EASA AD No.: 2013-0288

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0288

Date: 06 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

Supersedure: This AD supersedes EASA AD 2011-0069R1 dated 11 April 2012, and EASA 

Emergency AD 2013-0132-E dated 25 June 2013.

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

Inspection / Replacement / Modification

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

opening/closing sequence, leading to the generation of 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 corrected, could prevent 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.

EASA AD 2006-0112R1 was issued to require repetitive inspections of the 

opening sequence of the MLG door in order to identify the defective actuators, 

and to introduce as an optional terminating action Airbus production Modification
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(MOD) 38274 and associated Service Bulletin (SB) A320-32-1338, which 

incorporate an improved retaining ring, located on the piston rod's extension end, 

and a new piston rod with machined shoulder to accommodate the thicker section 

of the modified retaining ring.

After in-service introduction of the new MLG door actuator, Part Number (P/N)

114122012 (Post MOD 38274 – SB A320-32-1338), several operators reported 

failures of internal parts of the MLG door actuator. Investigations confirmed that 

these failures could result in slow extension of the actuator rod, delaying the MLG 

door operation, or possibly stopping just before the end of the stroke, preventing 

the door to reach the fully open position.

EASA AD 2011-0069R1, which supersedes EASA AD 2006-0112R1, required an 

amendment of the applicable Airplane Flight Manual (AFM), repetitive checks of 

specific Centralized Fault Display System (CFDS) messages, repetitive 

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

findings, corrective action(s).

Since that AD was issued, Airbus introduced a reinforced MLG door actuator P/N 

114122014 (MOD 153655). Airbus issued SB A320-32-1407 containing 

instructions for in-service replacement of the affected MLG door actuators, or 

modification of the actuators to the new standard.

In addition, following a recent occurrence with a gear extension problem, the 

result of additional analyses by Airbus revealed that the CFDS expected specific 

messages may not be 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 MOD 39303, or in service through Airbus SB A320-32-1409), in 

combination with LGCIUs 80-178-02-88012 or 80-178-03-88013 in both positions 

and at least one MLG door actuator pre MOD 153655 (SB A320-32-1407 – SB 

114122-32-105) installed.

Prompted by these findings, EASA issued Emergency AD 2013-0132-E to require 

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.

That AD also provided an optional terminating action by disconnection of the 

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

Airbus SB A320-32-1407 (equivalent to production MOD 153655).

Since those ADs were issues, analyses performed by Airbus have revealed that 

the MLG door opening sequence inspection interval must be reduced, and that 

the (previously optional) terminating action must be made mandatory.

For the reasons described above, this AD retains the requirements of EASA 

AD 2011-0069R1 and AD 2013-0132-E, which are superseded, but with reduced

inspection intervals, and requires replacement or modification, as applicable, of 

the affected MLG door actuators as terminating action for the monitoring,

repetitive checks and inspections.

Effective Date: 20 December 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Restatement of the requirements of EASA AD 2011-0069R1:

Note 1: The inspection interval of paragraph (6) has been reduced, as compared 

to the requirements of EASA AD 2011-0069R1, and reference is made to the 

instructions of Airbus SB A320-32-1390 Revision 02.

Operational procedure

(1) Within 14 days after 02 May 2011 [the effective date of the original issue of 

EASA AD 2011-0069], amend the applicable AFM to incorporate the 

operational procedure as specified below, and thereafter, operate the 
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aeroplane accordingly.

● If ECAM triggers the “L/G GEAR NOT DOWNLOCKED” 

warning, apply the following procedure:

Recycle landing gear.

● If unsuccessful after 2 min:

Extend landing gear by gravity.

Refer to ABN-32 L/G GRAVITY EXTENSION.

Inserting a copy of this AD into the AFM is an acceptable method to comply 

with the requirement of paragraph (1) of this AD.

Note 2: This operational procedure was introduced in a global AFM revision 

approved by EASA on 04 April 2011.

Note 3: For an aeroplane in a configuration as defined in paragraph (10) of this 

AD, some additional actions are required – see paragraph (15) of this AD to avoid 

duplication of actions.

Post Flight Report (PFR) Monitoring: Paragraphs (2) through (9) of this AD apply 

only to aeroplanes with a MLG door actuator installed, having a P/N as listed in 

Table 1 of this AD.

(2) Within 14 days after 02 May 2011 [the effective date of the original issue of 

EASA AD 2011-0069], or before the accumulation of 800 FC since 

aeroplane first flight, whichever occurs later, monitor the PFR to check the 

CFDS messages triggered during the last 8 calendar days in accordance 

with the instructions of paragraph 4.2.1 of Airbus All Operator Telex (AOT) 

A320-32A1390.

(3) Thereafter, at intervals not to exceed 8 calendar days or 5 FC, whichever 

occurs later, check the CFDS messages recorded during each interval in 

accordance with the instructions of paragraph 4.2.1 of Airbus AOT

A320-32A1390.

(4) If, during any of the PFR monitoring checks as required by paragraphs (2) 

and (3) of this AD, a pair of the specific CFDS messages as listed in 

paragraph 4.2.1 of Airbus AOT A320-32A1390 has been triggered by both 

Landing Gear Control and Indication Units (LGCIU) for the same flight, 

before next flight, inspect the door opening sequence of the affected doors 

of the MLG in accordance with the instructions of Airbus SB A320-32-1390

Revision 02.

Repetitive inspections of the door opening sequence of the Left Hand (LH) 

and Right Hand (RH) doors of the MLG in accordance with the instructions 

of Airbus SB A320-32-1390 Revision 02 are an acceptable alternative 

method of compliance for the actions required by paragraph (3) of this AD.

