Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the fastener at hole H263: 1 Screw MS21250-06018 Item 61 1 Washer MS20002C6 Item 62 1 Nut NSA5057-6 Item 63 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (7) Subtask 573115-833-004-001 - Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCCAA Sheet 01

.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 438 5

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# @A330 SERVICE BULLETIN
b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (8) Subtask 573115-833-014-001 - Oversize the Hole of the Area A Pre Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCCAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (9) Subtask 573115-833-005-001 - Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 439 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCDAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (10) Subtask 573115-833-015-001 - Oversize the Hole of the Area A Post Service Bulletin No. A330-57-3083 to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 440 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCDAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (11) Subtask 573115-833-023-005 - Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 In accordance with SRM 51-44-00 (a) Depending on inspection results of the areas B, if crack is found, oversize the holes.
a Drill to the first oversize diameter in comparison with the current hole diameter the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

. DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 441 5

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# @A330 SERVICE BULLETIN
b Do a rototest inspection of the drilled holes to check if the crack is still present. Refer to NTM 51-10-01 (12) Subtask 573115-833-017-005 - Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 In accordance with SRM 51-44-00 (a) Depending on inspection results of the areas B, if crack is found, oversize the holes.
a Drill to the first oversize diameter in comparison with the current hole diameter the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

. b Do a rototest inspection of the drilled holes to check if the crack is still present. Refer to NTM 51-10-01 (13) Subtask 573115-833-007-015 - Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 442 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 1 NUT 3 EN6115V6X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V6X16 Item 3 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 443 5

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# @A330 SERVICE BULLETIN (14) Subtask 573115-833-018-003 - Install New Fastener Pre Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A01R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 1 NUT Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 EN6115V6X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCCAA Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCCAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 444 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V6X16 Item 3 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (15) Subtask 573115-833-008-015 - Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 79 EN6115V7X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 445 5

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# @A330 SERVICE BULLETIN
Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V7X16 Item 79 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (16) Subtask 573115-833-019-003 - Install New Fastener Post Service Bulletin No. A330-57-3083 of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 78 ASNA2531-7 1 NUT 79 EN6115V7X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 446 5

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# @A330 SERVICE BULLETIN

References Fig. A-FCDAA Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCDAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V7X16 Item 79 1 Nut ASNA2531-7 Item 78 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (17) Subtask 573115-833-024-005 - Install New Fasteners of the Area B in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 8 NUT 3 EN6115V6X16 2 SCREW 9 ASNA2531-5 1 NUT 52 ASNA0094-6 1 NUT 62 MS20002C6 1 WASHER 65 NSA5398-6-18A 1 SCREW 74 EN6115V5X20 1 SCREW DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 447 5

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# @A330 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 76 EN6115V6X24 4 SCREW 92 EN6115V6X19 1 SCREW 95 EN6115V6X22 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found: 1 Install the first oversize fasteners at holes H12 and H14: 2 Screw EN6115V6X16 Item 3 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the first oversize fastener at hole H13: 1 Screw EN6115V6X19 Item 92 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6X24 Item 76 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 448 5

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# @A330 SERVICE BULLETIN

4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the first oversize fastener at hole H261: 1 Screw EN6115V5X20 Item 74 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the first oversize fastener at hole H262: 1 Screw EN6115V6X22 Item 95 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the first oversize fastener at hole H263: 1 Screw NSA5398-6-18A Item 65 1 Washer MS20002C6 Item 62 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (18) Subtask 573115-833-021-005 - Install New Fasteners of the Area B in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 449 5

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# @A330 SERVICE BULLETIN
Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 8 NUT 3 EN6115V6X16 2 SCREW 9 ASNA2531-5 1 NUT 52 ASNA0094-6 1 NUT 62 MS20002C6 1 WASHER 65 NSA5398-6-18A 1 SCREW 74 EN6115V5X20 1 SCREW 76 EN6115V6X24 4 SCREW 92 EN6115V6X19 1 SCREW 95 EN6115V6X22 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found: 1 Install the first oversize fasteners at holes H12 and H14: 2 Screw EN6115V6X16 Item 3 2 Nut ASNA2531-6 Item 2 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 450 5

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# @A330 SERVICE BULLETIN
Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the first oversize fastener at hole H13: 1 Screw EN6115V6X19 Item 92 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6X24 Item 76 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the first oversize fastener at hole H261: 1 Screw EN6115V5X20 Item 74 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the first oversize fastener at hole H262: 1 Screw EN6115V6X22 Item 95 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the first oversize fastener at hole H263: 1 Screw NSA5398-6-18A Item 65 1 Washer MS20002C6 Item 62
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 451 5

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# @A330 SERVICE BULLETIN

1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required
**CONF 007 (1) Subtask 573115-833-003-001 - Install New same Fastener of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 1 SCREW 2 ASNA2531-6 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCEAA Removal/Installation of the Fastener of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCEAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 452 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V6-16 Item 1 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (2) Subtask 573115-833-012-001 - Install New same Fastener of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 1 SCREW 2 ASNA2531-6 1 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCEAA Removal/Installation of the Fastener of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCEAA Sheet 01 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 453 5

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# @A330 SERVICE BULLETIN
Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found, install the fastener. 1 Install the fastener at hole H260: 1 Screw EN6115V6-16 Item 1 1 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required (3) Subtask 573115-833-022-005 - Install New same Fasteners of the Area B in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 2 SCREW 2 ASNA2531-6 8 NUT 9 ASNA2531-5 1 NUT 61 MS21250-06018 1 SCREW 62 MS20002C6 1 WASHER 63 NSA5057-6 1 NUT 73 EN6115V5-20 1 SCREW 75 EN6115V6-24 4 SCREW 91 EN6115V6-19 1 SCREW 93 EN6115V6-22 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 454 5

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# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found, install the fasteners. 1 Install the fasteners at holes H12 and H14: 2 Screw EN6115V6-16 Item 1 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the fastener at hole H13: 1 Screw EN6115V6-19 Item 91 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6-24 Item 75 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with:
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 455 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

4 Install the fastener at hole H261: 1 Screw EN6115V5-20 Item 73 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the fastener at hole H262: 1 Screw EN6115V6-22 Item 93 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the fastener at hole H263: 1 Screw MS21250-06018 Item 61 1 Washer MS20002C6 Item 62 1 Nut NSA5057-6 Item 63 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (4) Subtask 573115-833-013-005 - Install New same Fasteners of the Area B in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 456 5

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# @A330 SERVICE BULLETIN
Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V6-16 2 SCREW 2 ASNA2531-6 8 NUT 9 ASNA2531-5 1 NUT 61 MS21250-06018 1 SCREW 62 MS20002C6 1 WASHER 63 NSA5057-6 1 NUT 73 EN6115V5-20 1 SCREW 75 EN6115V6-24 4 SCREW 91 EN6115V6-19 1 SCREW 93 EN6115V6-22 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found, install the fasteners. 1 Install the fasteners at holes H12 and H14: 2 Screw EN6115V6-16 Item 1 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 457 5

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# @A330 SERVICE BULLETIN

2 Install the fastener at hole H13: 1 Screw EN6115V6-19 Item 91 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6-24 Item 75 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the fastener at hole H261: 1 Screw EN6115V5-20 Item 73 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the fastener at hole H262: 1 Screw EN6115V6-22 Item 93 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the fastener at hole H263: 1 Screw MS21250-06018 Item 61 1 Washer MS20002C6 Item 62 1 Nut NSA5057-6 Item 63 Wet install the fastener with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 458 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required (5) Subtask 573115-833-006-001 - Oversize the Hole of the Area A to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCEAA Removal/Installation of the Fastener of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCEAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCEAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (6) Subtask 573115-833-016-001 - Oversize the Hole of the Area A to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 459 5

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# @A330 SERVICE BULLETIN

References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCEAA Removal/Installation of the Fastener of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCEAA Sheet 01 In accordance with SRM 51-44-00 (a) Depending on inspection results of the area A, if crack is found, oversize the hole.
a Drill to the first oversize diameter in comparison with the hole H260 to the dimension given in Fig. A-FCEAA Sheet 01

. b Do a rototest inspection of the drilled hole to check if the crack is still present. Refer to NTM 51-10-01 (7) Subtask 573115-833-023-005 - Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 In accordance with SRM 51-44-00

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 460 5

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# @A330 SERVICE BULLETIN (a) Depending on inspection results of the areas B, if crack is found, oversize the holes.
a Drill to the first oversize diameter in comparison with the current hole diameter the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

. b Do a rototest inspection of the drilled holes to check if the crack is still present. Refer to NTM 51-10-01 (8) Subtask 573115-833-017-005 - Oversize the Holes of the Area B to First Oversize in comparison with the current hole diameter, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Structural Repair Manual (SRM) 51-44-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 In accordance with SRM 51-44-00 (a) Depending on inspection results of the areas B, if crack is found, oversize the holes.
a Drill to the first oversize diameter in comparison with the current hole diameter the holes H12, H13, H14, H21, H22, H23, H24, H261, H262 and H263 to the dimension given in Fig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02

. b Do a rototest inspection of the drilled holes to check if the crack is still present. Refer to NTM 51-10-01

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 461 5

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# @A330 SERVICE BULLETIN (9) Subtask 573115-833-009-001 - Install New Fastener of the Area A in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 1 NUT 3 EN6115V6X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCEAA Removal/Installation of the Fastener of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCEAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V6X16 Item 3 1 Nut ASNA2531-6 Item 2 Wet install the fastener with:
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 462 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required (10) Subtask 573115-833-020-001 - Install New Fastener of the Area A in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 1 NUT 3 EN6115V6X16 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCEAA Removal/Installation of the Fastener of the Area A of the Frame 40, LH and RH Sides Sheet 01

