# @ A330
SERVICE BULLETIN REVISION TRANSMITTAL SHEET

7 DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : 1 of 3 Printed in FRANCE © AIRBUS, 2006 All rights reserved 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 

# MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 32 TITLE : LANDING GEAR - MLG - INSPECTION OF THE MLG RETRACTION ACTUATOR PISTON-ROD MODIFICATION No. : None This page transmits Revision No. 03 of Service Bulletin No. A330-32-3173 ADDITIONAL WORK Additional work is required by this revision for aircraft modified by any previous issue. Do a one-time ultrasonic inspection of the full length of the piston rods. REASON This revision has been issued to inform operators that: — A one-time ultrasonic longitudinal and circumferential inspection on the full piston rod has been added. — Modification Service Bulletin references have been added as a closing action. — Accomplishment timescale has been amended. — The interval for the fluid drainage has been amended. — Operator 79X has been added. Operators 61Y, BWG, DAH, I2L and SSV have been deleted. — Config. 01 has been added. CHANGES SUMMARY : — REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES . Sentence and Note added. EVALUATION TABLE revised. — EFFECTIVITY

# @ A330
SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved . Operators 61Y, BWG, DAH, I2L and SSV deleted. Operator 79X added. NOTE added. — MANPOWER . Config. 01 added. PLANNING INFORMATION : — EFFECTIVITY . 1.A. NOTE added. Operators 61Y, BWG, DAH, I2L and SSV deleted. Operator 79X added. Effectivity updated. Config. 01 added. — REASON — History . 1.C.(1) Sentence and NOTE added. — Objective/Action . 1.C.(2) Sentence updated. — DESCRIPTION . 1.D.(1) Config. 01 added. . 1.D.(1)(e) Paragraph added. — COMPLIANCE — Accomplishment Timescale . 1.E.(2) Sentence amended. . 1.E.(2)(b)1 Paragraph amended. . 1.E.(2)(b)2 NOTE added. . 1.E.(2)(c) Paragraph amended. . 1.E.(2)(c)2 Sentence amended. . 1.E.(2)(d)1 Paragraph amended. . 1.E.(2)(d)2 Paragraph amended. . 1.E.(2)(e) Paragraph added. . 1.E.(2)(e)1 Paragraph added. — MANPOWER . 1.G. Config. 01, one-time ultrasonic inspection added.

2

# @ A330
SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved — REFERENCES . 1.J. Service Bulletin reference added. ACCOMPLISHMENT INSTRUCTIONS : — GENERAL — Preparation . 3.A.(1)(a) Config. 01 added. — INSPECTION . 3.B.(1) Config. 01 added. . 3.B.(1)(d) One-time ultrasonic inspection added. — CLOSE-UP . 3.D.(1) Config. 01 added. FILING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS Revision 01 of this Service Bulletin was issued to add a new AD (CN) No. F-2004-086 (B) to supersede AD (CN) No. F-2003-458 (B) and mandates this Service Bulletin. This is due to the addition of the repetitive 7 day inspection of the complete chromed area of the piston rod. Also the opportunity has been taken to update the aircraft effectivity and clarify the aircraft configurations. Revision 02 of this Service Bulletin was issued to show the changes in the inspection procedures and to include the drainage of water or other fluids from the piston rod. The mandatory accomplishment timescales were also added. REVISION SEQUENCE ORIGINAL : Dec 17/03 REVISION No. : 01 — Jun 16/04 REVISION No. : 02 — May 11/05 REVISION No. : 03 — Mar 13/06

3

# @ A330
SERVICE BULLETIN SUMMARY

7 DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : 1 of 3 Printed in FRANCE © AIRBUS, 2006 All rights reserved 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 

# MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 32 TITLE : LANDING GEAR - MLG - INSPECTION OF THE MLG RETRACTION ACTUATOR PISTON-ROD MODIFICATION No. : None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES A rupture of a Main Landing Gear (MLG) retraction actuator piston rod-end has occurred on an in-service A330 aircraft. This resulted from internal corrosion and circumferential cracking around the painted upper end of the piston rod. A longitudinal crack has also been found on the chromed part of a retraction actuator piston-rod. Investigations indicate that the crack started from a line of corrosion pitting within the piston rod bore. All Operator Telex. (AOT) No. A330-32A3172 was issued to request operators to carry out an ultrasonic inspection of the retraction actuator piston rods that have been in service for more than six years. The Messier Dowty Service Bulletin A33/34-32-222 requires the actions that follow on the MLG retraction actuator piston rods that have been in service for three years or more:- — A visual inspection of the chromed area of the piston rods for cracks. — The draining of water or other fluids from the piston rods which could freeze and cause future cracks. — A repeat ultrasonic longitudinal inspection of the painted upper end of the piston rods for corrosion pitting and/or circumferential cracks. — A one-time ultrasonic longitudinal and circumferential inspection of the full length of the piston rods for corrosion pitting and/or circumferential cracks. This Service Bulletin supersedes AOT A330-32A3172. The accomplishment of this Service Bulletin makes sure that the MLG retraction actuator rod has no cracks and is free of any severe internal corrosion pitting that could cause cracks.

# @ A330
SERVICE BULLETIN SUMMARY

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Original issue of this Service Bulletin was rendered Mandatory by Airworthiness Directive (AD) (Consigne de Navigabilite (CN)) No. F-2003-458 (B). A second in-service piston rod rupture occurred as a result of a line of corrosion pitting within the piston-rod bore along the chromed length. This occurrence led to a revision of the requirement for the inspection of the piston-rods chromed area. Following this second event a new AD (CN) F-2004-086 (B) was issued to supersede AD (CN) No. F-2003-458(B) and to mandate this Service Bulletin at revision 01 and above. A third in-service retraction actuator piston rupture has occurred. As with the first rupture, this failure resulted from internal corrosion and circumferential cracking around the painted upper end of the piston rod. Subsequently, another piston rod has been found in operation with a longitudinal crack in the chromium plated part of the piston rod. Investigations indicate that the crack started from a line of corrosion pitting within the piston rod bore. The accomplishment of Service Bulletin A330-32-3174 or Service Bulletin A330-32-3180 Rev 01 cancels the requirements of this Service Bulletin. NOTE : The accomplishment of Service Bulletin A330-32-3174 is the interim solution for the piston rod actuator. Service Bulletin A330-32-3180 Rev 01 will take the piston rod actuator to Design Service Goal.

EFFECTIVITY This Service Bulletin is applicable to these operators : 79X AAR ACA ACI AFR ALK AUA BMA CAL CPA CRL CRX CYP DAT DLH DRD EDW EEZ EIN ETD EVA FWI GFA GIA GRL HDA IWD IYE KAL LDI LTU LXR MAS MEA MON MSR MYT NVR NWA PAL QAF QFA QTR SAS SEU TAM TCX THA TSC UAE USA VKG NOTE : The modification 52980H15418 is embodied in production on MSN 0644, and subsequent. Aircraft with this modification embodied are not required to embody this Service Bulletin. EVALUATION TABLE COMPLIANCE Mandatory CANCELS INSPECTION SB No AD Yes A/C OPERATION AFFECTED No RELIABILITY AFFECTED Yes PAX COMFORT AFFECTED No COST SAVING No ETOPS AFFECTED No STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED Yes KIT PRICE (USD) No kit

2

# @ A330
SERVICE BULLETIN SUMMARY

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved CONCURRENT REQUIREMENTS None REFERENCES/REPERCUSSIONS TFU : 32.31.46.008 OEB : None AOT : A330-32A3172 SIL : None LIFE LIMIT : None LINE MAINTENANCE AFFECTED : No OTHERS : OIT 999.0129/03/CL, OIT 999.0034/04/CL NATURE OF THE WORK AIRCRAFT : Yes EQUIPMENT : No HARD : No SOFT : No OBRM : No MANPOWER Config. 01

NOTE : * For the inspection manhours, refer to the Messier-Dowty Service Bulletin No. A33/34-32-222. MATERIAL INFORMATION AIRCRAFT DATA None APPENDICES None TOTAL MANHOURS 1.0* ELAPSED TIME (HOURS) 1.0*

3

# @ A330
SERVICE BULLETIN

7 DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : 1 of 18 Printed in FRANCE © AIRBUS, 2006 All rights reserved 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 

# MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 32 TITLE : LANDING GEAR - MLG - INSPECTION OF THE MLG RETRACTION ACTUATOR PISTON-ROD 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 A. EFFECTIVITY (1) Models 330-201 330-202 330-203 330-223 330-243 330-301 330-302 330-303 330-321 330-322 330-323 330-341 330-342 330-343 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN : 0012 0017 0030 0037 0045 0050 0054 0055 0059 0060 0062 0064-0067 0069-0073 0077 0082 0083 0086 0087 0095 0096 0098-0100 0102 0106 0107 0109-0113 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 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

# @ A330
SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 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 NOTE : The modification 52980H15418 is embodied in production on MSN 0644, and subsequent. Aircraft with this modification embodied are not required to embody this Service Bulletin. (b) 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

79X 0305 0308 0312 AAR 0640 ACA 0277 0279 0284 0344 0400 0408 0412 0419 ACI 0507 0510 AFR 0422 0443 0448 0458 0465 0481 0498 0500 0502 0503 0516 0519 0567 0584 ALK 0303 0306 0311 0313 AUA 0181 0195 0223 0317 BMA 0398 0401 0404

CAL 0602 0607 0641 CPA 0012 0017 0071 0083 0099 0102 0109 0113 0118 0121 0155 0244 0386 0389 0393 0418 0420 0421 0423 0439 0539 0548 0565 CRL 0285 0320 CRX 0229 0249 0275 0288 0291 0294 0299 0343 0366 CYP 0505 0526

DAT 0030 0037 0045

2

# @ A330
SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved DLH 0322 0324 0570 0576 0579 0629 0636 0642 DRD 0054 0205 0211 0362 EDW 0369 EEZ 0358 0364 EIN 0055 0059 0070 0086 0269 0330 0397 ETD 0232 0259 0272 0339 0361 EVA 0530 0535 0555 0573 0587 0634 FWI 0240 0253 GFA 0276 0281 0286 0287 0334 0340 GIA 0138 0140 0144 0148 0153 0165 GRL 0230 HDA 0098 0106 0132 0177 0234 0405 0407 0479 0512 0581

IWD 0072 0461 IYE 0625 0632 KAL 0162 0172 0206 0219 0222 0226 0241 0256 0258 0267 0338 0350 0351 0368 0425 0428 0484 0490 0550 LDI 0551 0597 0627 LTU 0082 0120 0127 0171 0403 0432 0444 0454 0469 0476 0493 LXR 0087 0096 MAS 0067 0069 0073 0077 0095 0100 0107 0110 0116 0119 0143 0255 0262 0290 0296 0300 MEA 0527 0529 0532 MON 0261 0265 MSR 0600 0610 MYT 0254 0266 0301 0309 0349 NVR 0353 NWA 0524 0533 0542 0549 0552 0578 0588 0591 0609 0614 0618 0620 0621 0631 0633 PAL 0183 0184 0188 0189 0191 0198 0200 0203 QAF 0487 0605 QFA 0506 0508 0513 0522 0553 0558 0564 0574 0593 0595 0603 QTR 0441 0463 0473 0489 0504 0511 0521 0571 0612 0616 0623 0637 0638 SAS 0496 0497 0515 0568 SEU 0501 0635 OPERATOR MSN

3

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (c) Effectivity by MSN and Kit/Configuration The kits and configurations applicable to these MSNs are given at the end of this list: 0012 0017 0030 0037 0045 0050 0054-0055 0059-0060 0062 0064-0067 0069-0073 0077 0082-0083 0086-0087 0095-0096 0098-0100 0102 0106-0107 0109-0113 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 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

(3) Spares Refer to the Messier-Dowty Service Bulletin No. A33/34-32-222.
B. CONCURRENT REQUIREMENTS None TAM 0238 0247 0466 0472 0477 0486 TCX 0427 0456 THA 0050 0060 0062 0064 0065 0066 0112 0122 0209 0224 0231 0346 TSC 0111 0250 0271 0480 UAE 0248 0251 0283 0293 0295 0314 0316 0326 0328 0345 0348 0365 0372 0382 0384 0392 0396 0409 0437 0451 0452 0455 0462 0491 0494 0509 0518 0525 0536 USA 0315 0323 0333 0337 0342 0370 0375 0380 0388 VKG 0356 0357

