EASA AD No : 2011-0178R1 

EASA Form 110 Page 1/6 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0178R1 

[Correction: 07 March 2012] 

Date: 06 March 2012 

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with 

Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of 

the European third countries that participate in the activities of EASA under Article 66 of that 

Regulation. 

This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the 

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate 

an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency 

[EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

Type Approval Holder’s Name : 

AIRBUS

Type/Model designation(s) : 

A340-200/-300 aeroplanes 

TCDS Number: EASA.A.015 

Foreign AD: Not applicable 

Revision: This AD revises EASA AD 2011-0178 dated 16 September 2011 which 

superseded EASA AD 2006-0301R2 dated 10 September 2009. 

ATA 32 Landing Gear – Main Landing Gear Retraction Actuator Piston 

Rod – Inspection / Modification 

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A340-211, A340-212, A340-213, A340-311, A340-312 and A340-313 

aeroplanes, all manufacturer serial numbers, except those on which Airbus 

modification (mod.) 52980 has been embodied in production on both Main 

Landing Gear (MLG). 

Note: Aeroplanes which have embodied in production Airbus mod. 52980 are 

not required to accomplish the re-identification of the MLG retraction actuator 

P/N 114256002-055, which is mentioned in the accomplishment instructions 

of Airbus Service Bulletin (SB) A340-32-4222 Revision 03. 

Aeroplanes on which Airbus mod. 54500 has been embodied in production 

are not affected by this AD. 

Reason: During an approach phase, the flight crew of an A330 aeroplane had to 

perform a free-fall extension of the left-hand (LH) MLG. 

Rupture of the LH MLG retraction actuator piston rod was found near the 

rod attachment point. The inspection revealed at the location of the rupture 

the presence of corrosion resulting from incorrect application of the anticorrosion protection, and circumferential cracks resulting from normal 

operational loading effects. 

Since the above rupture, new cases of crack propagation along the length of 

the piston rod occurred. These ruptures led to a non-damped extension of the 

landing gear. Fully extended, the landing gear assembly was submitted to 

high loads jeopardising its structural integrity. 

This condition, if not detected and corrected, could lead to MLG failure 
EASA AD No : 2011-0178R1 

EASA Form 110 Page 2/6 

during landing or roll-out and consequent damage to the aeroplane and 

injury to occupants. 

DGAC France issued AD F-2005-099 (EASA approval 2005-5888) to address 

this unsafe condition. Since that AD was issued, the results of extensive 

investigation determined that the presence of water in the internal volume of 

the piston rod can lead to the formation of ice which represents a potential 

source of high magnitude tensile hoop stresses in the material of the rod, 

leading to propagation of longitudinal crack in the body of the piston rod. 

Prompted by these findings, EASA issued AD 2006-0301, partially retaining 

the requirements of DGAC France AD F-2005-099, which was superseded, 

and to revise the inspection requirements as follows: 

a. Extend the repetitive inspections interval for the removal of fluid from the 

internal volume of the piston rod using flight cycles in lieu of flight hours as 

this better represents the mechanism for the accumulation of water within 

the piston rod. 

b. Remove the preliminary visual inspection from the ultrasonic longitudinal 

inspection of the upper end of the piston rod. 

c. Add a new one-time ultrasonic longitudinal and circumferential inspection 

of the full piston rod length to eliminate any parts that exhibit severe 

corrosion along the internal length of the piston rod. 

d. Require installation of new design hollow piston rod Part Number (P/N) 

114256328 (Airbus mod. 52980 - SB A340-32-4222 Revision 01) without a 

vent hole, thus eliminating moisture ingress as the terminating action. 

EASA AD 2006-0301 was later revised: 

- at revision 01, to correct a number of typographical errors and to add 

reference to Airbus SB A340-32-4212 Revision 04, and 

- at revision 02 to extend the inspections threshold from 3 to 6 years in service 

usage for retraction actuator piston rod P/N 114256321 issue 06 which was 

re-identified to P/N 114256326 issue 01 in accordance with the instructions of 

Airbus SB A340-32-4260.

More recently, the sampling of piston rod P/N 114256326 issue 1 and P/N 

114256321 issue 06 have confirmed the need to replace all retraction actuator 

piston rods with a piston rod P/N114256328. 

