A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY 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. 05 of Service Bulletin No. A340-32-4212

ADDITIONAL WORK

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision 05 of this Service Bulletin has been issued in order to introduce a specific threshold inspection

for the piston rod PN 114256326 reidentified in accordance with Service Bulletin A340-32-4260.

The opportunity was taken to update the effectivity.

CHANGES

SUMMARY :

- REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Standard sentence has been added. Reference to Piston Rod PN 114256326 has been added.

References to ADs have been amended. References to ADs have been added. Service Bulletin

Nos have been corrected.

- EFFECTIVITY

. Operators 39Z, 50Z, AEA, AIB, BWA, CXN and DRD have been deleted. Operators 13W, AAW,

CCA, DGA, FIN, MPD, S3R and VCV have been added.

- CONCURRENT REQUIREMENTS

. Service Bulletin A340-32-4260 has been added.

PLANNING INFORMATION :

- CONCURRENT REQUIREMENTS

. 1.B. Service Bulletin A340-32-4216 has been added.

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 1 of 3

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

- REASON

- History

. 1.C.(1) AD references have been amended. Service Bulletin references have been corrected.

Sentence has been added.

- Objective/Action

. 1.C.(2) Standard sentence has been added.

- DESCRIPTION

. 1.D.(1)(b)2 Paragraph reference has been removed and Airworthiness Directive has been added.

. 1.D.(1)(c)1 Paragraph reference has been removed and Airworthiness Directive has been added.

. 1.D.(1)(d)2 Paragraph reference has been removed and Airworthiness Directive has been added.

. 1.D.(1)(e) Paragraph reference has been removed and Airworthiness Directive has been added.

- Accomplishment Timescale

. 1.E.(2) Revision 04 has been added. Sentence has been added.

- APPROVAL

. 1.F. Approval statement has been updated.

- REFERENCES

. 1.J. F-2003-458 becomes F-2003-459 and F-2004-086 becomes F-2004-087. AD F-2005-099,

F-2006-0301 and Service Bulletin A340-32-4260 have been added.

- INSPECTION

. 3.B.(1) Figure references have been added.

. 3.B.(1)(a)3 Paragraph reference has been removed and Airworthiness Directive has been added.

. 3.B.(1)(b)2 Paragraph reference has been removed and Airworthiness Directive has been added.

. 3.B.(1)(c)3 Paragraph reference has been removed and Airworthiness Directive has been added.

- Figure 1

. Flow Chart has been added.

- Figure 2

. Flow Chart has been added.

- Figure 3

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 2

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

. Flow Chart has been 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 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.

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

REVISION No. : 05 - Sep 26/08

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 3

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 4

Printed in France © AIRBUS 2008 All rights reserved
A340

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

MANDATORY 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

This Service Bulletin is published to advise all operators of A340 aircraft of the issue of Messier-Dowty

Service Bulletin No. A33/34-32-222.

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.

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.

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 1 of 4

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

SUMMARY

On aircraft fitted with the piston rod PN 114256326 reidentified in accordance with Service Bulletin

A340-32-4260, the inspection threshold is increased.

Original issue of this Service Bulletin was rendered Mandatory by Airworthiness Directive (AD) (Consigne de

Navigabilite (CN)) No. F-2003-459 (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-2004-087 (B) was issued to supersede AD (CN) No.

F-2003-459(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.

Other ADs have now been issued and therefore AD (CN) No. F-2004-087(B) has been superseded by AD

(CN) No. F-2005-099 which as also now been superseded by AD (CN) No. 2006-0301.

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 A340-32-4213 Rev 01 is the interim solution for the

piston rod actuator. Service Bulletin A340-32-4222 Rev 01 will take the piston rod actuator

to Design Service Goal.

