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SERVICE BULLETIN REVISION TRANSMITTAL SHEET

7 DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : 1 of 2 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. 04 of Service Bulletin No. A340-32-4212 ADDITIONAL WORK None REASON Revision 04 of this Service Bulletin has been issued to remove the detailed tasks in the 'Accomplishment Timescale' paragraph to be replaced by reference to the AD. The opportunity was taken to update the effectivity. CHANGES SUMMARY : — REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES . AD number added to the Evaluation Table. — EFFECTIVITY . Operators AIB, NMB and SWR have been added. Operator CRX has been deleted. PLANNING INFORMATION : — EFFECTIVITY . 1.A. Effectivity revised. Configuration layout applied to Effectivity by MSN and Kit/Configuration. — COMPLIANCE — Accomplishment Timescale

# @ A340
SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved . 1.E.(2) Accomplishment timescale sentence revised. Detailed visual inspection timescales deleted. — REFERENCES . 1.J. ESPM referance added. — GENERAL . 3.A. Electrical wiring CAUTION 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 was due to the addition of the repetitive 7 day inspection of the complete chromed area of the piston rod. Also the opportunity was 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 03 was issued to inform operators that: — A one-time ultrasonic longitudinal and circumferential inspection on the full piston rod was added. — Modification Service Bulletin references were added as a closing action. — Accomplishment timescale was amended. — The interval for the fluid drainage was amended. — Effectivity was revised. — Config. 01 was 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 REVISION No. : 04 — Jun 12/06

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SERVICE BULLETIN SUMMARY

7 DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 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 A340 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. A340-32A4211 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 longitudinal and circumferential cracks. This Service Bulletin supersedes AOT A340-32A4211.

# @ A340
SERVICE BULLETIN SUMMARY

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 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. 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 A340-32-4222 Rev 01 or Service Bulletin A340-32-4213 Rev 01 cancels the requirements of this Service Bulletin. NOTE : The accomplishment of Service Bulletin A330-32-4213 Rev 01 is the interim solution for the piston rod actuator. Service Bulletin A330-32-4222 Rev 01 will take the piston rod actuator to Design Service Goal.

EFFECTIVITY This Service Bulletin is applicable to these operators : 39Z 50Z ACA AEA AFR AIB AJM ALK ARG AUA B3R BWA CAL CES CPA CXN DLH DRD ETD GFA IBE KAC LAN M3R MAU MSR NMB OAL PAL QAF R3L RJA SAA SAS SWR TAP THT THY UAE VIR 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 AIRBUS kit

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SERVICE BULLETIN SUMMARY

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : The modification 52980H15418 is embodied in production on MSN 0643, and subsequent. Aircraft with this modification embodied are not required to embody this Service Bulletin. CONCURRENT REQUIREMENTS None REFERENCES/REPERCUSSIONS TFU : 32.31.46.008 OEB : None AOT : A340-32A4211 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*

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SERVICE BULLETIN

7 DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : 1 of 16 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 340-211 340-212 340-213 340-311 340-312 340-313 (2) Aircraft (a) Effectivity by MSN This Service Bulletin is applicable to aircraft MSN : 0001-0009 0011 0013-0016 0018-0029 0031-0035 0038-0041 0043 0044 0046-0049 0051-0053 0056-0058 0061 0063 0074-0076 0078-0081 0084 0085 0088-0091 0093 0094 0097 0101 0103 0104 0114 0115 0117 0123 0125 0126 0128 0129 0131 0133-0137 0139 0141 0142 0145-0147 0149-0152 0154 0156-0161 0163 0164 0166-0170 0173-0176 0178-0180 0182 0185-0187 0190 0192-0194 0196 0197 0199 0201 0202 0204 0207 0208 0210 0212-0218 0220 0221 0225 0227 0228 0233 0235-0237 0239 0242 0243 0245 0246 0252 0257 0260 0263 0264 0268 0270 0273 0274 0278 0280 0282 0292 0297 0302 0304 0307 0310 0318 0319 0321 0325 0327 0329 0331 0332 0335 0347 0352 0354 0355 0359 0363 0367 0373 0374 0377-0379 0381 0385 0387 0390 0395 0399 0402 0406 0411

# @ A340
SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 0413-0415 0424 0429 0430 0433-0435 0438 0442 0446 0447 0450 0459 0467 0470 0474 0483 0528 0538 0541 0544-0546 0554 0556 0559 0561 0562 0582 0585 0590 0598 (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
39Z 0151 50Z 0009 ACA 0048 0088 0150 0154 0167 0170 0175 0179 0273 0278 AEA 0031 AFR 0005 0029 0049 0078 0084 0168 0174 0186 0207 0210 0237 0245 0246 0260 0307 0310 0319 0373 0377 0399 AIB 0001 AJM 0216 0257 ALK 0032 0033 0034 0367 0374 ARG 0063 0074 0080 0085 AUA 0075 0081 0169 0263 B3R 0046 0204 BWA 0016 0093 CAL 0402 0406 0411 0415 0433 0528 0541 CES 0129 0131 0141 0161 0182 CPA 0123 0126 0128 0136 0137 0142 0147 0157 0160 0208 0218 0220 0227 0228 0381