KIT No. QTY PER A/C CONFIGURATION 01 OPERATOR MSN

4

# @ A330
SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved C. REASON (1) History A rupture of a MLG retraction actuator piston rod-end has occurred on an in-service A330 aircraft. This resulted from internal corrosion and circumferential cracking around the painted upper end of the piston rod. Longitudinal cracks have also been found on the chromed part of a retraction actuator piston-rod. Investigations indicate that the crack started from a line of corrosion pitting within the piston rod bore. Original issue of this Service Bulletin was rendered Mandatory by AD (CN) No. F-2003-458 (B). A second in-service piston rod rupture occurred as a result of a line of corrosion pitting within the piston-rod bore along the chromed length. This occurrence led to a revision of the requirement for the inspection of the piston-rods chromed area. Following this second event a new AD (CN) F-2004-086 (B) was issued to supersede AD (CN) No. F-2003-458(B) and to mandate this Service Bulletin at revision 01 and above. A third in-service retraction actuator piston rupture has occurred. As with the first rupture, this failure resulted from internal corrosion and circumferential cracking around the painted upper end of the piston rod. Subsequently, another piston rod has been found in operation with a longitudinal crack in the chromium plated part of the piston rod. Investigations indicate that the crack started from a line of corrosion pitting within the piston rod bore. All Operator Telex No. A330-32A3172 has been issued to request operators to carry out an ultrasonic inspection of the retraction actuator piston-rods that have been in service for more than six years. The accomplishment of Service Bulletin A330-32-3174 or Service Bulletin A330-32-3180 Rev 01 cancels the requirements of this Service Bulletin NOTE : The accomplishment of Service Bulletin A330-32-3174 is the interim solution for the piston rod actuator. Service Bulletin A330-32-3180 Rev 01 will take the piston rod actuator to Design Service Goal. (2) Objective/Action This Messier Dowty Service Bulletin A33/34-32-222 requires the actions that follow on the MLG retraction actuator piston rods that have been in service for three years or more:-

5

# @ A330
SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved — A visual inspection of the chromed area of the piston rods for cracks. — The draining of water or other fluids from the piston rods which could freeze and cause future cracks. — A repeat ultrasonic longitudinal inspection of the painted upper end of the piston rods for corrosion pitting and/or circumferential cracks. — A one-time ultrasonic longitudinal and circumferential inspection of the full length of the piston rods for corrosion pitting and/or circumferential cracks. (3) Advantages The accomplishment of this Service Bulletin makes sure that the MLG retraction actuator rod has no cracks and is free of any severe internal corrosion pitting that could cause cracks. This Service Bulletin supersedes AOT A330-32A3172. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to: (1) Config. 01 (a) Get access to the MLG (LH and RH) retraction actuator. NOTE : It is not necessary to raise the aircraft on jacks for this inspection. (b) Do a DVI of the chromed part of the retraction actuator piston rod for cracks in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222. 1 If one or more cracks are found during the DVI, replace the actuator BEFORE THE NEXT FLIGHT. 2 If no cracks are found, do a repeat DVI at the specified intervals given in para 1.E.(2)(b). 3 In the event of findings during the DVI, the piston rod vent hole should be sealed to retain the contents of the internal volume, before the removal and the return of the retraction actuator in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222.

6

# @ A330
SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 4 Report all retraction actuators rejected during the DVI in accordance with the instructions in Messier-Dowty Service Bulletin No. A33/34-32-222. (c) Drain the fluid from the retraction actuator piston rod and seal the vent hole in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222. 1 Repeat the draining and sealing of the vent hole procedure at the specified intervals given in para 1.E.(2)(c). 2 Report the results (regardless of findings) of the retraction actuator draining using the proforma at Appendix C of Messier-Dowty Service Bulletin No. A33/34-32-222. (d) Do an ultrasonic inspection of the inner surface of the upper painted area of the retraction actuator piston rod for indications of cracks in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222 Appendix A. 1 If indications of cracks are found during the ultrasonic inspection: a Replace the retraction actuator WITHIN THE NEXT 10 FLIGHTS, depending on the inspection results in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222 Appendix A.

