EASA AD No.: 2013-0132-E

TE.CAP.00111-003 © European Aviation Safety Agency. All rights reserved. 1/3

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2013-0132-E

Date: 25 June 2013

Note: This Emergency 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 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].

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

Supersedure: None

ATA 32 Landing Gear – Main Landing Gear Door Actuator / Control 

Interface Unit Interlink – Inspection / Disconnection

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, A320-111, 

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: Some operators reported slow operation of the main landing gear (MLG) door 

opening/closing sequence, leading to the generation of Centralized Fault 

Display System (CFDS) messages/ECAM warnings during the landing gear 

retraction or extension sequence. Investigations showed that the damping ring 

and associated retaining ring of the MLG door actuator deteriorate. The 

resultant debris increases the friction inside the actuator which can be 

sufficiently high to restrict opening of the MLG door by gravity, during operation 

of the landing gear alternate (free-fall) extension system.

This condition, if not detected and corrected, could prevent the full extension 

and/or down-locking of the MLG, possibly resulting in MLG collapse during 

landing and consequent damage to the aeroplane and injury to occupants.

To address this potential unsafe condition, EASA issued AD 2011-0069 

(currently at R1) to require an amendment of the applicable Airplane Flight 

Manual (AFM), repetitive checks of specific CFDS messages, and repetitive 

inspections of the opening sequence of the MLG door actuator and, depending 

on findings, corrective action.
EASA AD No.: 2013-0132-E

TE.CAP.00111-003 © European Aviation Safety Agency. All rights reserved. 2/3

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Since that AD was issued, following a recent occurrence with a gear extension 

problem, additional analyses by Airbus have revealed that the CFDS expected 

specific messages may be not generated and as a result, repetitive checks of 

messages are not effective for aeroplanes fitted with landing gear control 

interface unit (LGCIU) interlink communication ARINC 429 (applied in 

production through Airbus Modification (mod.) 39303, or in service through 

Airbus Service Bulletin (SB) A320-32-1409), in combination with certain 

LGCIUs and MLG door actuators installed.

For the reasons described above, this Emergency AD requires identification of 

the affected aeroplanes to establish the configuration and, for those 

aeroplanes, repetitive inspections of the opening sequence of the MLG door 

actuator and, depending on findings, replacement of the MLG door actuator.

This AD also provides optional terminating action by disconnection of the 

interlink for certain LGCIUs, or in-service modification of the aeroplane by 

installation of MLG actuator Part Number (P/N) 114122014 through Airbus SB

A320-32-1407 (Airbus production mod. 153655). 

Effective Date: 27 June 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Before exceeding 800 flight cycles (FC) since first flight of the aeroplane, 

or within 14 days after the effective date of this AD, whichever occurs later, 

determine the configuration (modification status) of the aeroplane and 

identify the P/N of left hand (LH) and right hand (RH) LGCIU and MLG 

door actuators.

A review of the aeroplane delivery - or maintenance records is acceptable 

for compliance with the requirements of paragraph (1) of this AD, provided 

the aeroplane configuration and installed components can be conclusively 

determined from that review.

Table 1 – Affected Components

Component name P/N

LGCIU (LH and RH)

80-178-02-88012

80-178-03-88013

MLG door actuator

114122006

114122007

114122009

114122010

114122011

114122012

(2) If, during the determination and identification as required by paragraph (1) 

of this AD, the configuration of the aeroplane is established as post-mod. 

39303 or post-SB A320-32-1409 (Interlink communication ARINC 429

installed), and a LGCIU and a MLG door actuator are installed with a P/N 

as listed in Table 1 of this AD, within the compliance time as defined in 

paragraph (1) of this AD, and thereafter at intervals not to exceed 8 

calendar days or 5 FC, whichever occurs later, inspect the door opening 

sequence of the LH and RH MLG doors in accordance with the instructions 

of Airbus Alert Operator Transmission (AOT) A32N001-13.

(3) If, during any inspection as required by paragraph (2) of this AD, any 

discrepancy is found, before next flight, replace the affected MLG door 

actuator in accordance with the instructions of Airbus AOT A32N001-13.

(4) Replacement of a MLG door actuator as required by paragraph (3) of this 
EASA AD No.: 2013-0132-E

TE.CAP.00111-003 © European Aviation Safety Agency. All rights reserved. 3/3

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

AD does not constitute terminating action for the repetitive inspections 

required by paragraph (2) of this AD, unless MLG door actuators P/N 

114122014 are installed on both LH and RH sides in accordance with the 

instructions of Airbus SB A320-32-1407 (see also paragraph (5) of this 

AD).

(5) An aeroplane on which the LGCIU interlink is disconnected (Airbus 

mod.155522 applied in production, or modified in-service in accordance 

with the instructions of Airbus AOT A32N001-13), or on which MLG door 

actuators P/N 114122014 are installed on both LH and RH sides (Airbus 

mod.153655 applied in production, or modified in-service in accordance 

with the instructions of Airbus SB A320-32-1407) is not affected by the 

requirements of paragraphs (2) and (3) of this AD, provided that the 

aeroplane is not modified to a configuration as defined in paragraph (2) of 

this AD.

(6) Inspection of the door opening sequence of the LH and RH doors of the 

MLG of an aeroplane, as required by paragraph (2) of this AD, is an 

acceptable alternative method to comply with the requirements of 

paragraphs (2), (3) and (6) of EASA AD 2011-0069R1 for that aeroplane.

Ref. Publications: Airbus AOT A32N001-13 original issue, dated 24 June 2013.

Airbus SB A320-32-1409 original issue, dated 19 March 2013.

Airbus SB A320-32-1407 original issue, dated 14 May 2013.

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 results of the safety assessment have indicated the need for 

immediate publication and notification, without the full public consultation 

process.

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.