For the reasons described above, this AD at original issue retained the 

requirements of EASA AD 2006-0301R2, which is superseded, and required 

the replacement of all retraction actuator piston rods with a piston rod P/N 

114256328, which constitutes terminating action to the repetitive requirements 

of this AD. 

This AD is revised to clarify that aeroplanes on which Airbus mod. 52980 has 

been embodied in production are not required to accomplish the reidentification of MLG retraction actuator P/N 114256002-055 which is 

mentioned in the accomplishment instructions of Airbus SB A340-32-4222 

Revision 03.

This AD has been republished to correct a typographical mistake of the 

applicable Airbus SB number in the Applicability (in the Note) and in the 

Reason sections of this AD. 

Effective Date: 

Original issue: 30 September 2011 

Revision 1: 20 March 2012 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless previously accomplished: 

A) Restatement of EASA AD 2006-0301R2 requirements:

Paragraphs (1), (2), (3), (4), (5), (6) and (7) of this AD are applicable, as 

indicated, after 19 October 2006 [the effective date of EASA AD 2006-
EASA AD No : 2011-0178R1 

EASA Form 110 Page 3/6 

0301R2] for aeroplanes equipped with:

(a) Retraction actuator piston rods P/N 114256309 and P/N 114256321 

issue 03, upon accumulation of three years of use in service, and 

(b) Retraction actuator piston rods P/N 114256326 issue 01 and P/N 

114256321 issue 06, upon accumulation of six years of use in service: 

(1) Detailed visual inspection of the retraction actuator piston rod: 

 For each concerned retraction actuator piston rod not yet visually 

inspected in accordance with the instructions of Airbus SB A340-32-

4212 at Revision 01, or Revision 02, or Revision 03, or Revision 04, or 

Revision 05, at the latest upon accumulation of three years or six years , 

as applicable, of in service usage, 

 or, 

 for each concerned retraction actuator piston rod that has already been 

visually inspected in accordance with the instructions of Airbus SB 

A340-32-4212 Revision 01, or Revision 02, or Revision 03, or Revision 

04, or Revision 05, within 8 days from the last visual inspection 

performed in accordance with the instructions of SB A340-32-4212 

Revision 01, or Revision 02, or Revision 03, or Revision 04, or Revision 

05, 

(1.1) Accomplish a visual inspection of the visible chromed area of the 

piston rod in fully extended position to search for cracks, in 

accordance with the instructions of Airbus SB A340-32-4212 

Revision 05. 

(1.2) Thereafter, at intervals not exceeding 8 days, repeat the visual 

inspection required by paragraph (1.1) of this AD, in accordance 

with the instructions of Airbus SB A340-32-4212 Revision 05. 

(1.3) If, during any inspection required by paragraphs (1.1) and (1.2) 

of this AD, one or more cracks are found, before next flight, 

replace the retraction actuator in accordance with the 

instructions of Airbus SB A340-32-4212 Revision 05.

Note 1: No further repetitive visual inspection is required to comply with 

paragraph (1) of this AD after accomplishment of drainage of the fluid from the 

piston as required by paragraph (2) of this AD in addition to the one-timeultrasonic non-destructive testing (NDT) inspection of the full length of the 

piston as required by paragraph (4) of this AD. 

(2) Drain the fluid from the piston rod and seal the vent hole: 

 For each concerned retraction actuator piston rod not yet inspected/fluiddrained in accordance with the instructions of Airbus SB A340-32-4212 

at Revision 02, or Revision 03, or Revision 04, or Revision 05, at the 

latest when it reaches three years or six years, as applicable, of in 

service usage, 

 or, 

 for each concerned retraction actuator piston rod that has already been 

inspected/fluid-drained in accordance with the instructions of Airbus SB 

A340-32-4212 at Revision 02, or Revision 03, or Revision 04, or 

Revision 05, within 1 000 flight cycles (FC) or 24 months, whichever 

occurs first, from the last inspection/fluid-drainage performed in 

accordance with the instructions of Airbus SB A340-32-4212 at 

Revision 02, or Revision 03, or Revision 04, or Revision 05, 

(2.1) Do the procedure to drain fluid from the retraction actuator piston 

rod internal volume and seal the vent hole in accordance with 

the instructions of Airbus SB A340-32-4212 Revision 05. 