or b Replace the retraction actuator BEFORE THE NEXT FLIGHT, depending on the inspection results in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222 Appendix A. 2 If no cracks are found, do a repeat ultrasonic inspection at the specified intervals given in para 1.E.(2)(d). 3 If a finding requiring the retraction actuator removal is made during the ultrasonic inspection, and the piston rod has not yet been drained, the piston rod vent hole should be re-sealed to retain the contents of the internal volume, before the removal and the return of the retraction actuator in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222. 4 Report the results of the ultrasonic inspection (regardless of findings) using the proforma at Appendix C of Messier-Dowty Service Bulletin No. A33/34-32-222. (e) Do a one-time ultrasonic inspection of the chromed part of the retraction actuator piston rods within the specified intervals given in Para 1.E.(2)(e), and in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222 Appendix E and F.

7

# @ A330
SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 1 If indications of cracks are found during the ultrasonic inspection: a Replace the retraction actuator WITHIN THE NEXT 10 FLIGHTS, depending on the inspection results in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222 Appendix E and F.

or b Replace the retraction actuator BEFORE THE NEXT FLIGHT, depending on the inspection results in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222 Appendix E and F. 2 If a finding requiring the retraction actuator removal is made during the ultrasonic inspection, and the piston rod has not yet been drained, the piston rod vent hole should be re-sealed to retain the contents of the internal volume, before the removal and the return of the retraction actuator in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222. 3 Report the results of the one-time ultrasonic inspection (regardless of findings) using the proforma at Appendix C of Messier-Dowty Service Bulletin No. A33/34-32-222.
E. COMPLIANCE (1) Classification Mandatory (2) Accomplishment Timescale (a) Accomplishment of this Service Bulletin has been rendered mandatory by the issue of a Airworthiness Directive (AD) published by the DGAC on behalf of the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandatory accomplishment timescale. (b) DVI: - For retraction actuator piston rods identified in accordance with Messier-Dowty Service Bulletin No. A33/34-32-222, when they reach three years use in service at the latest. For aircraft that are close to or have exceeded the three year period, the inspection must be done at 315 FC, 1,750 FH or 5 months whichever occurs first from the issue of this revision. 1 Do a DVI in accordance with Messier-Dowty Service Bulletin No. A33/34-32-222.

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 2 Repeat inspections are required at intervals not exceeding 8 calendar days from the previous DVI, in accordance with Messier-Dowty Service Bulletin No. A33/34-32-222. NOTE : When the one-time ultrasonic inspection has been performed with no findings and the fluid drainage has been performed, as detailed in this Service Bulletin it is no longer necessary to perform the 8 day DVI on the piston rods. (c) Fluid drain and vent hole sealing: - For retraction actuator piston rods identified in accordance with Messier-Dowty Service Bulletin No. A33/34-32-222, when they reach three years use in service at the latest. 1 Do the procedure to drain fluid from the retraction actuator piston rods internal volume and seal the vent hole, in accordance with Messier-Dowty Service Bulletin No. A33/34-32-222. 2 Repeat the procedure at intervals of 1,000 FC or 24 months whichever occurs first in accordance with Messier-Dowty Service Bulletin No. A33/34-32-222. NOTE : When the one-time ultrasonic inspection has been performed with no findings and the fluid drainage has been performed, as detailed in this Service Bulletin it is no longer necessary to perform the 8 day DVI on the piston rods. (d) Ultrasonic inspection of the upper painted area of the piston rods: - For retraction actuator piston rods identified in accordance with Messier-Dowty Service Bulletin No. A33/34-32-222, when they reach three years use in service at the latest. 1 Do an ultrasonic inspection of the painted area at the upper end of the piston rods, in accordance with Messier-Dowty Service Bulletin No. A33/34-32-222. 2 Repeat ultrasonic inspections are required at 250 FC, 1400 FH or 4 months whichever occurs first. (e) One-time ultrasonic inspection of the full piston rod length: - For retraction actuator piston rods identified in accordance with Messier-Dowty Service Bulletin No. A33/34-32-222, when they have reached three years use in service at the latest. 1 Do a one-time ultrasonic inspection of the full length of the piston rods, in accordance with Messier-Dowty Service Bulletin No. A33/34-32-222. For aircraft that are close to or have exceeded the three year period, the inspection must be done at 315 FC, 1,750 FH or 5 months whichever occurs first from the issue of this revision.

