7 DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 32

TITLE : LANDING GEAR - MLG - INSPECTION OF THE MLG RETRACTION ACT

PISTON-ROD

MODIFICATION No. : None

This page transmits Revision No. 03 of Service Bulletin No. A340-

ADDITIONAL WORK

Additional work is required by this revision for aircraft mod

previous issue.

Do a one-time ultrasonic inspection of the full length of the 

REASON

This revision has been issued to inform operators that:

— A one-time ultrasonic longitudinal and circumferential insp

full piston rod has been added.

— Modification Service Bulletin references have been added as 

action.

— Accomplishment timescale has been amended.

— The interval for the fluid drainage has been amended.

— Operators AEA and DRD have been added. Operator AIB has bee

— Config. 01 has been added.

CHANGES

SUMMARY :

— REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Sentence and NOTE added. EVALUATION TABLE revised.

— EFFECTIVITY
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— EFFECTIVITY

. 1.A. Note added. Operator AIB deleted. Operators AEA and 

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) thru (s) 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
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— 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 

complete document. Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service B

HISTORY OF PREVIOUS REVISIONS

Revision 01 of this Service Bulletin was issued to add a new A

F-2004-086 (B) to supersede AD (CN) No. F-2003-458 (B) and ma

Service Bulletin. This is due to the addition of the repetitiv

inspection of the complete chromed area of the piston rod. Al

opportunity has been taken to update the aircraft effectivity 

the aircraft configurations.

Revision 02 of this Service Bulletin was issued to show the c

inspection procedures and to include the drainage of water or 

from the piston rod. The mandatory accomplishment timescales w

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
7 DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

This summary is for information only

and is not approved for modification of the aircraf

MANDATORY MANDATORY MAND

ATA SYSTEM : 32

TITLE : LANDING GEAR - MLG - INSPECTION OF THE MLG RETRACTION ACT

PISTON-ROD

MODIFICATION No. : None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

A rupture of a Main Landing Gear (MLG) retraction actuator piston 

occurred on an in-service A340 aircraft. This resulted from inter

and circumferential cracking around the painted upper end of the 

A longitudinal crack has also been found on the chromed part of a 

actuator piston-rod. Investigations indicate that the crack start

of corrosion pitting within the piston rod bore.

All Operator Telex. (AOT) No. A340-32A4211 was issued to request 

carry out an ultrasonic inspection of the retraction actuator pis

have been in service for more than six years.

The Messier Dowty Service Bulletin A33/34-32-222 requires the act

follow on the MLG retraction actuator piston rods that have been 

three years or more:-

— A visual inspection of the chromed area of the piston rods for 

— The draining of water or other fluids from the piston rods whic

and cause future cracks.

— A repeat ultrasonic longitudinal inspection of the painted uppe

piston rods for corrosion pitting and/or circumferential cracks

— A one-time ultrasonic longitudinal and circumferential inspecti

length of the piston rods for corrosion pitting and/or longitud

circumferential cracks.

This Service Bulletin supersedes AOT A340-32A4211.
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

corrosion pitting within the piston-rod bore along the chromed le

occurrence led to a revision of the requirement for the inspectio

piston-rods chromed area.

Following this second event a new AD (CN) F-2004-086 (B) was issue

AD (CN) No. F-2003-458(B) and to mandate this Service Bulletin at 

and above.

A third in-service retraction actuator piston rupture has occurre

first rupture, this failure resulted from internal corrosion and c

cracking around the painted upper end of the piston rod.

Subsequently, another piston rod has been found in operation with 

crack in the chromium plated part of the piston rod. Investigatio

that the crack started from a line of corrosion pitting within th

bore.

The accomplishment of Service Bulletin A340-32-4222 or Service Bu

A340-32-4213 Rev 01 cancels the requirements of this Service Bull

NOTE : The accomplishment of Service Bulletin A330-32-4213 Rev 01 

solution for the piston rod actuator. Service Bulletin A33

take the piston rod actuator to Design Service Goal.

EFFECTIVITY

This Service Bulletin is applicable to these operators :

39Z 50Z ACA AEA AFR AJM ALK ARG AUA B3R BWA CAL CES CPA CRX CXN D

IBE KAC LAN M3R MAU MSR OAL PAL QAF R3L RJA SAA SAS TAP THT THY UA

EVALUATION TABLE

COMPLIANCE Mandatory CANCELS INSPECTION S

AD Yes A/C OPERATION AFFECT

RELIABILITY AFFECTED Yes PAX COMFORT AFFECTED 

COST SAVING No ETOPS AFFECTED 

STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED 

KIT PRICE (USD) No kit

2
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

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 999.0034/0

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 

Bulletin No. A33/34-32-222.