(5) The use of an alternative method to check the list of CFDS messages (such 

as AIRMAN) is acceptable in lieu of the PFR monitoring required by 

paragraphs (2) and (3) of this AD, provided that this alternative method has 

been approved by the National Authority of the State of Registry of the 

aeroplane and that the list of the CFDS messages can be conclusively 

identified from that check.

MLG Door Actuator Opening Sequence Inspection

(6) Within 800 FC after 02 May 2011 [the effective date of the original issue of 

EASA AD 2011-0069] and, thereafter, at intervals not to exceed 8 calendar 

days or 5 FC, whichever occurs later, without exceeding 425 FC since last 

inspection (previous interval as required by EASA AD 2011-0069R1), 

inspect the door opening sequence of the LH and RH doors of the MLG in 

accordance with the instructions of Airbus SB A320-32-1390 Revision 02.
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 In case an aeroplane is not operated for a period longer than 8 days, 

accomplish the next inspection as required by paragraph (6) of this AD 

before next flight.

(7) If, during any inspection as required by paragraph (4) or (6) of this AD, as 

applicable, any discrepancy is found, before next flight, replace the affected 

MLG door actuator in accordance with the instructions of Airbus SB

A320-32-1390 Revision 02.

(8) MLG door opening sequence inspections and corrective actions, 

accomplished before the effective date of this AD in accordance with the 

instructions of Airbus AOT A320-32A1390, or those of Airbus SB

A320-32-1390 at Revision 01, are acceptable to comply with the initial 

requirements of paragraphs (4), (6) and (7) of this AD, as applicable.

Restatement of the requirements of EASA AD 2013-0132-E:

Note 4: The inspection interval of paragraph (10) has been reduced, as compared 

to the requirements of EASA AD 2013-0132-E.

(9) Before exceeding 800 FC since first flight of the aeroplane, or within 14 

days after 27 June 2013 [the effective date of EASA AD 2013-0132-E], 

whichever occurs later, determine the configuration (modification status) of 

the aeroplane and identify the P/N of both LGCIU and MLG door actuators.

A review of the aeroplane delivery records 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 80-178-02-88012

80-178-03-88013

MLG Door Actuator

114122006

114122007

114122009

114122010

114122011

114122012

(10) If, during the determination and identification as required by paragraph (9) 

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 both LGCIU and at least one 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 (9) 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.

In case an aeroplane is not operated for a period longer than 8 days, 

accomplish the next inspection, as required by paragraph (10) of this AD,

before next flight. 

(11) If, during any inspection as required by paragraph (10) 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.

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

155522 applied in production, or modified in service in accordance with the 
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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 (10) and (11) of this AD, provided that the aeroplane is not 

modified to a configuration as defined in paragraph (10) of this AD.

Note 5: LGCIU interlink reconnection can be done after installation of MLG door 

actuators P/N 114122014 on both LH and RH sides.

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

MLG of an aeroplane, as required by paragraph (10) of this AD, is an 

acceptable alternative method to comply with the requirements of 

paragraphs (2), (3) and (6) of this AD for that aeroplane.

New requirements of this AD:

(14) For aeroplanes with a MLG door actuator P/N 114122012 installed, within

12 months after the effective date of this AD, replace each P/N 114122012 

MLG door actuator in accordance with the instructions of Airbus SB

A320-32-1407, or modify each actuator in accordance with the instructions 

of General Electric (GE) SB 114122-32-105, as applicable.

(15) For aeroplanes with a MLG door actuator installed, having a P/N as listed in 

Table 1 of this AD (except P/N 114122012, see paragraph (14) of this AD), 

within 24 months after the effective date of this AD, replace each MLG door 

actuator with a P/N 114122014 MLG door actuator in accordance with the 

instructions of Airbus SB A320-32-1407, or modify the actuator in 

accordance with the instructions of GE SB 114122-32-105, as applicable.

(16) Modification of an aeroplane as required by paragraph (14) or (15) of this 

AD, as applicable, constitutes terminating action for all repetitive actions 

(PFR monitoring checks and inspections) required by this AD for that 

aeroplane.

(17) Replacement of a MLG door actuator as required by paragraph (7) or (11)

of this AD, or corrective actions as specified in paragraph (8) of this AD, do

not constitute terminating action for the repetitive inspections required by 

paragraph (3) or (6) or (11) 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 paragraphs (10) and 

(11) of this AD.

(18) An aeroplane 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 or GE SB 114122-32-105) is not affected by the 

requirements of paragraphs (2) to (15) of this AD, provided that since first 

flight, or since modification, as applicable, no MLG door actuator with a P/N 

as listed in Table 1 of this AD, has been installed on that aeroplane.

(19) Do not install on any aeroplane a MLG door actuator, having a P/N as listed 

in Table 1 of this AD, as required by paragraph (19.1) or (19.2) of this AD, 

as applicable.

(19.1) For aeroplanes that must comply with paragraph (14) or (15) of this 

AD: after modification of the aeroplane.

(19.2) For aeroplanes that, on the effective date of this AD, do not have a

MLG door actuator installed with a P/N as listed in Table 1 of this 

AD: from the effective date of this AD.

Ref. Publications: Airbus AOT A320-32A1390 original issue dated 10 February 2011.

Airbus SB A320-32-1390 Revision 01 dated 21 September 2011, or Revision 02 

dated 23 October 2013.
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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.

GE SB 114122-32-105 original issue dated 17 January 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. This AD was posted on 21 August 2013 as PAD 13-125 for consultation until 

18 September 2013, republished on 25 September 2013 as PAD 13-125R1

for consultation until 09 October 2013, and republished on 13 November 

2013 as PAD 13-125R2 for consultation until 27 November 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.