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

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 2

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A340

SERVICE BULLETIN

SUMMARY

EFFECTIVITY

This Service Bulletin is applicable to these operators :

13W AAW ACA AFR AJM ALK ARG AUA B3R CAL CCA CES CPA DGA DLH ETD FIN GFA IBE KAC LAN

M3R MAU MPD MSR NMB OAL PAL QAF R3L RJA S3R SAA SAS SWR TAP THT THY UAE VCV VIR

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

Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the following

Service Bulletin(s) or the equivalent production modification(s):

Service Bulletin No. A340-32-4260

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

TOTAL MANHOURS 1.0*

ELAPSED TIME (HOURS) 1.0*

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 3

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A340

SERVICE BULLETIN

SUMMARY

NOTE(*) For the inspection manhours, refer to the Messier-Dowty Service Bulletin No. A33/34-32-222.

MATERIAL INFORMATION

AIRCRAFT DATA

None

APPENDICES

None

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 4

Printed in France © AIRBUS 2008 All rights reserved
A340

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

MANDATORY 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 :

0002-0009 0011 0013-0015 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

(b) Effectivity by Operator

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 1 of 19

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A340

SERVICE BULLETIN

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

13W 0009

AAW 0151

ACA 0088 0154 0170 0175 0179 0273 0278

AFR 0029 0049 0078 0084 0168 0174 0186 0207 0210 0237 0245 0246

0260 0307 0310 0319 0373 0377 0399

AJM 0216 0257

ALK 0032 0033 0034 0367 0374

ARG 0048 0063 0074 0080 0085 0093

AUA 0169

B3R 0046

CAL 0402 0406 0411 0415 0433 0541

CCA 0192 0199 0201 0242 0243 0264

CES 0129 0131 0141 0161 0182

CPA 0123 0126 0128 0136 0137 0142 0147 0157 0160 0208 0218

0220 0227 0228 0381

DGA 0075 0081

DLH 0020 0024 0027 0028 0035 0052 0053 0056 0135 0158 0213 0233

0252 0274 0297 0304 0321 0325 0327 0335 0347 0352 0354

0355 0379 0390 0434 0447

ETD 0117

FIN 0058

GFA 0039 0040 0097 0103 0133 0212 0215 0282 0554

IBE 0005 0125 0134 0145 0146 0193 0197 0217 0221 0302 0318 0329

0332 0378 0387 0414 0459 0474 0483

KAC 0089 0090 0101 0104

LAN 0167 0359 0363 0429 0442

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 2

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A340

SERVICE BULLETIN

OPERATOR MSN

M3R 0061

MAU 0076 0094 0152 0194 0268

MPD 0007 0013 0015

MSR 0156 0159 0178

NMB 0047 0051

OAL 0235 0239 0280 0292

PAL 0173 0176 0187 0196

QAF 0026 0528

R3L 0004

RJA 0014 0022 0038 0043

S3R 0204

SAA 0006 0008 0011 0018 0019 0021 0544 0582 0590

SAS 0413 0424 0430 0435 0450 0467 0470

SWR 0150 0263 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

VCV 0031

VIR 0002 0003 0114 0164 0214 0225

(c) Effectivity by MSN and Kit/Configuration

The Kits and configurations applicable to these MSNs are given at the end of this list

0002-0009 0011 0013-0015 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

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 3

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A340

SERVICE BULLETIN

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

KIT No. QTY PER A/C CONFIGURATION

None 01

NOTE : Config. 01 is valid for all the aircraft given in the effectivity of this Service

Bulletin as a standard configuration.

(3) Spares

Refer to the Messier-Dowty Service Bulletin No. A33/34-32-222.

B. CONCURRENT REQUIREMENTS

Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the

following Service Bulletin(s) or the equivalent production modification(s):

Service Bulletin No. A340-32-4260

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-2003-459

(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-2004-087 (B) was issued to supersede AD

(CN) No. F-2003-459(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.

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 4

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A340

SERVICE BULLETIN

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.

Other ADs have now been issued and therefore AD (CN) No. F-2004-087(B) has been

superseded by AD (CN) No. F-2005-099 which as also now been superseded by AD

(CN) No. 2006-0301.