CXN 0192 0199 0201 0242 0243 0264 DLH 0020 0024 0027 0028 0035 0047 0052 0053 0056 0135 0158 0213 0233 0252 0274 0297 0304 0321 0325 0327 0335 0347 0352 0354 0355 0379 0390 0434 0447 DRD 0007 ETD 0117 GFA 0039 0040 0097 0103 0133 0212 0215 0282 0554 IBE 0125 0134 0145 0146 0193 0197 0217 0221 0302 0318 0329 0332 0378 0387 0414 0459 0474 0483 KAC 0089 0090 0101 0104 LAN 0359 0363 0429 0442

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 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: 0001-0009 0011 0013-0016 0018-0029 0031-0035 0038-0041 0043-0044 0046-0049 0051-0053 0056-0058 0061 0063 0074-0076 0078-0081 0084-0085 0088-0091 0093-0094 0097 0101 0103-0104 0114-0115 0117 0123 0125-0126 0128-0129 0131 0133-0137 0139 0141-0142 0145-0147 0149-0152 0154 0156-0161 0163-0164 0166-0170 0173-0176 0178-0180 0182 0185-0187 0190 0192-0194 0196-0197 0199 0201-0202 0204 0207-0208 0210 0212-0218 0220-0221 0225 0227-0228 0233 0235-0237 0239 0242-0243 0245-0246 0252 0257 0260 0263-0264 0268 0270 0273-0274 0278 0280 0282 0292 0297 0302 0304 0307 0310 0318-0319 0321 0325 0327 0329 0331-0332 0335 0347 0352 0354-0355 0359 0363 0367 0373-0374 0377-0379 0381 0385 0387 0390 0395 0399 0402 0406 0411 0413-0415 0424 0429-0430 0433-0435 0438 0442 0446-0447 0450 0459 0467 0470 0474 0483 0528 0538 0541 0544-0546 0554 0556 0559 0561-0562 0582 0585 0590 0598 M3R 0061 MAU 0076 0094 0152 0194 0268 MSR 0156 0159 0178 NMB 0051 OAL 0235 0239 0280 0292 PAL 0173 0176 0187 0196 QAF 0026 R3L 0004 RJA 0014 0022 0038 0043 SAA 0006 0008 0011 0018 0019 0021 0544 0582 0590 SAS 0413 0424 0430 0435 0450 0467 0470 SWR 0538 0545 0546 0556 0559 0561 0562 0585 0598 TAP 0041 0044 0079 0091 THT 0385 0395 0438 0446 THY 0023 0025 0057 0115 0180 0270 0331 UAE 0139 0149 0163 0166 0185 0190 0202 0236 VIR 0002 0003 0013 0015 0058 0114 0164 0214 0225

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

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (3) Spares Refer to the Messier-Dowty Service Bulletin No. A33/34-32-222. B. CONCURRENT REQUIREMENTS None C. REASON (1) History A rupture of a MLG retraction actuator piston rod-end has occurred on an in-service A340 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. A340-32A4211 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 A340-32-4222 Rev 01 or Service Bulletin A340-32-4213 Rev 01 cancels the requirements of this Service Bulletin. NOTE : The accomplishment of Service Bulletin A330-32-4213 Rev 01 is the interim solution for the piston rod actuator. Service

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Bulletin A330-32-4222 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:- — 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 corrosion pitting and/or longitudinal and 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 A340-32A4211. (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).

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 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. 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 including nil results 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 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.

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (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. 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 longitudinal and circumferential 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 Accomplishment of this Service Bulletin has been rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandatory accomplishment timescale. 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

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 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

All Operator Telex (AOT) A340-32A4211, Messier-Dowty Service Bulletin (VSB) A33/34-32-222 Operator Information Telex (OIT) 999.0129/03/CL 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 ESPM : 20-55-00

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Operator Information Telex (OIT) 999.0034/04/CL Service Bulletin A340-32-4213 Rev 01 Service Bulletin A340-32-4222 Rev 01 K. PUBLICATIONS AFFECTED None L. INTERCHANGEABILITY/MIXABILITY None

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 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. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 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. 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 CHAPTER 20-55-00, CLEANING. (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

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 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 rod 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). 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 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 inspection: a Replace the retraction actuator WITHIN THE NEXT 10 FLIGHTS, depending on the inspection results in

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 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). 4 If a finding requiring the retraction actuator removal is made during the ultrasonic longitudinal 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 longitudinal and circumferential inspection, and the piston rod has not yet been drained, the piston rod vent hole should be re-sealed. This will

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SERVICE BULLETIN

DATE : Dec 17/03 SERVICE BULLETIN No. : A340—32—4212 REVISION No. : 04 — Jun 12/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 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 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. : A340—32—4212 REVISION No. : 04 — Jun 12/06 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:..........................

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

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

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....................................... 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. : A340—32—4212 REVISION No. : 04 — Jun 12/06 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.