EASA AD No.: 2012-0274

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0274

Date: 21 December 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 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):

A330 and A340-200/-300 aeroplanes

TCDS Numbers: EASA.A.004 and EASA.A.015

Foreign AD: Not applicable

Supersedure: None

ATA 52 Doors – Forward and Aft Cargo Compartment Doors –Inspection /

Repair

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, 

A330-243F, A330-301, A330-302, A330-303, A330-321, A330-322, A330-323, 

A330-341, A330-342 and A330-343 aeroplanes, all manufacturer serial numbers

(MSN).

Airbus A340-211, A340-212, A340-213, A340-311, A340-312 and A340-313 

aeroplanes, all MSN.

Reason: One A330 operator recently reported a case where two adjacent frame (FR) forks 

of a forward cargo door were found cracked. FR20B was found cracked through, 

FR21 was found cracked half through. At the time of the findings, the affected

aeroplane had accumulated around 21 000 flight cycles (FC) and it had already 

been inspected in accordance with EASA AD 2011-0007R1and ALI Task 

523106-01-1. However, during those inspections, the forward cargo door handle 

access panel is not required to be removed, which explains why the cracks at 

these two internal frame locations were not detected.

After further analysis, it was determined that, in case of cracked or ruptured 

(forward or aft) cargo door frame, the loads will be transferred to the remaining 

structural elements. However, the second load path is able to sustain the loads 

for a limited number of flight cycles only.

This condition, if not detected and corrected, could lead to rupture of two vertical 

frames, resulting in reduced structural integrity of the forward or aft cargo door.

To address this condition, Airbus issued four separate Alert Operators
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Transmissions (AOT), giving instructions for repetitive inspections of the affected 

areas.

For the reasons described above, this AD requires repetitive detailed visual 

inspections of aft cargo door at FR60 and FR60A and forward cargo door at 

FR21 and FR20B, where the cargo door handle access panels are located, as 

follow:

- outer skin rivets for sheared, loose or missing rivets at frame fork ends,

- whole inner forks for cracks and for sheared, loose or missing rivets at frame 

web and flange after removal of handle access panels, and

the accomplishment of the applicable corrective actions.

Note: Accomplishment of the above inspections does not cancel 

accomplishment of the inspections as required by EASA 2011-0007R1, 

nor accomplishment of those in accordance with ALI Task 523106-01-1.

Effective Date: 28 December 2012

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Paragraph (1) is applicable to A330 aeroplanes up to MSN 0162 inclusive, except 

those on which Airbus SB A330-52-3044 has been embodied in service and to 

A340 aeroplanes up to MSN 0164 inclusive, except those on which Airbus SB 

A340-52-4054 has been embodied in service.

(1) Before the accumulation of 15 800 FC since the aeroplane first flight or 

within 100 FC after the effective date of this AD, whichever occurs later, and 

thereafter at intervals not to exceed 400 FC, accomplish a detailed visual 

inspection of outer skin rivets and whole inner forks at the frame fork end of

FR60 and FR60A of the Aft cargo door in accordance with the instructions of 

AOT A330-A52L001-12 or A340-A52L002-12, as applicable to aeroplane 

type.

Paragraphs (2) to (4) are applicable to all aeroplanes.

(2) Within the compliance time defined in Table 1 of this AD and thereafter, at 

intervals not to exceed 800 FC, accomplish a detailed visual inspection of

outer skin rivets and whole inner forks at the frame fork end of FR21 and 

FR20B of the forward cargo door in accordance with the instructions of AOT 

A330-A52L003-12 or A340-A52L004-12, as applicable to aeroplane type.

Table 1 – Forward Cargo Door Inspections

FC accumulated from the 

aeroplane first flight, on the

effective date of this AD

Compliance time 

less than 18 400 FC

Before the accumulation of 10 600 

FC from the aeroplane first flight, or 

within 100 FC after the effective date 

of this AD, whichever occurs later

equal to or more than 18 400 

FC 

Within 50 FC after the effective date 

of this AD.

(3) If, during any of the inspections as required by this AD, a discrepancy is 

found, before next flight, contact Airbus to obtain the necessary approved

repair instructions for corrective action and accomplish those instructions

accordingly.

(4) Repair of forward and/or aft cargo door(s) in accordance with the repair 

instructions as required by paragraph (3) of this AD does not constitute 
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terminating action for repetitive actions of this AD for that cargo door, unless 

it is specified in the repair instruction.

Ref. Publications: Airbus AOT A330-A52L001-12 dated 03 December 2012.

Airbus AOT A340-A52L002-12 dated 03 December 2012.

Airbus AOT A330-A52L003-12 dated 03 December 2012.

Airbus AOT A340-A52L004-12 dated 03 December 2012.

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. Based on the required actions and the compliance time, EASA have decided 

to issue a Final AD with Request for Comments, postponing the public 

consultation process until after publication.

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 – EIAL; E-mail: 

airworthiness.A330-A340@airbus.com.