MATERIAL INFORMATION

AIRCRAFT DATA

None

APPENDICES

None

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

3
7 DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 32

TITLE : LANDING GEAR - MLG - INSPECTION OF THE MLG RETRACTION ACT

PISTON-ROD

MODIFICATION No. : None

This document contains AIRBUS PROPRIETARY INFORMATION and shall a

remain the property of AIRBUS; no intellectual property right or 

granted by AIRBUS in connection with any information contained in 

delivered on the express condition that said document and the inf

contained in it shall be treated as confidential, shall not be us

purpose other than that for which it is hereby delivered. It shal

disclosed in whole or in part to third parties and shall not be d

any manner (except for the purposes of performing the tasks descr

and provided that any recipient of such document shall comply wit

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 

0002-0009 0011 0013-0016 0018-0029 0031-0035 00

0044 0046-0049 0051-0053 0056-0058 0061 0063 00

0078-0081 0084 0085 0088-0091 0093 0094 0097 010

0114 0115 0117 0123 0125 0126 0128 0129 0131 01

0141 0142 0145-0147 0149-0152 0154 0156-0161 01

0166-0170 0173-0176 0178-0180 0182 0185-0187 019

0196 0197 0199 0201 0202 0204 0207 0208 0210 02

0221 0225 0227 0228 0233 0235-0237 0239 0242 024

0252 0257 0260 0263 0264 0268 0270 0273 0274 02

0292 0297 0302 0304 0307 0310 0318 0319 0321 03

0331 0332 0335 0347 0352 0354 0355 0359 0363 03

0377-0379 0381 0385 0387 0390 0395 0399 0402 040
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(b) Effectivity by Operator

The Operator/MSN relationship is provided for in

and is correct at the time of issue in accordan

information available to AIRBUS. Any future cha

from transfer of an aircraft from one operator t

not be reflected in this list unless the Service 

revised for another reason.

OPERATOR MSN

39Z 0151

50Z 0009

ACA 0048 0088 0150 0154 0167 0170 0175 0

AEA 0031

AFR 0005 0029 0049 0078 0084 0168 0174 0

0237 0245 0246 0260 0307 0310 0319 0

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 0

0218 0220 0227 0228 0381

CRX 0538 0545 0546 0556 0559 0561 0562 0

CXN 0192 0199 0201 0242 0243 0264

DLH 0020 0024 0027 0028 0035 0047 0051 0

0135 0158 0213 0233 0252 0274 0297 0

0327 0335 0347 0352 0354 0355 0379 0

DRD 0007

ETD 0117

GFA 0039 0040 0097 0103 0133 0212 0215 0

2
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

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 

at the end of this list:

0002-0009 0011 0013-0016 0018-0029 0031-0035 00

0043-0044 0046-0049 0051-0053 0056-0058 0061 00

0078-0081 0084-0085 0088-0091 0093-0094 0097 010

0114-0115 0117 0123 0125-0126 0128-0129 0131 01

0141-0142 0145-0147 0149-0152 0154 0156-0161 01

0166-0170 0173-0176 0178-0180 0182 0185-0187 019

0196-0197 0199 0201-0202 0204 0207-0208 0210 02

0220-0221 0225 0227-0228 0233 0235-0237 0239 024

0245-0246 0252 0257 0260 0263-0264 0268 0270 02

0280 0282 0292 0297 0302 0304 0307 0310 0318-03

0327 0329 0331-0332 0335 0347 0352 0354-0355 03

0373-0374 0377-0379 0381 0385 0387 0390 0395 039

0411 0413-0415 0424 0429-0430 0433-0435 0438 044

0450 0459 0467 0470 0474 0483 0528 0538 0541 054

0556 0559 0561-0562 0582 0585 0590 0598

M3R 0061

MAU 0076 0094 0152 0194 0268

MSR 0156 0159 0178

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 0

SAS 0413 0424 0430 0435 0450 0467 0470

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 0

VIR 0002 0003 0013 0015 0058 0114 0164 0

KIT No. QTY PER A/C CONFIGURATION

01

3
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

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 

on an in-service A340 aircraft. This resulted from i

corrosion and circumferential cracking around the pai

of the piston rod.

