EASA AD No .: 20 13

- 0283 R1

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No
. : 2013 - 0283 R1 [Correction: 11 December 2013]

Date: 0 9 December 2013

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 EU 748/2012, Part 21.A.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 ope rate 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) exempt ion]. 

### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A318, A319, A320 and A321 aeroplanes
TCDS Number: EASA.A.064
F oreign AD: Not applicable
Revision : This AD revises EASA AD 2013

- 0283 dated 29 November 2013.



### ATA 32 Landing Gear
– Main Landing Gear Retraction Actuator
–

Inspection / Replacement
Manufacturer(s): Airbus (f ormerly Airbus Industrie) Applicability: Airbus A318

- 111, A318

- 112, A318

- 121, A318

- 122, A319

- 111, A319

- 112, A319

- 113, A319

- 114, A319

- 115, A319

- 131, A319

- 132, A319

- 133, A320

- 211, A320

- 212, A320

- 214, A320

- 215, A320

- 216, A320

- 231, A320

- 232, A320

- 233, A321

- 111, A321

- 112, A321

- 131, A321

- 211, A321

- 212, A321

- 213, A321

- 231 and A321

- 232 aeroplane s , all manufacturer serial number s

. Reason: During routine pre

- flight inspection of an Airbus A319, a hy draulic fluid leak w as detected, coming from the retraction actuator of the m ain l anding g ear (MLG). The results of subsequent investigations revealed that a galvanic difference between materials induce d an internal corrosion which wa s the crack initiator of the component. A ctuators from 201590 series we re identified a s potentially affected , unless inspected and corrected during MLG overhaul

. This condition, if not detected and corrected , could lead to retraction actuator failure, prevent ing the full extension and/or down

- locking of the MLG, possibly resulting in MLG collapse during landing or rollout and consequent damage to the aeroplane and injury to occupants. To address this potential unsafe condition, Airbus published Service Bulletin ( SB) A320

- 32

- 1408, providing instructions to identify and replace the affected actuators that have already exceeded 20 000 flight cycles ( FC ) or 10 years of operation since new , or since last overhaul

. F o r the reason describe d above, EASA AD 2013

- 0283 was issued to require a one - time identification and replacement of each affected MLG retraction actuator

.EASA AD No .: 20 13

- 0283 R1

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. EASA AD 2013

- 0283 R1 wa s issued to introduce the correct Maintenance Review Board Report (MRBR) task number and to add modification number s in paragraph (3), and to introduce some editorial changes for clarification. This AD is re - published to correct paragraph (3).
Effective Date: Revision 1 (same as original issue): 13 December 2013 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within 18 m onths after the effective date of this AD, i nspect each MLG r etraction actuator to determine whether the P art N umber (P/N) is 201590001, P/N 201590002, P/N 201590002

- 010, P/N 201590002

- 020, or P/N 201590003, and to determine the time in service accumulated by the actuator (see Note 1) and, within the compliance time as specified in Table 1 of this AD, as applicable, replace each actuator with a serviceable actuator in accordance with the instruction s of Airbus SB A320

- 32

- 1408

. A review of aeroplane delivery or maintenance records is acceptable to make the i de ntification and determination as required by paragraph (1) of this AD , provided those records can be relied upon for that purpose, and the P/N and time since first installation or since overhaul, as applicable, of the MLG retraction actuator can be conclusively identified from that review.
Table 1

– MLG Retraction Actuator Replacement Time accumulated (see Note below ) by the actuator on the effective date of this AD Compliance time

Equal to or more than 20 000 FC or 10 years , whichever occur red first Within 18 months after the effective date of this AD Less than 20 000 FC or 10 years Within the limits defined in the MRBR Note: The FC and calendar time are those accumulated since (a) first installation on an aeroplane, or (b) since last actuator overhaul, or (c) since last accomplishment of MRBR task 321147

- 01

- 1 , whichever of (a), (b) or (c) occurred later

. (2) Within 18 m onths after the effective date of this AD, replace e ach MLG r etraction actuator , having a P/N as specified in paragraph (1) of this AD and for which the in

- service history is not known, with a serviceable actuator in accordance with the instruction s of Airbus SB A320

- 32

- 1408. (3) A n a eroplane that do es not have Airbus MOD 26644 or MOD 150820 (all Models) , or MOD 27151 (A321) , applied in production , as applicable, is not affected by the requirements of paragraph (1) or (2) of this AD, provided that no MLG retraction actuator , having a P/N as specified in paragraph (1) of this AD , has been installed on that aeroplane since first flight

. ( 4 ) From the effective date of this AD, install ation on an aeroplane of a MLG retraction actuator that has a P/N as specified in paragraph (1) of this AD is allowed, provided that the MLG retraction actuator has not accumulated or exceeded 20 000 FC or 10 years since new , or since overhaul

. Ref. Public ations: Airbus SB A320

- 32

- 1408 original issue, dated 22 July 2013

. Airbus A318/A319/A320/A321 MRBR , currently at R ev ision 1 8, dated March 2013

.EASA AD No .: 20 13

- 0283 R1

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. The use of later approved revisions of th e s e document s 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. Th e original issue of th is AD was posted on 05 September 2013 as PAD 13

- 134 for consultation until 03 October 2013

. The Comment Response Document can be found at http://ad.easa.europa.eu

. 3. Enquiries regarding this AD should be referred to the Safety Information Section, Executive Directo rate, 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

– E I AS , Fax +33 5 61 93 44 51, E

- mail: account.airworth

- eas@airbus.com

.