Refer toFig. A-FCEAA Sheet 01 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area A, if no crack is found: 1 Install the fastener at hole H260: 1 Screw EN6115V6X16 Item 3
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 463 5

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# @A330 SERVICE BULLETIN

1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (11) Subtask 573115-833-024-005 - Install New Fasteners of the Area B in transition fit, LH Side Work Zones and Access Panels Zone Access/Work location 137 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 8 NUT 3 EN6115V6X16 2 SCREW 9 ASNA2531-5 1 NUT 52 ASNA0094-6 1 NUT 62 MS20002C6 1 WASHER 65 NSA5398-6-18A 1 SCREW 74 EN6115V5X20 1 SCREW 76 EN6115V6X24 4 SCREW 92 EN6115V6X19 1 SCREW 95 EN6115V6X22 1 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 464 5

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# @A330 SERVICE BULLETIN
Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found: 1 Install the first oversize fasteners at holes H12 and H14: 2 Screw EN6115V6X16 Item 3 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the first oversize fastener at hole H13: 1 Screw EN6115V6X19 Item 92 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6X24 Item 76 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

4 Install the first oversize fastener at hole H261: 1 Screw EN6115V5X20 Item 74 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the first oversize fastener at hole H262: 1 Screw EN6115V6X22 Item 95 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 465 5

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# @A330 SERVICE BULLETIN

1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the first oversize fastener at hole H263: 1 Screw NSA5398-6-18A Item 65 1 Washer MS20002C6 Item 62 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required (12) Subtask 573115-833-021-005 - Install New Fasteners of the Area B in transition fit, RH Side Work Zones and Access Panels Zone Access/Work location 138 Work location Frame 40 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 573115A06R03 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2531-6 8 NUT 3 EN6115V6X16 2 SCREW 9 ASNA2531-5 1 NUT 52 ASNA0094-6 1 NUT 62 MS20002C6 1 WASHER 65 NSA5398-6-18A 1 SCREW 74 EN6115V5X20 1 SCREW 76 EN6115V6X24 4 SCREW 92 EN6115V6X19 1 SCREW 95 EN6115V6X22 1 SCREW

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 466 5

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# @A330 SERVICE BULLETIN

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-801 Structural Repair Manual (SRM) 51-42-00 51-43-00 Fig. A-FCAAF Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides Sheet 01 Sheet 02

Refer toFig. A-FCAAF Sheet 01 and Fig. A-FCAAF Sheet 02 Refer to AMM Task 20-21-11-911-801 In accordance with SRM 51-42-00, SRM 51-43-00 (a) Depending on inspection results of the area B, if no crack is found: 1 Install the first oversize fasteners at holes H12 and H14: 2 Screw EN6115V6X16 Item 3 2 Nut ASNA2531-6 Item 2 Wet install the fasteners with: Sealant-Brush Consistency 09-013 As required

2 Install the first oversize fastener at hole H13: 1 Screw EN6115V6X19 Item 92 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

3 Install the first oversize fasteners at holes H21, H22, H23 and H24: 4 Screw EN6115V6X24 Item 76 4 Nut ASNA2531-6 Item 2 Wet install the fasteners with:

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 467 5

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# @A330 SERVICE BULLETIN

Sealant-Brush Consistency 09-013 As required

4 Install the first oversize fastener at hole H261: 1 Screw EN6115V5X20 Item 74 1 Nut ASNA2531-5 Item 9 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

5 Install the first oversize fastener at hole H262: 1 Screw EN6115V6X22 Item 95 1 Nut ASNA2531-6 Item 2 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required

6 Install the first oversize fastener at hole H263: 1 Screw NSA5398-6-18A Item 65 1 Washer MS20002C6 Item 62 1 Nut ASNA0094-6 Item 52 Wet install the fastener with: Sealant-Brush Consistency 09-013 As required
**CONF ALL D. TEST **CONF 001 (1) Subtask 573115-700-002-002 - Testing Manpower Resources Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 468 5

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# @A330 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access SUBTASK 573115-010-003 001 Remove/Open for Access in the FWD Cargo-Compartment and SUBTASK 573115-010-004 001 Remove/Open for Access in the Belly Fairing Area . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802). 2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). 5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). **CONF 002 (1) Subtask 573115-700-002-001 - Testing Manpower Resources Skills NON SPECIFIC DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 469 5

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# @A330 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access SUBTASK 573115-010-003 001 Remove/Open for Access in the FWD Cargo-Compartment and SUBTASK 573115-010-004 001 Remove/Open for Access in the Belly Fairing Area . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802). 2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). 5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). **CONF 003 (1) Subtask 573115-700-002-003 - Testing Manpower Resources Skills NON SPECIFIC DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 470 5

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# @A330 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access SUBTASK 573115-010-003 001 Remove/Open for Access in the FWD Cargo-Compartment and SUBTASK 573115-010-004 001 Remove/Open for Access in the Belly Fairing Area . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802). 2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). 5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). **CONF 004 (1) Subtask 573115-700-002-004 - Testing Manpower Resources Skills NON SPECIFIC DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 471 5

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# @A330 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access SUBTASK 573115-010-003 001 Remove/Open for Access in the FWD Cargo-Compartment and SUBTASK 573115-010-004 001 Remove/Open for Access in the Belly Fairing Area . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802). 2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). 5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). **CONF 005 (1) Subtask 573115-700-002-006 - Testing Manpower Resources Skills NON SPECIFIC DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 472 5

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# @A330 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access SUBTASK 573115-010-003 001 Remove/Open for Access in the FWD Cargo-Compartment and SUBTASK 573115-010-004 001 Remove/Open for Access in the Belly Fairing Area . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802). 2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). 5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). **CONF 006 (1) Subtask 573115-700-002-007 - Testing Manpower Resources Skills NON SPECIFIC DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 473 5

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# @A330 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access SUBTASK 573115-010-003 001 Remove/Open for Access in the FWD Cargo-Compartment and SUBTASK 573115-010-004 001 Remove/Open for Access in the Belly Fairing Area . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802). 2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). 5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). **CONF 007 (1) Subtask 573115-700-002-008 - Testing Manpower Resources Skills NON SPECIFIC DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 474 5

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

# @A330 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 21-52-41-400-801 Task 25-52-00-400-801 Task 36-22-19-400-801 Task 53-35-13-400-802 NOTE: This test procedure is to be accomplished after the installation of the parts removed for the access SUBTASK 573115-010-003 001 Remove/Open for Access in the FWD Cargo-Compartment and SUBTASK 573115-010-004 001 Remove/Open for Access in the Belly Fairing Area . (a) Job Set-up: 1 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Belly Fairing Access-Panels (Refer to AMM Task 53-35-13-400-802). 2 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 3 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 4 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Ceiling Panels, the Partition Panels and the Sidewall Panels in the Forward Cargo Compartment (Refer to AMM Task 25-52-00-400-801). 5 Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801). (b) Procedure: 1 Do test procedure as specified after the Installation of Wing Bleed-air Duct Sensing Elements (Refer to AMM Task 36-22-19-400-801). 2 Do test procedure as specified after the Installation of Air Conditioning Pack (Refer to AMM Task 21-52-41-400-801). 3 Do test procedure as specified after the Installation of the Air-Conditioning Distribution Ducts (Refer to AMM Task 21-20-00-410-801).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 475 5

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# @A330 SERVICE BULLETIN
**CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 573115-410-003-002 - Install/Close Items Removed/Opened for access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 27-84-41-400-802 Task 53-35-13-400-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 002 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) On the RH side, install the retained universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 476 5

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# @A330 SERVICE BULLETIN (c) On the RH side, install the air ventilation duct (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBCAA Sheet 01). 1 Install: 1 Duct Item (41) Retained at removal (d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-400-802). (2) Subtask 573115-410-004-002 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 25-80-00-400-801 Task 52-30-00-410-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 002 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment.
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 477 5

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# @A330 SERVICE BULLETIN (b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801). (c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retained at removal (d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801). (e) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (3) Subtask 573115-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition. **CONF 002 (1) Subtask 573115-410-003-001 - Install/Close Items Removed/Opened for access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 478 5

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# @A330 SERVICE BULLETIN

References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-001 Task 27-84-41-400-802 Task 53-35-13-400-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: This paragraph is apply only if no crack found after the result of the inspection. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 001 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) On the RH side, install the retained universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-400-802). (c) On the RH side, install the air ventilation duct (Refer toAMM Task 21-20-00-410-001 and Fig. A-FBCAA Sheet 01). 1 Install: 1 Duct Item (41) Retained at removal (d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-001 and Fig. A-FBBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 479 5

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

# @A330 SERVICE BULLETIN (2) Subtask 573115-410-004-001 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 25-80-00-400-801 Task 52-30-00-410-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 001 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801). (c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retained at removal DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 480 5

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# @A330 SERVICE BULLETIN (d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801). (e) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (3) Subtask 573115-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition. **CONF 003 (1) Subtask 573115-410-003-003 - Install/Close Items Removed/Opened for access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 27-84-41-400-802 Task 53-35-13-400-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 481 5

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

# @A330 SERVICE BULLETIN SUBTASK 573115-700-001 003 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) On the RH side, install the retained universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-400-802). (c) On the RH side, install the air ventilation duct (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBCAA Sheet 01). 1 Install: 1 Duct Item (41) Retained at removal (d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-400-802). (2) Subtask 573115-410-004-003 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 25-80-00-400-801 Task 52-30-00-410-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 482 5

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# @A330 SERVICE BULLETIN
CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 003 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801). (c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retained at removal (d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801). (e) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (3) Subtask 573115-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition. **CONF 004 (1) Subtask 573115-410-003-004 - Install/Close Items Removed/Opened for access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 483 5