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 A340-32-4213 Rev 01 is the interim

solution for the piston rod actuator. Service Bulletin A340-32-4222 Rev 01 will

take the piston rod actuator to Design Service Goal.

(2) Objective/Action

This Service Bulletin is published to advise all operators of A340 aircraft of the issue of

Messier-Dowty Service Bulletin No. A33/34-32-222.

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 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.

On aircraft fitted with the piston rod PN 114256326 reidentified in accordance with Service

Bulletin A340-32-4260, the inspection threshold is increased.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to:

(1) Config. 01

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 5

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A340

SERVICE BULLETIN

(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 the

Airworthiness Directive.

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 the Airworthiness Directive.

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 the Airworthiness Directive.

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

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 6

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A340

SERVICE BULLETIN

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 threshold given in the Airworthiness Directive,

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.

It is anticipated that a revision to the AD will be issued to introduce an increased inspection

threshold for piston rod PN 114256326 reidentified in accordance with Service Bulletin

A340-32-4260.

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA 21J.031.

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 7

Printed in France © AIRBUS 2008 All rights reserved
A340

SERVICE BULLETIN

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

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

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

Airworthiness Directive (AD) : F-2003-459 (B) F-2004-087 (B)

F-2005-099 F-2006-0301

Aircraft Maintenance Manual (AMM) : 12-34-24 32-12-00 32-31-46

ESPM : 20-55-00

All Operator Telex (AOT) A340-32A4211

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 8

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SERVICE BULLETIN

Messier-Dowty Service Bulletin (VSB) A33/34-32-222

Operator Information Telex (OIT) 999.0129/03/CL999.0034/04/CL

Service Bulletin A340-32-4213 Rev 01

Service Bulletin A340-32-4222 Rev 01

Service Bulletin A340-32-4260

K. PUBLICATIONS AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

None

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SERVICE BULLETIN

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

DESCRIPTION REFERENCE TO CML QTY PER A/C INST/DISP

MAT No.

Cleaning agent Mat. No. 11-026 As required

(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.

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SERVICE BULLETIN

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.

IN CASE OF CONTAMINATION REFER TO ESPM 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

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SERVICE BULLETIN

None

B. INSPECTION

(1) Config. 01

Refer to Figure 1

Refer to Figure 2

Refer to Figure 3

(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 the Airworthiness Directive.

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 the Airworthiness Directive.

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:

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SERVICE BULLETIN

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 the Airworthiness Directive.

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 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.

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SERVICE BULLETIN

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.

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

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A340

SERVICE BULLETIN

Figure 1, Sheet 1

Config. 01: Flow Chart, 1

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 17

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A340

SERVICE BULLETIN

Figure 2, Sheet 1

Config. 01: Flow Chart, 2

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 18

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A340

SERVICE BULLETIN

Figure 3, Sheet 1

Config. 01: Flow Chart, 3

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

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This Page Intentionally Left Blank

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SERVICE BULLETIN

REPORTING SHEET

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 embodiement:

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

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

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

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

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

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

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

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

From Airline: ........................................................................................................................................................

Name/Title: ..........................................................................................................................................................

Signature:..................... Date: .....................................................

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next

normal revision or prior to SB embodiment, please indicate required service(s):

Either : Advance data................................................................................... YES/NO

Or : Intermediate/Temporary 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: SEDCC1 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 : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 1 of 1

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SERVICE BULLETIN

REPORTING QUALITY

TITLE : LANDING GEAR - MLG - INSPECTION OF THE MLG RETRACTION ACTUATOR PISTON-ROD

MODIFICATION No. : None

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 futher 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 CEDEX FRANCE

Attn: SEMB Service Bulletins Management

FAX: (+33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE : Dec 17/03 SERVICE BULLETIN No. : A340-32-4212

REVISION No. : 05 - Sep 26/08 Page : 1 of 1

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