(2.2) Thereafter, at intervals not exceeding 1 000 FC or 24 months 

whichever occurs first, repeat the draining and the sealing of the 
EASA AD No : 2011-0178R1 

EASA Form 110 Page 4/6 

vent hole required by paragraph (2.1) of this AD, in accordance 

with the instructions of Airbus SB A340-32-4212 Revision 05. 

Note 2: Accomplishment of drainage of the fluid from the piston as required by 

paragraph (2) of this AD, in addition to the one-time-ultrasonic NDT inspection 

of the full length of the piston as required by paragraph (4) of this AD, 

constitutes terminating action for the repetitive visual inspections required by 

paragraph (1) of this AD. 

(3) Ultrasonic NDT inspection of the upper end of the piston rod: 

 For each concerned retraction actuator piston rod not yet inspected in 

accordance with the instructions of Airbus SB A340-32-4212 at original 

issue, or Revision 01, or Revision 02, or Revision 03, or Revision 04, or 

Revision 05, upon accumulation of three years or six years, as 

applicable, of in service usage, 

 or, 

 for each concerned retraction actuator piston rod already NDT 

inspected in accordance with the instructions of Airbus SB A340-32-

4212 at original issue, or at Revision 01, or Revision 02, or Revision 03, 

or Revision 04, or Revision 05, within 1 400 flight hours, 250 FC or 4 

months from the date of the last NDT inspection performed in 

accordance with the instructions of Airbus SB A340-32-4212 at original 

issue, or at Revision 01, or Revision 02, or Revision 03, or Revision 04, 

or Revision 05, whichever occurs first, 

(3.1) Do an ultrasonic inspection of the retraction actuator piston rod 

end in accordance with the instructions of Airbus SB A340-32-

4212 Revision 05. 

(3.2) If the results of the inspection required by paragraph (3.1) of this 

AD give an indication above 90% FSH (Full Screen Height) and 

between 5 and 7 in Time Base, before next flight, replace the 

retraction actuator. 

(3.3) If the results of the inspection required by paragraph (3.1) of this 

AD give an indication between 75% and 90% FSH and between 

5 and 7 in Time Base, within the next 10 FC replace the 

retraction actuator. 

(3.4) If the results of the inspection required by paragraph (3.1) of this 

AD give an indication below 75% FSH and between 5 and 7 in 

Time Base, repeat the inspections required by paragraph (3.1) of 

this AD at intervals not exceeding 1 400 flight hours (FH) or 250 

FC or 4 months, from the previous inspection, whichever occurs 

first, and do the applicable corrective actions. 

(4) One-time ultrasonic (longitudinal and circumferential) NDT 

inspections of the full length of the piston rod: 

(a) At the latest when each concerned retraction actuator piston rod 

reaches three years or six years, as applicable, of in service usage, 

 or, 

(b) within 1 750 FH, 315 FC or 5 months, whichever occurs first, after 19 

October 2006 [the effective date of EASA AD 2006-0301R2] 

 whichever occurs later between (a) and (b): 

(4.1) One-time ultrasonic longitudinal NDT inspection of the full 

length of the piston rod: 

(4.1.1) Do a one-time ultrasonic longitudinal inspection of the 

chromium-plated area (full length) of the piston rod in 

accordance with the instructions of Airbus SB A340-32-

4212 Revision 05, and do the applicable corrective actions 

required by paragraph (3.2) or (3.3) of this AD. 
EASA AD No : 2011-0178R1 

EASA Form 110 Page 5/6 

(4.1.2) If the results of the inspection defined in paragraph (4.1.1) 

give an indication below 75% FSH and between 5 and 7 in 

Time Base, no further action is required. 

(4.2) One-time ultrasonic circumferential NDT inspection of the full 

length chromed part of the piston rod: 

(4.2.1) Do a one-time ultrasonic circumferential inspection of the 

chromium-plated area (full length) of the piston rod, in 

accordance with the instructions of Airbus SB A340-32-

4212 Revision 05. 

(4.2.2) If the results of the inspection required by paragraph 

(4.2.1) of this AD give an indication above 90% FSH and 

between 7 and 9.5 on the time base, before next flight 

replace the retraction actuator. 