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# @A330 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 27-84-41-400-802 Task 53-35-13-400-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 004 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) On the RH side, install the retained universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-400-802). (c) On the RH side, install the air ventilation duct (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBCAA Sheet 01). 1 Install: 1 Duct Item (41) Retained at removal (d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 484 5

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# @A330 SERVICE BULLETIN (2) Subtask 573115-410-004-004 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 25-80-00-400-801 Task 52-30-00-410-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 004 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801). (c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retained at removal DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 485 5

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# @A330 SERVICE BULLETIN (d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801). (e) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (3) Subtask 573115-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition. **CONF 005 (1) Subtask 573115-410-003-006 - Install/Close Items Removed/Opened for access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 27-84-41-400-802 Task 53-35-13-400-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 486 5

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

# @A330 SERVICE BULLETIN SUBTASK 573115-700-001 006 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) On the RH side, install the retained universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-400-802). (c) On the RH side, install the air ventilation duct (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBCAA Sheet 01). 1 Install: 1 Duct Item (41) Retained at removal (d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-400-802). (2) Subtask 573115-410-004-006 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 25-80-00-400-801 Task 52-30-00-410-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 487 5

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

# @A330 SERVICE BULLETIN
CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 006 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801). (c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retained at removal (d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801). (e) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (3) Subtask 573115-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition. **CONF 006 (1) Subtask 573115-410-003-007 - Install/Close Items Removed/Opened for access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 488 5

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

# @A330 SERVICE BULLETIN
Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 27-84-41-400-802 Task 53-35-13-400-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 007 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) On the RH side, install the retained universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-400-802). (c) On the RH side, install the air ventilation duct (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBCAA Sheet 01). 1 Install: 1 Duct Item (41) Retained at removal (d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-400-802).

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 489 5

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

# @A330 SERVICE BULLETIN (2) Subtask 573115-410-004-007 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 25-80-00-400-801 Task 52-30-00-410-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 007 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801). (c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retained at removal DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 490 5

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# @A330 SERVICE BULLETIN (d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801). (e) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (3) Subtask 573115-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition. **CONF 007 (1) Subtask 573115-410-003-008 - Install/Close Items Removed/Opened for access in the Belly Fairing Area Work Zones and Access Panels Zone Access/Work location 192 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 27-84-41-400-802 Task 53-35-13-400-802 Fig. A-FBBAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

Fig. A-FBCAA Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL. CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 491 5

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

# @A330 SERVICE BULLETIN SUBTASK 573115-700-001 008 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) On the RH side, install the retained universal joint between the slat angle gearbox and the torque shaft (Refer to AMM Task 27-84-41-400-802). (c) On the RH side, install the air ventilation duct (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBCAA Sheet 01). 1 Install: 1 Duct Item (41) Retained at removal (d) On the RH side, install the air-conditioning pack outlet duct as follows (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBBAA Sheet 01). 1 Install: 1 Duct Item (26) Retained at removal (e) Install the access panels 192JB, 192GB, 191FB and 191KB (Refer to AMM Task 53-35-13-400-802). (2) Subtask 573115-410-004-008 - Install/Close Items Removed/Opened for Access in the FWD Cargo-Compartment Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 39.1 to Frame 40 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-801 Task 25-52-00-400-801 Task 25-80-00-400-801 Task 52-30-00-410-801 Fig. A-FBAAA Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD Cargo-Compartment) Sheet 01

WARNING: MAKE SURE THAT AIR IS NOT SUPPLIED TO THE AIR CONDITIONING SYSTEM FROM THE MAIN ENGINE, THE APU OR A GROUND SOURCE. HOT COMPRESSED AIR CAN CAUSE INJURY TO PERSONNEL.
DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 492 5

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

# @A330 SERVICE BULLETIN
CAUTION: DO NOT STEP ON THE DUCTS BECAUSE THEY ARE FRAGILE. NOTE: The parts removed for the access must be installed before the SUBTASK 573115-700-001 008 Testing . (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the insulation back in position, (Refer to AMM Task 25-80-00-400-801). (c) On the LH and RH sides, install the air conditioning ducts between Frame 39.1 and Frame 40 (Refer to AMM Task 21-20-00-410-801 and Fig. A-FBAAA Sheet 01). 1 Install: 2 Duct Item (11) Retained at removal 2 Duct Item (12) Retained at removal2 Recirculation filterhousing Item (13) Retained at removal 2 Recirculation fan Item (14) Retained at removal (d) Install the partition panels 131CX, 131DX, 132CX and 132DX (Refer to AMM Task 25-52-00-400-801). (e) Close the FWD cargo-compartment door 821 (Refer to AMM Task 52-30-00-410-801). (3) Subtask 573115-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC (a) Remove all the fixtures, tools, test and support equipment used during this procedure. (b) Remove the access platform(s). (c) Restore the systems and the aircraft to normal operating condition.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 493 5

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

# @A330 SERVICE BULLETIN

**CONF ALL

RH SIDE SHOWN LH SIDE SYMMETRICAL Z130 FR39.1 FR40

(11) (12)

(14) (13)



## B **B**
**B A** 



## A

G_SB_573115_5_BAAA_01_01 Figure A-FBAAA - Sheet 01Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (FWD CargoCompartment) DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 494 5

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

# @A330 SERVICE BULLETIN

**CONF ALL



### A **B** FR39.2FR40.2



## A

**B** (26) Z192

G_SB_573115_5_BBAA_01_01 Figure A-FBBAA - Sheet 01 Removal/Installation of the Air Conditioning Ducts between FR39.1 and FR40 (Belly Fairing Area) DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 495 5

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

# @A330 SERVICE BULLETIN

**CONF ALL

FR39.2FR40.2



### B

(41) 

## A

**B A**  Z192

G_SB_573115_5_BCAA_01_01 Figure A-FBCAA - Sheet 01 Removal/Installation of the Ventilation Ducts between FR39.1 and FR40 (Belly Fairing Area) DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 496 5

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

# @A330 SERVICE BULLETIN

**CONF 001 FR47

FR40

FR40 

### B
**B** 

## A

**B** LH SIDE SHOWN RH SIDE SYMMETRICAL 

### A − Z141 Z142

STGR38

STGR39

STGR40 STGR37 H263 H262 H261

H23 H14 H24 H22 H21 H13 H12

VIEW LOOKING AFT CENTER WING BOX LOWER PANEL REFERENCE

**NOTE:** AREA HOLE NUMBER 12, 13, 14, 21, 22, 23, 24, B 261, 262, 263

G_SB_573115_5_CAAB_01_02 Figure A-FCAAB - Sheet 01 Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 497 5

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

# @A330 SERVICE BULLETIN

**CONF 001

HOLE SYMBOL PN DESCRIPTION FINAL HOLE DIAMETER MIN MAX EN6115V6−16 SCREW ASNA2531−6 NUT EN6115V6X16 SCREW NUT N 1 2 3 2 01 EXISTING HOLE DIAMETER MIN MAX

9.387 mm (0.369 in) 9.427 mm (0.370 in) 01
EN6115V6−18 SCREW NUT EN6115V6X18 SCREW NUT N 4 2 5 2 01

01
EN6115V6−20 SCREW NUT EN6115V6X20 SCREW NUT N 6 2 7 2 01

01
EN6115−5X18 SCREW ASNA2531−5 NUT EN6115−5Y18 SCREW NUT N ASNA2531−5 91 9 57 9

10.282 mm (0.404 in) 10.321 mm (0.406 in) NSA5399−6−18A SCREW ASNA2394EW6 WASHER ASNA0094−6 NUT N MS21250−07018 50 58 52 53

N 82 90 02

9.387 mm (0.369 in) 9.427 mm (0.370 in)

9.387 mm (0.369 in) 9.427 mm (0.370 in)

8.211 mm (0.323 in) 8.245 mm (0.324 in) ASNA2531−6
ASNA2531−6
ASNA2531−6
ASNA2531−6
ASNA2531−6

SCREW WASHER NUT ASNA2394EW7 NSA5057−7

10.282 mm (0.404 in) 10.321 mm (0.406 in) NSA5399−6−22A SCREW ASNA2394EW6 WASHER ASNA0094−6 NUT MS21250−07022 59 58 52 60 82 90 SCREW WASHER NUT ASNA2394EW7 NSA5057−7 02

02

02

02

02 (1) (2) (1) (2) (4) (2) (1) (2) (6) (2) (6) (2) (91) (9) (56) (9) (50) (58) (52) (50) (51) (52) (59) (58) (52) (59) (58) (52) ITEM REMARKS
STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE

NEXT NOMINAL STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE
STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE
SECOND OVERSIZE

IN TRANSITION FIT SECOND OVERSIZE

IN TRANSITION FIT

NEXT NOMINAL IN TRANSITION FIT SECOND OVERSIZE

IN TRANSITION FIT N HEAD ON THE VISIBLE SIDE
**NOTE:** DEPENDING ON INSPECTION RESULT 01 02 INSTALL THE FASTENERS WITH MAT. No 09−013 (WET ASSEMBLY) 01 02 01 02
01 02

01 02

01 02

01 02 9.886 mm (0.389 in) 9.925 mm (0.390 in)

8.692 mm (0.342 in) 8.732 mm (0.343 in)

11.080 mm (0.436 in) 11.120 mm (0.437 in) 9.490 mm (0.373 in) 9.530 mm (0.377 in)

9.886 mm (0.389 in) 9.925 mm (0.390 in)

9.886 mm (0.389 in) 9.925 mm (0.390 in) 8.296 mm (0.326 in) 8.335 mm (0.328 in)

