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 b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an Community, its Member States and of the European third countries that participate in th e 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 en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accor dance with the requirements of that AD, unless othe rwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, 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superseded EASA AD 2006-0301R2 dated 10 September 2 009.



### ATA 32 Landing Gear – Main Landing Gear Retraction Actuato r 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 prod uction 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 ret raction actuator P/N 114256002-055, which is mentioned in the accomp lishment instructions of Airbus Service Bulletin (SB) A340-32-4222 Revisi on 03. Aeroplanes on which Airbus mod. 54500 has been embo died in production are not affected by this AD.

Reason: During an approach phase, the flight crew o f an A330 aeroplane had to perform a free-fall extension of the left-hand (LH) MLG. Rupture of the LH MLG retraction actuator piston ro d was found near the rod attachment point. The inspection revealed at th e location of the rupture the presence of corrosion resulting from incorrect application of the anticorrosion protection, and circumferential cracks re sulting from normal operational loading effects. Since the above rupture, new cases of crack propaga tion along the length of the piston rod occurred. These ruptures led to a no n-damped extension of the landing gear. Fully extended, the landing gear asse mbly was submitted to high loads jeopardising its structural integrity. This condition, if not detected and corrected, coul d lead to MLG failureEASA 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 200 5-5888) to address this unsafe condition. Since that AD was issued, th e 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 whi ch represents a potential source of high magnitude tensile hoop stresses in t he material of the rod, leading to propagation of longitudinal crack in the body of the piston rod. Prompted by these findings, EASA issued AD 2006-030 1, partially retaining the requirements of DGAC France AD F-2005-099, whic h was superseded, and to revise the inspection requirements as follow s: a. Extend the repetitive inspections interval for t he removal of fluid from the internal volume of the piston rod using flight cycl es in lieu of flight hours as this better represents the mechanism for the accumu lation of water within the piston rod. b. Remove the preliminary visual inspection from th e ultrasonic longitudinal inspection of the upper end of the piston rod. c. Add a new one-time ultrasonic longitudinal and c ircumferential inspection of the full piston rod length to eliminate any part s that exhibit severe corrosion along the internal length of the piston r od. d. Require installation of new design hollow piston rod Part Number (P/N) 114256328 (Airbus mod. 52980 - SB A340-32-4222 Revi sion 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 typographi cal errors and to add reference to Airbus SB A340-32-4212 Revision 04, an d - at revision 02 to extend the inspections threshol d from 3 to 6 years in service usage for retraction actuator piston rod P/N 114256 321 issue 06 which was re-identified to P/N 114256326 issue 01 in accordan ce with the instructions of Airbus SB A340-32-4260. More recently, the sampling of piston rod P/N 11425 6326 issue 1 and P/N 114256321 issue 06 have confirmed the need to repla ce all retraction actuator piston rods with a piston rod P/N114256328. For the reasons described above, this AD at origina l issue retained the requirements of EASA AD 2006-0301R2, which is super seded, and required the replacement of all retraction actuator piston r ods 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 wh ich Airbus mod. 52980 has been embodied in production are not required to acc omplish the reidentification of MLG retraction actuator P/N 11425 6002-055 which is mentioned in the accomplishment instructions of Air bus SB A340-32-4222 Revision 03

. This AD has been republished to correct a typograph ical mistake of the applicable Airbus SB number in the Applicability (i n 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 accomplish ed: 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 dat e 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 a nd P/N 114256321 issue 03, upon accumulation of three years of use i n service, and (b) Retraction actuator piston rods P/N 114256326 i ssue 01 and P/N 114256321 issue 06, upon accumulation of six years of use in service: (1) Detailed visual inspection of the retraction actuat or piston rod: For each concerned retraction actuator piston rod not yet visually inspected in accordance with the instructions of Ai rbus 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 thr ee 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 instructi ons of Airbus SB A340-32-4212 Revision 01, or Revision 02, or Revisi on 03, or Revision 04, or Revision 05, within 8 days from the last vis ual inspection performed in accordance with the instructions of SB A340-32-4212 Revision 01, or Revision 02, or Revision 03, or Rev ision 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 Rev ision 05. (1.3) If, during any inspection required by paragra phs (1.1) and (1.2) of this AD, one or more cracks are found, before ne xt 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 requir ed to comply with paragraph (1) of this AD after accomplishment of dr ainage of the fluid from the piston as required by paragraph (2) of this AD in a ddition 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 ve nt hole: For each concerned retraction actuator piston rod not yet inspected/fluiddrained in accordance with the instructions of Airb us 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 inst ructions of Airbus SB A340-32-4212 at Revision 02, or Revision 03, or Rev ision 04, or Revision 05, within 1 000 flight cycles (FC) or 24 months, whichever occurs first, from the last inspection/fluid-draina ge performed in accordance with the instructions of Airbus SB A340- 32-4212 at Revision 02, or Revision 03, or Revision 04, or Rev ision 05, (2.1) Do the procedure to drain fluid from the retr action actuator piston rod internal volume and seal the vent hole in accor dance 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 theEASA AD No : 2011-0178R1