Longitudinal cracks have also been found on the chrom

retraction actuator piston-rod. Investigations indica

crack started from a line of corrosion pitting withi

rod bore.

Original issue of this Service Bulletin was rendered 

AD (CN) No. F-2003-458 (B).

A second in-service piston rod rupture occurred as a 

line of corrosion pitting within the piston-rod bore 

chromed length. This occurrence led to a revision of 

requirement for the inspection of the piston-rods ch

Following this second event a new AD (CN) F-2004-086 

to supersede AD (CN) No. F-2003-458(B) and to mandat

Bulletin at revision 01 and above.

A third in-service retraction actuator piston rupture 

As with the first rupture, this failure resulted from 

corrosion and circumferential cracking around the pai

of the piston rod.

Subsequently, another piston rod has been found in op

longitudinal crack in the chromium plated part of th

Investigations indicate that the crack started from a 

corrosion pitting within the piston rod bore.

All Operator Telex No. A340-32A4211 has been issued t

operators to carry out an ultrasonic inspection of t

actuator piston-rods that have been in service for mo

years.

The accomplishment of Service Bulletin A340-32-4222 o

Bulletin A340-32-4213 Rev 01 cancels the requirement

Service Bulletin.

NOTE : The accomplishment of Service Bulletin A330-3

is the interim solution for the piston rod act

4
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— A visual inspection of the chromed area of the pist

cracks.

— The draining of water or other fluids from the pist

could freeze and cause future cracks.

— A repeat ultrasonic longitudinal inspection of the 

end of the piston rods for corrosion pitting and/o

circumferential cracks.

— A one-time ultrasonic longitudinal and circumferent

of the full length of the piston rods corrosion pit

longitudinal and circumferential cracks.

(3) Advantages

The accomplishment of this Service Bulletin makes sur

retraction actuator rod has no cracks and is free of 

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 act

NOTE : It is not necessary to raise the aircraft 

this inspection.

(b) Do a DVI of the chromed part of the retraction a

rod for cracks in accordance with the Messier-Do

Bulletin No. A33/34-32-222.

1 If one or more cracks are found during the DV

actuator BEFORE THE NEXT FLIGHT.

2 If no cracks are found, do a repeat DVI at t

intervals given in para 1.E.(2)(b).

5
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Bulletin No. A33/34-32-222.

(c) Drain the fluid from the retraction actuator pi

seal the vent hole in accordance with the Messie

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

1 Repeat the draining and sealing of the vent 

at the specified intervals given in para 1.E

2 Report the results including nil results of t

actuator draining using the proforma at Appe

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

(d) Do an ultrasonic inspection of the upper painted 

retraction actuator piston rod for indications o

accordance with the Messier-Dowty Service Bullet

A33/34-32-222 Appendix A.

1 If indications of cracks are found during the 

inspection:

a Replace the retraction actuator WITHIN TH

FLIGHTS, depending on the inspection resul

accordance with the Messier-Dowty Service 

A33/34-32-222 Appendix A.

or

b Replace the retraction actuator BEFORE TH

depending on the inspection results in acc

the Messier-Dowty Service Bulletin No. A3

Appendix A.

2 If no cracks are found, do a repeat ultrason

at the specified intervals given in para 1.E

3 If a finding requiring the retraction actuato

made during the ultrasonic inspection, and t

has not yet been drained, the piston rod vent 

be re-sealed to retain the contents of the in

before the removal and the return of the ret

actuator in accordance with the Messier-Dowty 

Bulletin No. A33/34-32-222.

4 Report the results of the ultrasonic inspecti

of findings) using the proforma at Appendix C 

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

6
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

a Replace the retraction actuator WITHIN TH

FLIGHTS, depending on the inspection resul

accordance with the Messier-Dowty Service 

A33/34-32-222 Appendix E and F.

or

b Replace the retraction actuator BEFORE TH

depending on the inspection results in acc

the Messier-Dowty Service Bulletin No. A3

Appendix E and F.

2 If a finding requiring the retraction actuato

made during the ultrasonic inspection, and t

has not yet been drained, the piston rod vent 

be re-sealed to retain the contents of the in

before the removal and the return of the ret

actuator in accordance with the Messier-Dowty 

Bulletin No. A33/34-32-222.