10.282 mm (0.404 in) 10.321 mm (0.443 in)

10.282 mm (0.404 in) 10.321 mm (0.406 in) 9.490 mm (0.373 in) 9.530 mm (0.377 in)

9.490 mm (0.373 in) 9.530 mm (0.377 in)

11.080 mm (0.436 in) 11.120 mm (0.437 in)

G_SB_573115_5_CAAB_02_06 Figure A-FCAAB - Sheet 02 Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 498 5

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

# @A330 SERVICE BULLETIN

**CONF 002 FR47

FR40

FR40 

### B
**B** 

## A

**B** LH SIDE SHOWN RH SIDE SYMMETRICAL 

### A − Z141 Z142

STGR38

STGR39

STGR40 STGR37 H263 H262 H261

H23 H14 H24H22 H21 H13 H12

VIEW LOOKING AFT CENTER WING BOX LOWER PANEL REFERENCE

**NOTE:** AREA HOLE NUMBER 12, 13, 14, 21, 22, 23, 24, B 261, 262, 263

G_SB_573115_5_CAAA_01_03 Figure A-FCAAA - Sheet 01 Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 499 5

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

# @A330 SERVICE BULLETIN

**CONF 002

HOLE SYMBOL PN DESCRIPTION REMARKS FINAL HOLE DIAMETER MIN MAX

9.886 mm (0.389 in) 9.925 mm (0.390 in) STANDARD FASTENER

IN TRANSITION FIT EN6115V6−16 SCREW ASNA2531−6 NUT EN6115V6X16 SCREW NUT N IN TRANSITION FIT (1) (2) (1) (2) 01

N HEAD ON THE VISIBLE SIDE EXISTING HOLE DIAMETER MIN MAX

9.387 mm (0.369 in) 9.427 mm (0.370 in) FIRST OVERSIZE 01
EN6115V6−18 SCREW NUT EN6115V6X18 SCREW NUT N (4) (2) (1) (2) 01

01
EN6115V6−20 SCREW NUT EN6115V6X20 SCREW NUT N (6) (2) (6) (2) 01

01

8.692 mm (0.342 in) 8.732 mm (0.343 in) EN6115−5X19 SCREW ASNA2531−5 NUT EN6115−5Y19 SCREW NUT N ASNA2531−5 (8) (9) (8) (9)

11.080 mm (0.436 in) 11.120 mm (0.437 in) 10.282 mm (0.404 in) 10.321 mm (0.406 in) NSA5399−6−18A SCREW NSA5372EW616B WASHER ASNA0094−6 NUT N MS21250−07018 (50) (51) (52) (50)

N (51) (52) NEXT NOMINAL 02 9.490 mm (0.373 in) 9.530 mm (0.377 in)

9.886 mm (0.389 in) 9.925 mm (0.390 in) 9.387 mm (0.369 in) 9.427 mm (0.370 in)

9.886 mm (0.389 in) 9.925 mm (0.390 in) 9.387 mm (0.369 in) 9.427 mm (0.370 in)

8.211 mm (0.323 in) 8.245 mm (0.324 in) 8.296 mm (0.326 in) 8.335 mm (0.328 in) ASNA2531−6
ASNA2531−6
ASNA2531−6
ASNA2531−6
ASNA2531−6

SCREW WASHER NUT 10.282 mm (0.404 in) 10.321 mm (0.443 in)

NSA5372EW716B NSA5057−7

10.282 mm (0.404 in) 10.321 mm (0.406 in) NSA5399−6−16A SCREW NSA5372EW616B WASHER ASNA0094−6 NUT MS21250−07016 (54) (51) (52) (54) (51) (52) SCREW WASHER NUT 10.282 mm (0.404 in) 10.321 mm (0.406 in)

NSA5372EW716B NSA5057−7 02

02

02

02

02

**NOTE:** DEPENDING ON INSPECTION RESULT 01 02 1 2 3 2 4 2 5 2 6 2 7 2 8 9 10 9 50 51 52 53 80 90 54 51 52 55 80 90 ITEM

INSTALL THE FASTENERS WITH MAT. No 09−013 (WET ASSEMBLY) STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE
STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE
SECOND OVERSIZE

IN TRANSITION FIT SECOND OVERSIZE

IN TRANSITION FIT

NEXT NOMINAL IN TRANSITION FIT SECOND OVERSIZE

IN TRANSITION FIT 01 02 01 02
01 02

01 02

01 02

01 02 9.490 mm (0.373 in) 9.530 mm (0.377 in)

9.490 mm (0.373 in) 9.530 mm (0.377 in)

11.080 mm (0.436 in) 11.120 mm (0.437 in)

G_SB_573115_5_CAAA_02_06 Figure A-FCAAA - Sheet 02 Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 500 5

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

# @A330 SERVICE BULLETIN

**CONF 003 FR47

FR40

FR40 

### B
**B** 

## A

**B** LH SIDE SHOWN RH SIDE SYMMETRICAL 

### A − Z141 Z142

STGR38

STGR39

STGR40 STGR37 H263 H262 H261

H14 H22 H21 H13 H12

VIEW LOOKING AFT

H23 H24 CENTER WING BOX LOWER PANEL REFERENCE

**NOTE:** AREA HOLE NUMBER 12, 13, 14, 21, 22, 23, 24, B 261, 262, 263

G_SB_573115_5_CAAC_01_02 Figure A-FCAAC - Sheet 01 Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 501 5

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

# @A330 SERVICE BULLETIN

**CONF 003

HOLE SYMBOL PN DESCRIPTION FINAL HOLE DIAMETER MIN MAX EN6115V6−16 SCREW ASNA2531−6 NUT EN6115V6X16 SCREW NUT N 1 2 3 2 EXISTING HOLE DIAMETER MIN MAX

EN6115V6−18 SCREW NUT EN6115V6X18 SCREW NUT N 4 2 5 2 EN6115V6−20 SCREW NUT EN6115V6X20 SCREW NUT N 6 2 7 2 EN6115−5−19 SCREW ASNA2531−5 NUT EN6115−5X19 SCREW NUT N ASNA2531−5 88 9 8 9 MS21250−06018 SCREW WASHER NSA5057−6 NUT N NSA5398−6−18A 61 62 63 65

N 62 52 ASNA2531−6
ASNA2531−6
ASNA2531−6
ASNA2531−6
ASNA2531−6

SCREW WASHER NUT SCREW WASHER NUT 64 62 63 66 62 52 SCREW WASHER NUT MS20002C6

ASNA0094−6 MS20002C6
MS21250−06016
NSA5057−6 NSA5398−6−16A MS20002C6

ASNA0094−6 MS20002C6 (1) (2) (1) (2) (4) (2) (1) (2) (6) (2) (6) (2) (88) (9) (88) (9) (61) (62) (63) (61) (62) (63) (64) (62) (63) (64) (62) (63) ITEM
01 9.387 mm (0.369 in) 9.427 mm (0.370 in) 01

01

01

01

01 02

9.387 mm (0.369 in) 9.427 mm (0.370 in)

9.387 mm (0.369 in) 9.427 mm (0.370 in)

7.815 mm (0.307 in) 7.849 mm (0.309 in) 02

02

02

02

02 REMARKS
STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE
STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE
STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE
01 02 01 02
01 02

01 02

01 02

01 02 9.886 mm (0.389 in) 9.925 mm (0.390 in)

8.211 mm (0.323 in) 8.245 mm (0.324 in) 9.490 mm (0.373 in) 9.530 mm (0.377 in)

9.886 mm (0.389 in) 9.925 mm (0.390 in)

9.886 mm (0.389 in) 9.925 mm (0.390 in) 7.900 mm (0.311 in) 7.940 mm (0.312 in) 9.490 mm (0.373 in) 9.530 mm (0.377 in)

9.490 mm (0.373 in) 9.530 mm (0.377 in)

N HEAD ON THE VISIBLE SIDE
**NOTE:** DEPENDING ON INSPECTION RESULT 01 02 INSTALL THE FASTENERS WITH MAT. No 09−013 (WET ASSEMBLY) 9.490 mm (0.373 in) 9.530 mm (0.377 in)

9.490 mm (0.373 in) 9.530 mm (0.377 in) STANDARD FASTENER IN TRANSITION FIT 9.490 mm (0.373 in) 9.530 mm (0.377 in)

STANDARD FASTENER IN TRANSITION FIT 9.490 mm (0.373 in) 9.530 mm (0.377 in) IN TRANSITION FIT FIRST OVERSIZE 9.886 mm (0.389 in) 9.925 mm (0.390 in)

IN TRANSITION FIT FIRST OVERSIZE 9.886 mm (0.389 in) 9.925 mm (0.390 in) STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE

G_SB_573115_5_CAAC_02_08 Figure A-FCAAC - Sheet 02 Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 502 5

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

# @A330 SERVICE BULLETIN

**CONF 004 FR47

FR40

FR40 

### B
**B** 

## A

**B** LH SIDE SHOWN RH SIDE SYMMETRICAL 

### A − Z141 Z142

STGR38

STGR39

STGR40 STGR37 H263 H262 H261

H14 H22 H21 H13 H12

VIEW LOOKING AFT

H23 H24 CENTER WING BOX LOWER PANEL REFERENCE

**NOTE:** AREA HOLE NUMBER 12, 13, 14, 21, 22, 23, 24, B 261, 262, 263

G_SB_573115_5_CAAD_01_03 Figure A-FCAAD - Sheet 01 Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 503 5

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

# @A330 SERVICE BULLETIN

**CONF 004

HOLE SYMBOL PN DESCRIPTION FINAL HOLE DIAMETER MIN MAX

9.886 mm (0.389 in) 9.925 mm (0.390 in) EN6115V6−16 SCREW ASNA2531−6 NUT EN6115V6X16 SCREW NUT N 1 2 3 2 EXISTING HOLE DIAMETER MIN MAX