9

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved F. APPROVAL Approved under the authority of the EASA 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 labour 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. Config. 01

NOTE : * For the preparation and inspection man-hours refer to the Messier-Dowty Service Bulletin A33/34-32-222. H. WEIGHT AND BALANCE Not changed I. ELECTRICAL LOAD DATA Not changed J. REFERENCES Get access 0.5 Visual inspection * Drain Fluid from Piston Rod * Ultrasonic inspection * One-time ultrasonic inspection * Close up 0.5 TOTAL MANHOURS 1.0 ELAPSED TIME (HOURS) 1.0

Airworthiness Directive (AD) : F-2004-086 (B) Airworthiness Directive (AD) : F-2003-458 (B) Aircraft Maintenance Manual (AMM) : 12-34-24 32-12-00 32-31-46

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved All Operator Telex (AOT) A330-32A3172, Messier-Dowty Service Bulletin (VSB) A33/34-32-222 Operator Information Telex (OIT) 999.0129/03/CL Operator Information Telex (OIT) 999.0034/04/CL Service Bulletin A330-32-3174 Rev 01 Service Bulletin A330-32-3180 Rev 01 K. PUBLICATIONS AFFECTED None L. INTERCHANGEABILITY/MIXABILITY None

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 2. MATERIAL INFORMATION A. MATERIAL — PRICE AND AVAILABILITY (1) Material If replacement parts are required refer to the Messier-Dowty Service Bulletin No. A33/34-32-222. (2) Price and Availability None B. INDUSTRY SUPPORT INFORMATION Refer to the Messier-Dowty Service Bulletin No. A33/34-32-222 for the industry support terms. C. LIST OF COMPONENTS None D. LIST OF MATERIALS — OPERATOR SUPPLIED (1) Consumable Materials

(2) Components None E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR None F. TOOLING — PRICE AND AVAILABILITY Refer to the Messier-Dowty Service Bulletin No. A33/34-32-222. G. SPECIAL TOOLS Refer to the Messier-Dowty Service Bulletin No. A33/34-32-222. DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C INST DISP
Cleaning agent 11-026 As required

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL WARNING : MAKE SURE THAT THE SAFETY DEVICES AND WARNING NOTICES ARE IN POSITION BEFORE YOU START A TASK ON OR NEAR: — THE FLIGHT CONTROLS — THE FLIGHT CONTROL SURFACES — THE LANDING GEAR AND RELATED DOORS — COMPONENTS THAT MOVE. WARNING : MAKE SURE THAT THE GROUND SAFETY LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR. WARNING : MAKE SURE THAT YOU OBEY ALL WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. (1) Preparation (a) Config. 01 1 Make sure that the aircraft is electrically grounded (Refer to AMM 12-34-24 Page block 201). 2 Open and safety the main gear doors (Refer to AMM 32-12-00 Page block 201). 3 Put access steps in position, as required. 4 Make sure that the piston rods of the retraction actuators are clean, use Cleaning agent (Mat No. 11-026) , as required. (2) Standard Practices None B. INSPECTION (1) Config. 01 (a) MLG (LH and RH) Retraction Actuator - DVI of the piston rod: 1 Do a DVI of the chromed part of the fully extended retraction actuator piston rods for cracks, in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222. 2 If one or more cracks are found during the visual inspection, replace the retraction actuator BEFORE THE NEXT FLIGHT (Refer to AMM 32-31-46 Page block 401).