3 Report the results of the one-time ultrasonic 

and circumferential inspection (regardless of 

using the proforma at Appendix C of Messier-D

Bulletin No. A33/34-32-222.

E. COMPLIANCE

(1) Classification

Mandatory

(2) Accomplishment Timescale

(a) Accomplishment of this Service Bulletin has bee

mandatory by the issue of a Airworthiness Direct

published by the DGAC on behalf of the European 

Safety Agency (EASA). The AD must be used as the 

document for the mandatory accomplishment times

(b) DVI: - For retraction actuator piston rods ident

accordance with Messier-Dowty Service Bulletin N

A33/34-32-222, when they reach three years use 

the latest.

7
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

8 calendar days, in accordance with Messier-D

Bulletin No. A33/34-32-222.

NOTE : When the one-time ultrasonic inspectio

performed with no findings and the flu

has been performed, as detailed in thi

Bulletin it is no longer necessary to 

day DVI on the piston rods.

(c) Fluid drain and vent hole sealing: - For retract

piston rods identified in accordance with Messie

Service Bulletin No. A33/34-32-222, when they re

years use in service at the latest.

1 Do the procedure to drain fluid from the ret

actuator piston rods internal volume and sea

hole, in accordance with Messier-Dowty Servic

A33/34-32-222.

2 Repeat the procedure at intervals of 1,000 FC 

whichever occurs first in accordance with Me

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

NOTE : When the one-time ultrasonic inspectio

performed with no findings and the flu

has been performed, as detailed in thi

Bulletin it is no longer necessary to 

day DVI on the piston rods.

(d) Ultrasonic inspection of the upper painted area 

rods: - For retraction actuator piston rods ide

accordance with Messier-Dowty Service Bulletin N

A33/34-32-222, when they reach three years use 

the latest.

1 Do an ultrasonic inspection of the painted a

upper end of the piston rods, in accordance w

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

2 Repeat ultrasonic inspections are required at 

FH or 4 months whichever occurs first.

(e) one-time ultrasonic inspection of the full pisto

- For retraction actuator piston rods identified 

with Messier-Dowty Service Bulletin No. A33/34-

they reach three years use in service at the lat

8
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Approved under the authority of the EASA Design Organisat

No. EASA. 21J.031.

If an aircraft listed in the effectivity has a modificatio

embodied that is not of AIRBUS origin, and which affects 

this Service Bulletin, the operator is responsible for ob

approval by its airworthiness authority for any adaptatio

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are 

direct labour cost to do the work. These estimates assume 

will be done by experienced personnel, and may need to be 

upwards to suit operator's circumstances. The estimates do 

the time to prepare, plan or inspect the work. Manufactur

procurement of parts and tools, drying times for paints, 

and general administration work are also not included.

Config. 01

NOTE : * For the preparation and inspection man-hours refe

Messier-Dowty Service Bulletin A33/34-32-222.

H. WEIGHT AND BALANCE

Not changed

I. ELECTRICAL LOAD DATA

Not changed

Get access 

Visual inspection 

Drain Fluid from Piston

Rod

Ultrasonic inspection 

One-time ultrasonic

inspection

Close up 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

9
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

p() ,

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 A340-32-4213 Rev 01, A340-32-4222

K. PUBLICATIONS AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

None

10
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(2) Price and Availability

None

B. INDUSTRY SUPPORT INFORMATION

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

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

G. SPECIAL TOOLS

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

DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C 

Cleaning agent 11-026 As required

11
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

This Page Intentionally Left Blank

12
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— THE FLIGHT CONTROL SURFACES

— THE LANDING GEAR AND RELATED DOORS

— COMPONENTS THAT MOVE.

WARNING : MAKE SURE THAT THE GROUND SAFETY LOCKS ARE CORRE

ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOV

LANDING GEAR.

WARNING : MAKE SURE THAT YOU OBEY ALL WARNINGS AND THE CAU

IN THE REFERENCED PROCEDURES.

(1) Preparation

(a) Config. 01

1 Make sure that the aircraft is electrically g

to AMM 12-34-24 Page block 201).

2 Open and safety the main gear doors (Refer to 

Page block 201).

3 Put access steps in position, as required.

4 Make sure that the piston rods of the retract

are clean, use Cleaning agent (Mat No. 11-026

required.