9.387 mm (0.369 in) 9.427 mm (0.370 in)

EN6115V6−18 SCREW NUT EN6115V6X18 SCREW NUT N 4 2 5 2 EN6115V6−20 SCREW NUT EN6115V6X20 SCREW NUT N 6 2 7 2

NSA5399−6−23A SCREW ASNA2394EW6 WASHER NSA5372EW616B

N ASNA0094−6 84 58 51 52 85 82 9.886 mm (0.389 in) 9.925 mm (0.390 in) 9.387 mm (0.369 in) 9.427 mm (0.370 in)

9.886 mm (0.389 in) 9.925 mm (0.390 in) 9.387 mm (0.369 in) 9.427 mm (0.370 in) ASNA2531−6
ASNA2531−6
ASNA2531−6
ASNA2531−6
ASNA2531−6 EN6115−5X18 SCREW NSA5368PD516B WASHER NSA5050−5 NUT N EN6115−5Y18 91 67 83 57 67 83 SCREW WASHER NUT NSA5368PD516B NSA5050−5 8.692mm (0.342 in) 8.732 mm (0.343 in) 8.211 mm (0.323 in) 8.245 mm (0.328 in) 8.296 mm (0.326 in) 8.335 mm (0.324 in)

80 90 WASHER NUT SCREW WASHER WASHER NUT MS21250−07023 ASNA2394EW7 NSA5372EW716B NSA5057−7 9.490 mm (0.374 in) 9.530 mm (0.375 in) (1) (2) (1) (2) (4) (2) (1) (2) (6) (2) (6) (2) (91) (67) (83) (91) (67) (83) (84) (58) (51) (52) (84) (58) (51) (52) ITEM
01

01

01

01

01

01 02

02

02

02

02

02 REMARKS
STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE

NEXT NOMINAL STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE
STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE

SECOND OVERSIZE

IN TRANSITION FIT SECOND OVERSIZE

IN TRANSITION FIT 01 02

01 02

01 02

01 02 N HEAD ON THE VISIBLE SIDE
**NOTE:** DEPENDING ON INSPECTION RESULT 01 02 INSTALL THE FASTENERS WITH MAT. No 09−013 (WET ASSEMBLY) 9.490 mm (0.374 in) 9.530 mm (0.375 in)

9.490 mm (0.374 in) 9.530 mm (0.375 in)

10.282 mm (0.404 in) 10.321 mm (0.406 in) 10.282 mm (0.404 in) 10.321 mm (0.443 in)

11.080 mm (0.436 in) 11.120 mm (0.437 in)

G_SB_573115_5_CAAD_02_06 Figure A-FCAAD - Sheet 02 Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 504 5

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

# @A330 SERVICE BULLETIN

**CONF 004

HOLE SYMBOL PN DESCRIPTION FINAL HOLE DIAMETER MIN MAX EXISTING HOLE DIAMETER MIN MAX

N SCREW ASNA2394EW6 WASHER 86 58 51
87 82 80 SCREW WASHER ASNA2394EW7 MS21250−07025 NSA5399−6−25A (86) (58) ITEM

(51) (86) (58) (51) REMARKS

NEXT NOMINAL IN TRANSITION FIT SECOND OVERSIZE

IN TRANSITION FIT 01 02

01 02

N HEAD ON THE VISIBLE SIDE
**NOTE:** DEPENDING ON INSPECTION RESULT 01 02 INSTALL THE FASTENERS WITH MAT. No 09−013 (WET ASSEMBLY) 11.080 mm (0.436 in) 11.120 mm (0.437 in) 10.282 mm (0.404 in) 10.321 mm (0.406 in) 10.282 mm (0.404 in) 10.321 mm (0.406 in) ASNA0094−6 NUT 52

90 NUT NSA5057−7 (52)

(52) NSA5372EW616B WASHER

NSA5372EW716B WASHER

G_SB_573115_5_CAAD_03_01 Figure A-FCAAD - Sheet 03 Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 505 5

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

# @A330 SERVICE BULLETIN

**CONF 005 thru 007 FR47

FR40

FR40 

### B
**B** 

## A

**B** LH SIDE SHOWN RH SIDE SYMMETRICAL 

### A − Z141 Z142

STGR38

STGR39

STGR40 STGR37 H263 H262 H261

H14 H22 H21 H13 H12

VIEW LOOKING AFT

H23 H24 CENTER WING BOX LOWER PANEL REFERENCE

**NOTE:** AREA HOLE NUMBER 12, 13, 14, 21, 22, 23, 24, B 261, 262, 263

G_SB_573115_5_CAAF_01_03 Figure A-FCAAF - Sheet 01 Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 506 5

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

# @A330 SERVICE BULLETIN

**CONF 005 thru 007

HOLE SYMBOL PN DESCRIPTION FINAL HOLE DIAMETER MIN MAX

9.886 mm (0.389 in) 9.925 mm (0.390 in) EN6115V6−16 SCREW ASNA2531−6 NUT EN6115V6X16 SCREW NUT N 1 2 3 2 EXISTING HOLE DIAMETER MIN MAX

9.387 mm (0.369 in) 9.427 mm (0.370 in)

EN6115V6−19 SCREW NUT EN6115V6X19 SCREW NUT N 91 2 92 2 EN6115V6−22 SCREW NUT EN6115V6X22 SCREW NUT N 93 2 94 2 EN6115V6−24 SCREW ASNA2531−6 NUT EN6115V6X24 SCREW NUT N ASNA2531−6 75 2 76 2

N 9.886 mm (0.389 in) 9.925 mm (0.390 in) 9.387 mm (0.369 in) 9.427 mm (0.370 in)

9.886 mm (0.389 in) 9.925 mm (0.390 in) 9.387 mm (0.369 in) 9.427 mm (0.370 in) ASNA2531−6
ASNA2531−6
ASNA2531−6
ASNA2531−6
ASNA2531−6

9.886 mm (0.389 in) 9.925 mm (0.390 in) SCREW WASHER NUT 61 62 63 65 62 52 SCREW WASHER NUT MS21250−06018
NSA5057−6 NSA5398−6−18A MS20002C6

ASNA0094−6 MS20002C6 9.490 mm (0.373 in) 9.530 mm (0.377 in) 9.490 mm (0.373 in) 9.530 mm (0.377 in) 8.296 mm (0.327 in) 8.335 mm (0.328 in) EN6115V5−20 SCREW ASNA2531−5 NUT EN6115V5X20 SCREW NUT N ASNA2531−5 73 9 74 9 7.815 mm (0.308 in) 7.849 mm (0.309 in) 9.886 mm (0.389 in) 9.925 mm (0.390 in) 9.387 mm (0.369 in) 9.427 mm (0.370 in)

7.900 mm (0.311 in) 7.940 mm (0.312 in) (1) (2) (1) (2) (91) (2) (92) (2) (93) (2) (93) (2) (75) (2) (75) (2) (73) (9) (73) (9) (61) (62) (63) (61) ITEM

(62) (63) 01

01

01

01

01

01 02

02

02

02

02

02 REMARKS
STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE
STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE
STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE

N HEAD ON THE VISIBLE SIDE
**NOTE:** DEPENDING ON INSPECTION RESULT 01 02 INSTALL THE FASTENERS WITH MAT. No 09−013 (WET ASSEMBLY) 01 02 01 02 01 02 01 02
01 02

01 02 STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE
STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE

STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE 9.490 mm (0.373 in) 9.530 mm (0.377 in)

9.490 mm (0.373 in) 9.530 mm (0.377 in)

9.490 mm (0.373 in) 9.530 mm (0.377 in)

9.490 mm (0.373 in) 9.530 mm (0.377 in)

G_SB_573115_5_CAAF_02_06 Figure A-FCAAF - Sheet 02 Removal/Installation of the Fasteners of the Area B of the Frame 40, LH and RH Sides

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 507 5

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

# @A330 SERVICE BULLETIN

**CONF ALL



### A − Z141 Z142

FR47

FR40



### B

**B** 

## A

G_SB_573115_5_CBAA_01_01 Figure A-FCBAA - Sheet 01 Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 508 5

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

# @A330 SERVICE BULLETIN

**CONF ALL

FR40 

## B LH SIDE SHOWN RH SIDE SYMMETRICAL STGR38

STGR39

STGR40 STGR37 H263 H260 H262 H261

H14 H22 H21 H13 H12

VIEW LOOKING AFT **NOTE:**

DO A ROTOTEST INSPECTION OF THE HOLE OF THE AREA A AS PER NTM TASK 51−10−01 DO A ROTOTEST INSPECTION OF THE HOLES OF THE AREA B AS PER NTM TASK 51−10−01 H23 H24 CENTER WING BOX LOWER PANEL REFERENCE

AREA HOLE NUMBER 12, 13, 14, 21, 22, 23, 24, 261, 262, 263 B 260 A

G_SB_573115_5_CBAA_02_05 Figure A-FCBAA - Sheet 02 Rototest Inspection of the Fastener Hole of the Area A and Area B of the Frame 40, LH and RH Sides DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 509 5

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

# @A330 SERVICE BULLETIN

**CONF 001 thru 006
FR47

FR40

FR40 

### B
**B** 

## A

**B** LH SIDE SHOWN RH SIDE SYMMETRICAL 

### A − Z141 Z142

STGR38

STGR39

STGR40 STGR37 H260

VIEW LOOKING AFT HOLE SYMBOL PN DESCRIPTION FINAL HOLE DIAMETER MIN MAX

9.886 mm (0.389 in) 9.925 mm (0.390 in) EN6115V6−16 SCREW ASNA2531−6 NUT EN6115V6X16 SCREW NUT N 1 2 3 2 EXISTING HOLE DIAMETER MIN MAX

