EASA AD No.: 2013-0283R1

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0283R1

[Correction: 11 December 2013]

Date: 09 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 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].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign 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 (formerly 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 aeroplanes, all manufacturer serial numbers.

Reason: During routine pre-flight inspection of an Airbus A319, a hydraulic fluid leak 

was detected, coming from the retraction actuator of the main landing gear 

(MLG). The results of subsequent investigations revealed that a galvanic 

difference between materials induced an internal corrosion which was the 

crack initiator of the component. Actuators from 201590 series were identified

as potentially affected, unless inspected and corrected during MLG overhaul.

This condition, if not detected and corrected, could lead to retraction actuator 

failure, preventing 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.

For the reason described above, EASA AD 2013-0283 was issued to require

a one-time identification and replacement of each affected MLG retraction 

actuator.
EASA AD No.: 2013-0283R1

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EASA AD 2013-0283R1 was issued to introduce the correct Maintenance 

Review Board Report (MRBR) task number and to add modification numbers 

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 Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 18 months after the effective date of this AD, inspect each MLG 

retraction actuator to determine whether the Part Number (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 instructions of Airbus SB 

A320-32-1408.

A review of aeroplane delivery or maintenance records is acceptable to 

make the identification 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 occurred 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 months after the effective date of this AD, replace each MLG 

retraction 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 instructions of Airbus SB A320-32-1408.

(3) An aeroplane that does 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, installation 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. Publications: Airbus SB A320-32-1408 original issue, dated 22 July 2013.

Airbus A318/A319/A320/A321 MRBR, currently at Revision 18, dated March 

2013.
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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 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 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 – EIAS,

Fax +33 5 61 93 44 51, E-mail: account.airworth-eas@airbus.com.