(2) Standard Practices

None

B. INSPECTION

(1) Config. 01

(a) MLG (LH and RH) Retraction Actuator - DVI of the 

1 Do a DVI of the chromed part of the fully ext

retraction actuator piston rod for cracks in 

with the Messier-Dowty Service Bulletin No. A

2 If one or more cracks are found during the v

inspection, replace the retraction actuator B

FLIGHT (Refer to AMM 32-31-46 Page block 401)

13
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

5 Report all retraction actuators rejected dur

inspection in accordance with the instructio

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

(b) MLG (LH and RH) Retraction Actuator - Drain the 

piston rod and seal the vent hole:

1 Drain the fluid from the retraction actuator 

seal the vent hole in accordance with the Me

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

2 Repeat the draining and sealing of the vent 

at the specified intervals given in Para 1.E

3 Report the results of the retraction actuato

using the proforma in Appendix C of Messier-D

Bulletin No. A33/34-32-222.

(c) MLG (LH and RH) Retraction Actuator - Ultrasoni

inspection of the painted area of the piston rod

1 Do an ultrasonic longitudinal inspection of t

painted area of the piston rods surface, for 

cracks in accordance with the Messier-Dowty S

Bulletin No. A33/34-32-222.

2 If indications of cracks are found during the 

inspection:

a Replace the retraction actuator WITHIN TH

FLIGHTS, depending on the inspection resul

accordance with the Messier-Dowty Service 

A33/34-32-222 (Refer to AMM 32-31-46 Page 

or

b Replace the retraction actuator BEFORE TH

depending on the inspection results in acc

the Messier-Dowty Service Bulletin No. A3

(Refer to AMM 32-31-46 Page block 401).

3 If no cracks are found, do a repeat ultrasoni

inspection at the specified intervals given 

1.E.(2)(d).

14
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

5 Report the results of the ultrasonic longitud

inspection (regardless of findings) using the 

Appendix C of Messier-Dowty Service Bulletin 

A33/34-32-222.

(d) MLG (LH and RH) Retraction Actuator - One-time 

longitudinal and circumferential inspection of t

of the piston rod:

1 Do an ultrasonic longitudinal and circumfere

inspection of the chromed area (full length) 

rods for indications of cracks, in accordance 

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

2 If indications of cracks are found during the 

longitudinal and circumferential inspection:

a Replace the retraction actuator WITHIN TH

FLIGHTS, depending on the inspection resul

accordance with the Messier-Dowty Service 

A33/34-32-222 (Refer to AMM 32-31-46 Page 

or

b Replace the retraction actuator BEFORE TH

depending on the inspection results in acc

the Messier-Dowty Service Bulletin No. A3

(Refer to AMM 32-31-46 Page block 401).

3 If a finding requiring the retraction actuato

made during the ultrasonic longitudinal and c

inspection, and the piston rod has not yet be

the piston rod vent hole should be re-sealed

retain the contents of the internal volume, d

removal and the return of the retraction act

accordance with the Messier-Dowty Service Bu

A33/34-32-222.

4 Report the results of the ultrasonic longitud

circumferential inspection (regardless of fi

the proforma at Appendix C of Messier-Dowty S

Bulletin No. A33/34-32-222.

C. TEST

None

15
DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(c) Close the main gear doors (Refer to AMM 32-12-00 

201).

E. DOCUMENTATION

Write in the applicable aircraft records that you have don

given in the Service Bulletin.

16
7 DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

A - SB WILL BE embodied............. YES/NO (if NO p

If YES, aircraft concerned (as per SB effectivity by default) and 

(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 th

information is needed prior to next normal revision or prior to S

please indicate required service:

Either: Modification Operational Impact (MOI), if available. . YE

Or : Intermediate revision. ................ YE

Important Information: This SB will only be incorporated in your m

operational documentation if this sheet is returned to Airbus and 

duly authorised representative. With the next feasible revision, 

result in

- updating of maintenance documentation to show pre and post S

- updating of maintenance and operational documentation to show 

after embodiment.

If this SB requires previous or simultaneous accomplishment of ot

Airbus shall automatically include them in the manual revisions. 

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.
7 DATE : Dec 17/03 SERVICE BULLETIN No. : A340

REVISION No. : 03 — Mar 13/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(Please rate on a scale of 1 to 4, with 4 being the 

- Quality rating of this SB 

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If you have had difficulties in the accomplishment of this SB plea

the area(s) and give a short description of the issue.

Planning Material Instruct

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Please return this form to :

AIRBUS

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31707 BLAGNAC

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