9.387 mm (0.369 in) 9.427 mm (0.370 in) ASNA2531−6 (1) (2) (1) (2)

ITEM
01

01 02

02 REMARKS
STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE N HEAD ON THE VISIBLE SIDE

DEPENDING ON INSPECTION RESULT 01 02 INSTALL THE FASTENERS WITH MAT. No 09−013 (WET ASSEMBLY)

9.490 mm (0.373 in) 9.530 mm (0.377 in) CENTER WING BOX LOWER PANEL REFERENCE **NOTE:** AREA HOLE NUMBER 260 A

G_SB_573115_5_CCAA_01_05 Figure A-FCCAA - Sheet 01 Removal/Installation of the Fastener Pre Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 510 5

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

# @A330 SERVICE BULLETIN

**CONF 001 thru 006
FR47

FR40

FR40 

### B
**B** 

## A

**B** LH SIDE SHOWN RH SIDE SYMMETRICAL 

### A − Z141 Z142

STGR38

STGR39

STGR40 STGR37 H260

VIEW LOOKING AFT HOLE SYMBOL PN DESCRIPTION FINAL HOLE DIAMETER MIN MAX

11.476 mm (0.452 in) 11.515 mm (0.453 in) EN6115V7−16 SCREW ASNA2531−7 NUT EN6115V7X16 SCREW NUT N 94 78 79 78 EXISTING HOLE DIAMETER MIN MAX

10.972 mm (0.432 in) 11.007 mm (0.433in) ASNA2531−7 (94) (78) (94) (78) ITEM
01

01 02

02 REMARKS
STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE 11.080 mm (0.436 in) 11.120 mm (0.437 in) CENTER WING BOX LOWER PANEL REFERENCE N HEAD ON THE VISIBLE SIDE

DEPENDING ON INSPECTION RESULT 01 02 INSTALL THE FASTENERS WITH MAT. No 09−013 (WET ASSEMBLY) **NOTE:**

AREA HOLE NUMBER 260 A

G_SB_573115_5_CDAA_01_05 Figure A-FCDAA - Sheet 01 Removal/Installation of the Fastener Post Service Bulletin A330-57-3083 of the Area A of the Frame 40, LH and RH Sides DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 511 5

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

# @A330 SERVICE BULLETIN

**CONF 007
FR47

FR40

FR40 

### B
**B** 

## A

**B** LH SIDE SHOWN RH SIDE SYMMETRICAL 

### A − Z141 Z142

STGR38

STGR39

STGR40 STGR37 H260

VIEW LOOKING AFT HOLE SYMBOL PN DESCRIPTION FINAL HOLE DIAMETER MIN MAX

9.886 mm (0.389 in) 9.925 mm (0.390 in) EN6115V6−16 SCREW ASNA2531−6 NUT EN6115V6X16 SCREW NUT N 1 2 3 2 EXISTING HOLE DIAMETER MIN MAX

9.387 mm (0.369 in) 9.427 mm (0.370 in) ASNA2531−6 (1) (2) (1) (2)

ITEM
01

01 02

02 REMARKS
STANDARD FASTENER

IN TRANSITION FIT IN TRANSITION FIT

FIRST OVERSIZE N HEAD ON THE VISIBLE SIDE

DEPENDING ON INSPECTION RESULT 01 02 INSTALL THE FASTENERS WITH MAT. No 09−013 (WET ASSEMBLY)

9.490 mm (0.373 in) 9.530 mm (0.377 in) CENTER WING BOX LOWER PANEL REFERENCE **NOTE:** AREA HOLE NUMBER 260 A

G_SB_573115_5_CEAA_01_03 Figure A-FCEAA - Sheet 01 Removal/Installation of the Fastener of the Area A of the Frame 40, LH and RH Sides DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 512 5

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

# @A330 SERVICE BULLETIN

**CONF 001 thru 006

QUESTION
ACTION FINDING AT THE THRESHOLD GIVEN IN THE TABLES 1 AND 2 OF THE PLANNING INFORMATION PARAGRAPH E.(2). AND (REFER TO SUBTASKS 573115−832−002 AND 573115−832−008 FOR AREA B)

CRACKS YES NO

INSTALL NEW SAME FASTENERS OF THE (REFER TO SUBTASKS 573115−832−010 AND 573115−832−011) DO A ROTOTEST INSPECTION OF THE FASTENER HOLES OF THE AREA B OF THE FRAME 40, LH AND RH SIDES AT THE THRESHOLD GIVEN IN THE TABLE 5 OF THE PLANNING INFORMATION PARAGRAPH E.(2).

FOUND

(REFER TO SUBTASK 573115−832−010

OF THE FASTENER HOLES OF THE AREA B OF THE FRAME 40, LH AND RH SIDES SEE FIG. A−FFAAA SHEET 03 SEE FIG. A−FFAAA SHEET 03 SEE FIG. A−FFAAA SHEET 02

AREA B IN TRANSITION FIT, LH AND

REPEAT THE ROTOTEST INSPECTION (REFER TO SUBTASKS 573115−832−001 AND 573115−832−007 FOR AREA A) DO A SPECIAL DETAILED INSPECTION OF THE FASTENER HOLES OF THE AREA A AND B OF THE FRAME 40, LH AND RH SIDES

AND/OR 573115−832−011) AT THE INTERVAL GIVEN IN THE TABLE 5 OF THE PLANNING INFORMATION PARAGRAPH E.(2). RH SIDES BEFORE NEXT FLIGHT (REFER TO SUBTASK 573115−833−022 AND/OR 573115−833−013) AREA A HOLE 260 AREA B HOLES 12, 13, 14, 21, 22, 23, 24, 261, 262 AND 263

G_SB_573115_5_FAAA_01_04 Figure A-FFAAA - Sheet 01 Flow Chart DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 513 5

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

# @A330 SERVICE BULLETIN

**CONF 001 thru 006

QUESTION
ACTION FINDING CRACKS OR

(REFER TO SUBTASKS 573115−832−003 AND 573115−832−009) SB No. A330−57−3083 OF THE FASTENER HOLE OF THE AREA A OF THE FRAME 40, LH AND RH SIDES AT THE THRESHOLD GIVEN IN THE TABLE 3 OF THE PLANNING INFORMATION PARAGRAPH E.(2).

FOUND A330−57−3083 NO YES ACCOMPLISHED SEE FIG. A−FFAAA SHEET 01

SB No.

CRACKS YES NO (REFER TO SUBTASK 573115−832−004 AND/OR 573115−832−005) AT THE THRESHOLD GIVEN IN THE TABLE 4 OF THE PLANNING INFORMATION PARAGRAPH E.(2).

FOUND

SEE FIG. A−FFAAA SHEET 03 SEE FIG. A−FFAAA SHEET 03

OR

(REFER TO SUBTASK 573115−832−003 AND/OR 573115−832−009) SB No. A330−57−3083 OF THE FASTENER HOLE OF THE AREA A OF THE FRAME 40, LH AND RH SIDES AT THE INTERVAL GIVEN IN THE TABLE 3 OF THE PLANNING INFORMATION PARAGRAPH E.(2). APPLY SB No. A330−57−3083

NO YES

SEE FIG. A−FFAAA SHEET 03 (SB No. A330−57−3083 ACCOMPLISHED) SEE FIG. A−FFAAA SHEET 03 (SB No. A330−57−3083 NOT ACCOMPLISHED)

INSTALL NEW SAME FASTENER PRE SB No. A330−57−3083

OF THE AREA A IN TRANSITION FIT, LH AND RH SIDES OF THE AREA A OF THE FRAME 40, LH AND RH SIDES DO A ROTOTEST INSPECTION PRE SB No. A330−57−3083 OF THE FASTENER HOLE DO A ROTOTEST INSPECTION POST

REPEAT THE ROTOTEST INSPECTION PRE (REFER TO SUBTASK 573115−832−004 AND/OR 573115−832−005) SB No. A330−57−3083 OF THE FASTENER HOLE OF THE AREA A OF THE FRAME 40, LH AND RH SIDES AT THE INTERVAL GIVEN IN THE TABLE 4 OF THE PLANNING INFORMATION PARAGRAPH E.(2). INSTALL NEW SAME FASTENER POST SB No. A330−57−3083 OF THE AREA A IN TRANSITION FIT, LH AND RH SIDES

REPEAT THE ROTOTEST INSPECTION POST BEFORE NEXT FLIGHT

**NOTE:** THRESHOLD TO BE COUNTED FROM MSB 57−3083 EMBODIMENT 01 01

BEFORE NEXT FLIGHT (REFER TO SUBTASK 573115−833−001 AND/OR 573115−833−010) BEFORE NEXT FLIGHT (REFER TO SUBTASK 573115−833−002 AND/OR 573115−833−011)

G_SB_573115_5_FAAA_02_04 Figure A-FFAAA - Sheet 02 Flow Chart DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 514 5

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

# @A330 SERVICE BULLETIN

**CONF 001 thru 006

QUESTION
ACTION FINDING CRACKS YES NO FOUND

NO YES SEE FIG. A−FFAAA SHEET 01 AND SHEET 02

INSTALL NEW FASTENER PRE OR POST LH AND RH SIDES BEFORE NEXT FLIGHT (REFER TO SUBTASK 573115−833−004 AND/OR 573115−833−014) OR

