EASA AD No : 2012-0118

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0118

Date: 04 July 2012

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 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 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 2007-0161 dated 11 June 2007.

ATA 53 Fuselage – Centre Fuselage / Main Landing Gear (MLG) Door Keel 

Beam Hinge and Actuator Fittings – Inspection

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: Several cases of cracks have reportedly been found on the MLG door hinge 

fitting and on the MLG door actuator fitting on the keel beam.

This condition, if not detected and corrected, could lead to in-flight detachment

of a MLG door, possibly resulting in injury to persons on the ground and/or 

damage to the aeroplane.

To address this potential unsafe condition, EASA issued EASA AD 2007-0161, 

to require a one-time inspection of the affected fittings and accomplishment of 

the applicable corrective actions.

Since that AD was issued, some cracks have been found on fittings that had 

successfully passed the one-time inspection as required by EASA AD 2007-

0161. Analyses of these cracks have lead Airbus to reconsider the repetitive 

inspections of the MLG door hinge and actuator fittings on the keel beam, in 

accordance with the ALI task 533154-02-1 requirement as defined in Airbus 

A318/A319/A320/A321 Airworthiness Limitation Items (ALI) Document, by 

introducing more restrictive inspection thresholds and intervals.

For the reasons stated above, this AD, which supersedes EASA AD 2007-
EASA AD No : 2012-0118

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0161 and the ALI task 533154-02-1 requirements, expands the AD 

applicability to all A318/A319/A320/A321 aeroplanes and requires repetitive 

inspections of the MLG door hinge and actuator fittings on the keel beam at a 

new threshold and interval and, depending on findings, the accomplishment of 

applicable corrective actions.

Effective Date: 18 July 2012

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously :

(1) Initially, within the compliance time indicated in Table 1 of this AD, and 

thereafter at intervals not to exceed 2 250 flight cycles (FC), accomplish 

Detailed Visual, High Frequency Eddy Current (HFEC) and Ultrasonic 

inspections of the left-hand (LH) and right-hand (RH) MLG door actuator

fittings on the keel beam, in accordance with the instructions of Airbus 

Service Bulletin (SB) A320-53-1195 Revision 03.

Table 1 – Compliance Time - A or B, whichever occurs later

Airbus SB A320-53-1195 Revision 03

A Before the accumulation of 3 000 FC since the 

aeroplane first flight, or within 2 250 FC after the last 

inspection in accordance with the instructions of 

Airbus SB A320-53-1195 (at any revision), or ALI task 

533154-02-1, as applicable.

B Within 1 500 FC after the effective date of this AD.

(2) Initially, within the compliance time indicated in Table 2 of this AD, and 

thereafter at intervals not to exceed 3 000 FC, accomplish Detailed Visual 

and HFEC inspections of the LH and RH MLG door hinge fittings on the 

keel beam, in accordance with the instructions of Airbus SB A320-53-1196 

Revision 02.

Table 2 – Compliance Time - A or B, whichever occurs later

Airbus SB A320-53-1196 Revision 02

A Before the accumulation of 3 000 FC since the 

aeroplane first flight, or within 3 000 FC after the last 

inspection in accordance with the instructions of 

Airbus SB A320-53-1196 (at any revision), or ALI task 

533154-02-1 as applicable.

B Within 1 500 FC after the effective date of this AD

(3) If, during any inspection as required by paragraph (1) or (2) of this AD, 

any discrepancy (as defined in Airbus SB A320-53-1195 Revision 03 or 

Airbus SB A320-53-1196 Revision 02, as applicable) is found, before next 

flight, depending on findings, accomplish the applicable corrective actions 

in accordance with the instructions of Airbus SB A320-53-1195 Revision 

03, or Airbus SB A320-53-1196 Revision 02, as applicable.

(4) The accomplishment of a corrective action on an aeroplane, as required 

by paragraph (3) of this AD, does not constitute terminating action for the 

repetitive inspection requirements of this AD for that aeroplane.

(5) For aeroplanes for which a Repair Approval Sheet (RAS) has been issued 

by Airbus to cover findings from an inspection performed before the 

effective date of this AD in accordance with the instructions of Airbus SB 

A320-53-1195 or Airbus SB A320-53-1196 or ALI task 533154-02-1 
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requirements, the RAS instructions must be accomplished. Thereafter, the 

repetitive inspection requirements of paragraph (1) and (2) of this AD are 

applicable.

(6) From the effective date of this AD, complying with the requirements of this 

AD cancels the ALI task 533154-02-1 requirements.

Ref. Publications: Airbus SB A320-53-1195 Revision 03, dated 08 November 2011.

Airbus SB A320-53-1196 Revision 02, dated 08 November 2011.

Airbus A318/A319/A320/A321 ALI document reference AI/SEM4/95A.0252/96 issue 11, approved by EASA on 09 November 2010.

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 30 April 2012 as PAD 12-039 for consultation until 

28 May 2012. 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.