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 3 If no cracks are found, do a repeat visual inspection at the specified intervals given in Para 1.E.(2)(b). 4 If cracks are found, during the visual inspection, the piston rod vent hole should be sealed to retain the contents of the internal volume, before the removal and the return of the retraction actuator in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222. 5 Report all retraction actuators rejected during the visual inspection, in accordance with the instructions in Messier-Dowty Service Bulletin No. A33/34-32-222. (b) MLG (LH and RH) Retraction Actuator - Drain the fluid from the piston rod and seal the vent hole: 1 Drain the fluid from the retraction actuator piston rod and seal the vent hole, in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222. 2 Repeat the draining and sealing of the vent hole procedure at the specified intervals given in Para 1.E.(2)(c). 3 Report the results of the retraction actuator draining using the proforma in Appendix C of Messier-Dowty Service Bulletin No. A33/34-32-222. (c) MLG (LH and RH) Retraction Actuator - Ultrasonic longitudinal inspection of the upper painted area of the piston rod: 1 Do an ultrasonic longitudinal inspection of the upper painted area of the piston rods surface for indications of cracks, in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222. 2 If indications of cracks are found during the ultrasonic longitudinal inspection: a Replace the retraction actuator WITHIN THE NEXT 10 FLIGHTS, depending on the inspection results in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222 (Refer to AMM 32-31-46 Page block 401).

or b Replace the retraction actuator BEFORE THE NEXT FLIGHT, depending on the inspection results in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222 (Refer to AMM 32-31-46 Page block 401). 3 If no cracks are found, do a repeat ultrasonic longitudinal inspection at the specified intervals given in Para 1.E.(2)(d).

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 4 If a finding requiring the retraction actuator removal is made during the ultrasonic inspection, and the piston rod has not yet been drained, the piston rod vent hole should be re-sealed. This will retain the contents of the internal volume, during the removal and the return of the retraction actuator in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222. 5 Report the results of the ultrasonic longitudinal inspection (regardless of findings) using the proforma at Appendix C of Messier-Dowty Service Bulletin No. A33/34-32-222. (d) MLG (LH and RH) Retraction Actuator - One-time ultrasonic longitudinal and circumferential inspection of the full length of the piston rod: 1 Do an ultrasonic longitudinal and circumferential inspection of the chromed area (full length) of the piston rods for indications of cracks, in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222. 2 If indications of cracks are found during the ultrasonic longitudinal and circumferential inspection: a Replace the retraction actuator WITHIN THE NEXT 10 FLIGHTS, depending on the inspection results in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222 (Refer to AMM 32-31-46 Page block 401).

or b Replace the retraction actuator BEFORE THE NEXT FLIGHT, depending on the inspection results in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222 (Refer to AMM 32-31-46 Page block 401). 3 If a finding requiring the retraction actuator removal is made during the ultrasonic inspection, and the piston rod has not yet been drained, the piston rod vent hole should be re-sealed. This will retain the contents of the internal volume, during the removal and the return of the retraction actuator in accordance with the Messier-Dowty Service Bulletin No. A33/34-32-222. 4 Report the results of the ultrasonic longitudinal and circumferential inspection (regardless of findings) using the proforma at Appendix C of Messier-Dowty Service Bulletin No. A33/34-32-222. C. TEST None

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved D. CLOSE UP (1) Config. 01 (a) Make sure that the work area is clean and clear of tools and other items of equipment. (b) Remove the access steps. (c) Close the main gear doors (Refer to AMM 32-12-00 Page block 201). E. DOCUMENTATION Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

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SERVICE BULLETIN REPORTING SHEET

7 DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : 1 of 1 Printed in FRANCE © AIRBUS, 2006 All rights reserved TITLE : LANDING GEAR - MLG - INSPECTION OF THE MLG RETRACTION ACTUATOR PISTON-ROD MODIFICATION No. : None

Please complete the appropriate item (A or B): A - SB WILL BE embodied............. YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:..........................

........................................

........................................ B - SB HAS BEEN embodied on aircraft:.....................

........................................

........................................ Operator comments:..............................

.......................................

....................................... From Airline:................................. Name/Title:.................................. Signature:.............. Date:............. If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service: 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.

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SERVICE BULLETIN QUALITY PERCEPTION FORM

7 DATE : Dec 17/03 SERVICE BULLETIN No. : A330—32—3173 REVISION No. : 03 — Mar 13/06 Page : 1 of 1 Printed in FRANCE © AIRBUS, 2006 All rights reserved 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 4 3 2 1 - Quality rating of the Accomplishment Instructions 4 3 2 1 - Quality rating of the Illustrations 4 3 2 1 - 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 X Mod/Inspection X Manpower Operator Supplied 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 Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.