SEE FIG. A−FFAAA SHEET 02 (SB No. A330−57−3083 NOT ACCOMPLISHED) SEE FIG. A−FFAAA SHEET 02 (SB No. A330−57−3083

ACCOMPLISHED) SEE FIG. A−FFAAA SHEET 01 CONTACT AIRBUS

A330−57−3083 ACCOMPLISHED SB No. SB No. A330−57−3083 OF THE AREA A (REFER TO SUBTASK 573115−833−005 AND/OR 573115−833−015)

(REFER TO SUBTASK 573115−832−003 SB No. A330−57−3083 OF THE FASTENER HOLE OF THE AREA A OF THE FRAME 40, LH AND RH SIDES REPEAT THE ROTOTEST INSPECTION PRE (REFER TO SUBTASK 573115−832−004 SB No. A330−57−3083 OF THE FASTENER HOLE OF THE AREA A OF THE FRAME 40, LH AND RH SIDES REPEAT THE ROTOTEST INSPECTION POST IN TRANSITION FIT, LH AND RH SIDES BEFORE NEXT FLIGHT (REFER TO SUBTASK 573115−833−007 AND/OR 573115−833−018) OR

(REFER TO SUBTASK 573115−833−008 AND/OR 573115−833−019) CRACKS YES NO FOUND

INSTALL NEW FASTENERS OF THE AREA B LH AND RH SIDES BEFORE NEXT FLIGHT (REFER TO SUBTASK 573115−833−023 AND/OR 573115−833−017)

IN TRANSITION FIT, LH AND RH SIDES BEFORE NEXT FLIGHT (REFER TO SUBTASK 573115−833−024

(REFER TO SUBTASK 573115−832−010 OF THE FASTENER HOLES OF THE AREA B OF THE FRAME 40, LH AND RH SIDES REPEAT THE ROTOTEST INSPECTION BEFORE NEXT FLIGHT

AND/OR 573115−832−009) AT THE INTERVAL GIVEN IN THE TABLE 3 OF THE PLANNING INFORMATION PARAGRAPH E.(2). AND/OR 573115−832−005) AT THE INTERVAL GIVEN IN THE TABLE 4 OF THE PLANNING INFORMATION PARAGRAPH E.(2). CONTACT AIRBUS BEFORE NEXT FLIGHT AND/OR 573115−833−021)

AND/OR 573115−832−011) AT THE INTERVAL GIVEN IN THE TABLE 5 OF THE PLANNING INFORMATION PARAGRAPH E.(2). AREA A HOLE 260 AREA B HOLES 12, 13, 14, 21, 22, 23, 24, 261, 262 AND 263

THE CURRENT HOLE DIAMETER AND DO A ROTOTEST INSPECTION, OVERSIZE THE HOLE OF THE AREA A PRE OR POST SB No. A330−57−3083 TO FIRST OVERSIZE IN COMPARISON WITH CURRENT HOLE DIAMETER AND DO A ROTOTEST INSPECTION, OVERSIZE THE HOLES OF THE AREA B TO FIRST OVERSIZE IN COMPARISON WITH THE

G_SB_573115_5_FAAA_03_06 Figure A-FFAAA - Sheet 03 Flow Chart DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 515 5

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

# @A330 SERVICE BULLETIN

**CONF 007

QUESTION
ACTION FINDING AT THE THRESHOLD GIVEN IN THE TABLES 1 AND 2 OF THE PLANNING INFORMATION PARAGRAPH E.(2). DO A SPECIAL DETAILED INSPECTION OF THE FASTENER HOLES OF THE AREA A AND B OF THE FRAME 40, LH AND RH SIDES

CRACKS YES NO

INSTALL NEW SAME FASTENERS OF THE AREA B (REFER TO SUBTASKS 573115−832−010 AND 573115−832−011) AT THE THRESHOLD GIVEN IN THE TABLE 4 OF THE PLANNING INFORMATION PARAGRAPH E.(2).

FOUND

SEE FIG. A−FFAAB SHEET 02 SEE FIG. A−FFAAB SHEET 02 (AREA B)

IN TRANSITION FIT, LH AND RH SIDES BEFORE NEXT FLIGHT (REFER TO SUBTASK 573115−833−022 AND/OR 573115−833−013) CRACKS YES NO FOUND

SEE FIG. A−FFAAB SHEET 02 SEE FIG. A−FFAAB SHEET 02 (AREA A) DO A ROTOTEST INSPECTION OF THE FASTENER HOLES OF THE AREA B OF THE FRAME 40, LH AND RH SIDES (REFER TO SUBTASKS 573115−832−006 AND 573115−832−012) OF THE FASTENER HOLE OF THE AREA A OF THE FRAME 40, LH AND RH SIDES AT THE THRESHOLD GIVEN IN THE TABLE 3 OF THE PLANNING INFORMATION PARAGRAPH E.(2).

(REFER TO SUBTASK 573115−832−006 AND/OR 573115−832−012) OF THE FASTENER HOLE OF THE AREA A OF THE FRAME 40, LH AND RH SIDES AT THE INTERVAL GIVEN IN THE TABLE 3 OF THE PLANNING INFORMATION PARAGRAPH E.(2). INSTALL NEW SAME FASTENER OF THE AREA A IN TRANSITION FIT, LH AND RH SIDES BEFORE NEXT FLIGHT (REFER TO SUBTASK 573115−833−003 AND/OR 573115−833−012) DO A ROTOTEST INSPECTION

REPEAT THE ROTOTEST INSPECTION (REFER TO SUBTASK 573115−832−010 AND/OR 573115−832−011) OF THE FASTENER HOLES OF THE AREA B OF THE FRAME 40, LH AND RH SIDES AT THE INTERVAL GIVEN IN THE TABLE 4 OF THE PLANNING INFORMATION PARAGRAPH E.(2). REPEAT THE ROTOTEST INSPECTION (REFER TO SUBTASKS 573115−832−001 AND 573115−832−007 FOR AREA A) AND (REFER TO SUBTASKS 573115−832−002 AND 573115−832−008 FOR AREA B)

AREA A HOLE 260 AREA B HOLES 12, 13, 14, 21, 22, 23, 24, 261, 262 AND 263

G_SB_573115_5_FAAB_01_04 Figure A-FFAAB - Sheet 01 Flow Chart DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 516 5

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# @A330 SERVICE BULLETIN

**CONF 007

QUESTION
ACTION FINDING CRACKS YES NO FOUND SEE FIG. A−FFAAB SHEET 01

INSTALL NEW FASTENER HOLE DIAMETER AND DO A ROTOTEST INSPECTION, OVERSIZE THE HOLE OF THE AREA A TO FIRST OVERSIZE IN COMPARISON WITH THE CURRENT

SEE FIG. A−FFAAB SHEET 01 SEE FIG. A−FFAAB SHEET 01 CONTACT AIRBUS OF THE AREA A IN TRANSITION FIT,

(REFER TO SUBTASK 573115−832−006 OF THE FASTENERS HOLE OF THE AREA A OF THE FRAME 40, LH AND RH SIDES REPEAT THE ROTOTEST INSPECTION LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573115−833−009 CRACKS YES NO FOUND

INSTALL NEW FASTENERS OF THE HOLE DIAMETER AND DO A ROTOTEST INSPECTION, OVERSIZE THE HOLES OF THE AREA B TO FIRST OVERSIZE IN COMPARISON WITH THE CURRENT LH AND RH SIDES BEFORE NEXT FLIGHT

AREA B IN TRANSITION FIT, LH AND RH SIDES BEFORE NEXT FLIGHT

(REFER TO SUBTASK 573115−832−010 OF THE FASTENER HOLES OF THE AREA B OF THE FRAME 40, LH AND RH SIDES REPEAT THE ROTOTEST INSPECTION BEFORE NEXT FLIGHT
AND/OR 573115−833−020)

AND/OR 573115−832−012) AT THE INTERVAL GIVEN IN THE TABLE 3 OF THE PLANNING INFORMATION PARAGRAPH E.(2). CONTACT AIRBUS BEFORE NEXT FLIGHT

AND/OR 573115−832−011) AT THE INTERVAL GIVEN IN THE TABLE 4 OF THE PLANNING INFORMATION PARAGRAPH E.(2). (REFER TO SUBTASK 573115−833−024 AND/OR 573115−833−021) AREA A HOLE 260 AREA B HOLES 12, 13, 14, 21, 22, 23, 24, 261, 262 AND 263

LH AND RH SIDES BEFORE NEXT FLIGHT (REFER TO SUBTASK 573115−833−023 AND/OR 573115−833−017) (REFER TO SUBTASK 573115−833−006 AND/OR 573115−833−016)

G_SB_573115_5_FAAB_02_05 Figure A-FFAAB - Sheet 02 Flow Chart DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 517 5

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# @A330 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 518 5

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# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report **CONF ALL (1) Inspection report (a) The results of the inspection, including no findings, replacement or actions to be done, must be forwarded to AIRBUSSEES1, on theattached inspection report sheet.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 1 5

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# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF 001 thru 004 **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A330−57−3115

DATE OF INSPECTION : RETURN TO :

INSPECTION METHOD :

LH SIDE ROTOTEST

CRACKS
YES INSPECTION

CRACKS AFTER OVERSIZE NO H12 CRACKS CRACKS AFTER OVERSIZE YES NO YES NO YES NO RH SIDE

YES NO H13 YES NO YES NO YES NO
YES NO H14 YES NO YES NO YES NO
YES NO H21 YES NO YES NO YES NO
YES NO H22 YES NO YES NO YES NO
YES NO H23 YES NO YES NO YES NO
YES NO H24 YES NO YES NO YES NO
YES NO H260 YES NO YES NO YES NO
YES NO H261 YES NO YES NO YES NO
YES NO H262 YES NO YES NO YES NO
YES NO H263 YES NO YES NO YES NO AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR) 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14 E−mail: Structure.sbinspectionresult@airbus.com