(4.2.3) If the results of the inspection required by paragraph 

(4.2.1) of this AD give an indication between 75 and 90% 

FSH and between 7 and 9.5 on the time base, within the 

next 10 landings replace the retraction actuator. 

(4.2.4) If the results of the inspection required by paragraph 

(4.2.1) of this AD give an indication below 75% FSH and 

between 7 and 9.5 in Time Base, no further action is 

required. 

Note 3: Accomplishment of the one-time-ultrasonic NDT inspection of the 

full length of the piston as defined in paragraph (4) in addition to the 

drainage of the fluid from the piston as defined in paragraph (2) cancels the 

repetitive visual inspection requirement as defined in paragraph (1) of this 

AD. 

Note 4: Any retraction actuator piston rod P/N 114256309 or 114256321 or 

114256326 issue 01, installed as a replacement, new or used, must comply 

with the applicable requirements of this AD at the stated thresholds and 

intervals. 

(5) Reporting 

(5.1) In all cases, upon completion of the tasks in accordance with the 

instructions of Airbus SB A340-32-4212 Revision 05, report to 

Airbus the results (regardless of findings) of: 

 - the visual inspection, 

- fluid drain/seal of the retraction actuator piston rod, 

- ultrasonic NDT of the upper end of the piston rod, and 

- the one time ultrasonic NDT inspection. 

(5.2) Report also the results whenever the replacement of the 

retraction actuator is required in accordance with the instructions 

of Airbus SB A340-32-4212 Revision 05. 

(6) Aeroplanes that have been inspected or drained, before the effective date 

of this AD at original issue, in accordance with the instructions of Airbus 

SB A340-32-4212 Revision 03, or Revision 04, are compliant with the 

initial requirements of paragraph (1), (2), (3), (4) and (5) of this AD. 

However, after the effective date of this AD at original issue, the repetitive 

inspections or draining must be accomplished in accordance with the 

instructions of Airbus SB A340-32-4212 Revision 05.

(7) Modification 

 Not later than 31 December 2007, remove and replace the retraction 

actuator piston rod P/N 114256309 or P/N 114256321 issue 03 in 

accordance with the instructions of Airbus SB A340-32-4222 Revision 01. 

(8) Installation of retraction actuator piston rod P/N 114256323 on a MLG 

retraction actuator, in accordance with the instructions of Airbus SB 

A340-32-4213 revision 01 constitutes an acceptable method to comply 
EASA AD No : 2011-0178R1 

EASA Form 110 Page 6/6 

with the requirements of paragraphs (1), (2), (3), (4), (6) and (7) of this 

AD for that MLG retraction actuator. 

B) New Requirements of this AD: 

(9) For all aeroplanes listed in the applicability section of this AD, within 48 

months after the effective date of this AD at original issue, modify the lefthand and right-hand MLG retraction actuators in accordance with the 

instructions of Airbus SB A340-32-4222 Revision 03.

(10) Aeroplanes on which, before the effective date of this AD at original 

issue: 

 - a MLG retraction actuator has been modified in accordance with the 

instructions of Airbus SB A340-32-4222 Revision 01 or Revision 02, 

 or, 

 - a MLG retraction actuator has been modified in accordance with the 

instructions of Airbus SB A340-32-4222 at original issue and re-identified 

in accordance with the instructions of Airbus SB A340-32-4222 Revision 

01 or Revision 02 

 are compliant with the requirements of paragraph (9) of this AD for that 

MLG retraction actuator. 

(11) Modification of a MLG retraction actuator as required by paragraph (9) of 

this AD constitutes terminating action for all repetitive requirements of this 

AD for that MLG retraction actuator. 

Ref. Publications: Airbus SB A340-32-4212 Revision 05 dated 26 September 2008. 

Airbus SB A340-32-4213 Revision 01 dated 16 September 2005. 

Airbus SB A340-32-4222 Revision 03 dated 28 January 2011. 

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD. 

Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. The original issue of this AD was posted on 07 July 2011 as PAD 11-065 

for consultation until 04 August 2011. The Comment Response 

Documents can be found at http://ad.easa.europa.eu/. 

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu. 

4. For any question concerning the technical content of the requirements in 

this AD, please contact: AIRBUS – Airworthiness Office – EIAL; 

Fax: +33 5 61 93 45 80. E-mail: airworthiness.A330-A340@Airbus.com.