EASA Form 110 Page 4/6 vent hole required by paragraph (2.1) of this AD, i n accordance with the instructions of Airbus SB A340-32-4212 Rev ision 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-ti me-ultrasonic NDT inspection of the full length of the piston as required by par agraph (4) of this AD, constitutes terminating action for the repetitive v isual inspections required by paragraph (1) of this AD. (3) Ultrasonic NDT inspection of the upper end of the p iston 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 si x years, as applicable, of in service usage,

or, for each concerned retraction actuator piston rod already NDT inspected in accordance with the instructions of Ai rbus SB A340-32- 4212 at original issue, or at Revision 01, or Revis ion 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 per formed in accordance with the instructions of Airbus SB A340- 32-4212 at original issue, or at Revision 01, or Revision 02, or Revisi on 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 S B 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 He ight) and between 5 and 7 in Time Base, before next flight, r eplace 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 b etween 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 a nd 7 in Time Base, repeat the inspections required by parag raph (3.1) of this AD at intervals not exceeding 1 400 flight hou rs (FH) or 250 FC or 4 months, from the previous inspection, which ever occurs first, and do the applicable corrective actions. (4) One-time ultrasonic (longitudinal and circumferenti al) NDT inspections of the full length of the piston rod: (a) At the latest when each concerned retraction ac tuator 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 2006-03 01R2] 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 inspe ction of the chromium-plated area (full length) of the piston ro d 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 in spection of the chromium-plated area (full length) of the piston ro d, in accordance with the instructions of Airbus SB A340- 32- 4212 Revision 05. (4.2.2) If the results of the inspection required b y 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 fli ght replace the retraction actuator. (4.2.3) If the results of the inspection required b y paragraph (4.2.1) of this AD give an indication between 75 an d 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 b y 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 i s required.

Note 3 : Accomplishment of the one-time-ultrasonic NDT ins pection 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 pisto n 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 replacem ent 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 th e instructions of Airbus SB A340-32-4212 Revision 03, or Revision 04, are co mpliant with the initial requirements of paragraph (1), (2), (3), (4 ) and (5) of this AD. However, after the effective date of this AD at ori ginal issue, the repetitive inspections or draining must be accomplished in acc ordance with the instructions of Airbus SB A340-32-4212 Revision 05. (7) Modification Not later than 31 December 2007, remove and replac e 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 instruc tions of Airbus SB A340-32-4213 revision 01 constitutes an acceptable method to complyEASA 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 origi nal issue, modify the lefthand and right-hand MLG retraction actuators in acc ordance 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 a ccordance with the instructions of Airbus SB A340-32-4222 Revision 01 or Revision 02,

or, - a MLG retraction actuator has been modified in a ccordance with the instructions of Airbus SB A340-32-4222 at original issue and re-identified in accordance with the instructions of Airbus SB A3 40-32-4222 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 r equired by paragraph (9) of this AD constitutes terminating action for all repe titive 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 Septemb er 2005. Airbus SB A340-32-4222 Revision 03 dated 28 January 2011. The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. The original issue of this AD was posted on 07 J uly 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 t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: AIRBUS – Airworthiness Off ice – EIAL; Fax: +33 5 61 93 45 80. E-mail: airworthiness.A330-A340@Airbus.com

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