G_SB_573115_5_RAAA_01_01 Figure A-FRAAA - Sheet 01 Inspection Report DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 2 5

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# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF 001 thru 004 **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A330−57−3115

DATE OF INSPECTION : RETURN TO :

INSPECTION METHOD :

LH SIDE ROTOTEST INSPECTION

H12 RH SIDE

H13
H14
H21
H22
H23
H24
H260
H261
H262
H263 AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR) 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14 E−mail: Structure.sbinspectionresult@airbus.com

mm FINAL DIAMETER in INITIAL DIAMETER FINAL DIAMETER INITIAL DIAMETER

mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

G_SB_573115_5_RAAA_02_01 Figure A-FRAAA - Sheet 02 Inspection Report DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 3 5

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# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF 001 thru 004 FR47

FR40

FR40



### B
**B** 

## A

**B** LH SIDE SHOWN RH SIDE SYMMETRICAL 

### A − Z141 Z142

STGR38

STGR39

STGR40 STGR37 H263 H260 H262 H261

H23 H14 H24H22 H21 H13 H12

VIEW LOOKING AFT CENTER WING BOX LOWER PANEL REFERENCE

G_SB_573115_5_RAAA_03_00 Figure A-FRAAA - Sheet 03 Inspection Report DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 4 5

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

# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF 001 thru 004

FR40 FRONT FITTING (8.5 mm) (0.335 in) FR40 REAR FITTING (9.2 mm) (0.362 in) 

### HOLE 260

HOLE 13

FR40 FRONT FITTING (8 mm) (0.315 in) FR40 SPAR WEB (4 mm) (0.157 in) FR40 REAR

FITTING (5 mm) (0.197 in) **FWD**

**FWD**

**NOTE:** THESE THICKNESSES ARE THEORETICAL CWB LOWER ANGLE (6.5 mm) (0.256 in) FR40 FRONT FITTING (8.5 mm) (0.335 in) FR40 REAR FITTING (9.2 mm) (0.362 in) 

### HOLE 12 & 14

**FWD** CWB LOWER ANGLE (6 mm) (0.236 in)

CWB LOWER ANGLE (6 mm) (0.236 in)

G_SB_573115_5_RAAA_04_01 Figure A-FRAAA - Sheet 04 Inspection Report DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 5 5

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

# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF 001 thru 004

FR40 FRONT FITTING (8.5 mm) (0.335 in) FR40 REAR FITTING (9.2 mm) (0.362 in)

FR40 REAR

FITTING (9.2 mm) (0.362 in) 

### HOLE 21, 22, 23 & 24

HOLE 262 HOLE 263 **FWD**

**FWD**

**NOTE:** THESE THICKNESSES ARE THEORETICAL CWB GUSSET

(5 mm) (0.197 in)

FR40 FRONT FITTING (8.5 mm) (0.335 in) CWB LOWER ANGLE (6.5 mm) (0.256 in) CWB GUSSET (8 mm TO 8.5 mm) FR40 REAR FITTING (9.2 mm) (0.362 in) CWB LOWER ANGLE (6.5 mm) (0.256 in) 

### HOLE 261

CWB LOWER ANGLE (6 mm) (0.236 in) FR40 SPAR (4 mm) (0.157 in) FR40 REAR

FITTING (5 mm) (0.197 in) FR40 POST Y1959 (6 mm) (0.236 in)

**FWD**

**FWD** (0.315 in to 0.334 in) CWB GUSSET (11 mm TO

11.5 mm) (0.433 in to

0.453 in) SHIM (6.5 mm) (0.256 in) CWB RIB

Y1959 (10 mm) (0.394 in)

G_SB_573115_5_RAAA_05_01 Figure A-FRAAA - Sheet 05 Inspection Report DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 6 5

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# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF 005 thru 007 **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A330−57−3115

DATE OF INSPECTION : RETURN TO :

INSPECTION METHOD :

LH SIDE ROTOTEST

CRACKS
YES INSPECTION

CRACKS AFTER OVERSIZE NO H12 CRACKS CRACKS AFTER OVERSIZE YES NO YES NO YES NO RH SIDE

YES NO H13 YES NO YES NO YES NO
YES NO H14 YES NO YES NO YES NO
YES NO H21 YES NO YES NO YES NO
YES NO H22 YES NO YES NO YES NO
YES NO H23 YES NO YES NO YES NO
YES NO H24 YES NO YES NO YES NO
YES NO H260 YES NO YES NO YES NO
YES NO H261 YES NO YES NO YES NO
YES NO H262 YES NO YES NO YES NO
YES NO H263 YES NO YES NO YES NO AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR) 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14 E−mail: Structure.sbinspectionresult@airbus.com

G_SB_573115_5_RAAB_01_00 Figure A-FRAAB - Sheet 01 Inspection Report DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 7 5

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# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF 005 thru 007 **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A330−57−3115

DATE OF INSPECTION : RETURN TO :

INSPECTION METHOD :

LH SIDE ROTOTEST INSPECTION

H12 RH SIDE

H13
H14
H21
H22
H23
H24
H260
H261
H262
H263 AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER WING BOX (WB/LR) 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14 E−mail: Structure.sbinspectionresult@airbus.com

mm FINAL DIAMETER in INITIAL DIAMETER FINAL DIAMETER INITIAL DIAMETER

mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

mm in mm in mm in mm in

G_SB_573115_5_RAAB_02_00 Figure A-FRAAB - Sheet 02 Inspection Report DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 8 5

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# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF 005 thru 007 FR47

FR40

FR40



### B
**B** 

## A

**B** LH SIDE SHOWN RH SIDE SYMMETRICAL 

### A − Z141 Z142

STGR38

STGR39

STGR40 STGR37 H263 H260 H262 H261

H23 H14 H21 H13 H12

VIEW LOOKING AFT H24H22
CENTER WING BOX LOWER PANEL REFERENCE

G_SB_573115_5_RAAB_03_01 Figure A-FRAAB - Sheet 03 Inspection Report DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 9 5

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

# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF 005 thru 007

FR40 FRONT FITTING (8.5 mm) (0.335 in) FR40 REAR FITTING (9.2 mm) (0.362 in) 

### HOLE 260

HOLE 13

FR40 FRONT FITTING (8 mm) (0.315 in) FR40 SPAR WEB (4 mm) (0.157 in) FR40 REAR

FITTING (5 mm) (0.197 in) **FWD**

**FWD**

**NOTE:** THESE THICKNESSES ARE THEORETICAL CWB LOWER ANGLE (6.5 mm) (0.256 in) FR40 FRONT FITTING (8.5 mm) (0.335 in) FR40 REAR FITTING (9.2 mm) (0.362 in) 

### HOLE 12 & 14

**FWD** CWB LOWER ANGLE (6 mm) (0.236 in)

CWB LOWER ANGLE (6 mm) (0.236 in)

G_SB_573115_5_RAAB_04_01 Figure A-FRAAB - Sheet 04 Inspection Report DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 10 5

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# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF 005 thru 007 

### HOLE 21, 23 & 24

**NOTE:** THESE THICKNESSES ARE THEORETICAL 

### HOLE 22

CWB LOWER ANGLE (6 mm) (0.236 in) CWB RIB Y1959 (10 mm) (0.394 in) FR40 SPAR (4 mm) (0.157 in) FR40 REAR

FITTING (5 mm) (0.197 in) FR40 POST Y1959 (12 mm) (0.472 in)

**FWD** CWB LOWER ANGLE (6 mm) (0.236 in) CWB RIB Y1959 (10 mm) (0.394 in) FR40 SPAR (4 mm) (0.157 in) FR40 REAR

FITTING (5 mm) (0.197 in) FR40 POST Y1959 (6 mm) (0.236 in)

FR40 FRONT FITTING (6 mm) (0.236 in)

**FWD**

G_SB_573115_5_RAAB_05_01 Figure A-FRAAB - Sheet 05 Inspection Report DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 11 5

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

# @A330 SERVICE BULLETIN Appendix 01 : Inspection Report

**CONF 005 thru 007

FR40 FRONT FITTING (8.5 mm) (0.335 in) FR40 REAR FITTING (9.2 mm) (0.362 in) FR40 REAR FITTING (9.2 mm) (0.362 in) 

### HOLE 262

HOLE 263 **FWD**

**FWD**

**NOTE:** THESE THICKNESSES ARE THEORETICAL FR40 FRONT FITTING (8.5 mm) (0.335 in) CWB LOWER ANGLE (6.5 mm) (0.256 in) CWB GUSSET (8 mm TO

9 mm)

FR40 REAR

FITTING (9.2 mm) (0.362 in) CWB LOWER ANGLE (6.5 mm) (0.256 in) 

### HOLE 261

**FWD** (0.315 in to 0.354 in)

CWB GUSSET (11 mm TO

12 mm) (0.433 in to

0.472 in) CWB GUSSET (12.5 mm TO

13.5 mm) (0.492 in to

0.531 in)

G_SB_573115_5_RAAB_06_01 Figure A-FRAAB - Sheet 06 Inspection Report DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 12 5

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# @A330 SERVICE BULLETIN REPORTING SHEET 

### TITLE: WINGS - CENTER WING BOX - INSPECTION OF FASTENER HOLES AT FRAME 40 VERTICAL WEB ABOVE CENTER WING BOX LOWER PANEL MODIFICATION No.: None Please complete the appropriate item (A or B): A - SB WILL BEembodied 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 BEENembodied 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: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 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.

DATE: Apr 04/13 SERVICE BULLETIN No.: A330-57-3115 REVISION No.: 00 - Apr 04/13 Page: 1 5

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