EASA AD No.: 2014-0228

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0228

Date: 20 October 2014

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):

A330 and A340 aeroplanes

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

Foreign AD: Not applicable

Supersedure: None

ATA 52 Doors – Forward Cargo Door Beam 3 Area – Inspection

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), except those on which Airbus modification 202702 has been 

embodied in production, and

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

A340-541, A340-542, A340-642 and A340-643 aeroplanes, all MSN.

Reason: An A330 aeroplane operator reported recently cases of crack findings on two 

different aeroplanes, at frame 20A and at frame 20B close to beam 3 of the 

forward cargo door. The first finding was detected during scheduled 

maintenance, while the second one was found during an inspection prompted 

by the first finding. Subsequent analyses of these cracks identified that the first 

crack initiated at frame 20B, which is the first primary load path, leading to 

excessive loads at frame 20A and consequent cracking. Nevertheless, on the

other aeroplane, a crack was detected on frame 20A only. Rupture of both 

frames 20A and 20B could lead to frame 21 failure after a limited number of 

flight cycles (FC).

This condition, if not detected and corrected, may potentially result in the loss of 

structural integrity of the forward cargo door, which could ultimately jeopardise 

the aeroplane’s safe flight.

Prompted by these findings, Airbus issued Alert Operators Transmission (AOT) 

A52L010-14 to provide instructions for a one-time inspection of frames 20A, 
EASA AD No.: 2014-0228

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20B and 21 in the area of beam 3, until the half pitch between beam 2 and 

beam 3.

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

Number (P/N) of the affected forward cargo doors, a one-time detailed 

inspection (DET) of each affected door and, depending on findings, 

accomplishment of applicable corrective action(s).

This AD is considered to be an interim action and further AD action may follow.

Effective Date: 03 November 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 200 FC after the effective date of this AD, accomplish a DET of the 

forward cargo door, having a P/N as listed in Table 1 of this AD, at frames 

20A, 20B and 21 areas located above beam 3, from outside and inside in 

accordance with the instructions of Airbus AOT A52L010-14.

Table 1 – Affected forward cargo door P/N

F523-70500-000 F523-70500-010 F523-70550-002

F523-70500-004 F523-70500-012 F523-70550-004

F523-70500-006 F523-70500-014 F523-70550-008

F523-70500-008 F523-70550-000 F523-70550-050

(2) If, during the DET as required by paragraph (1) of this AD, a discrepancy is 

found, before next flight, contact Airbus for approved instructions (repair, 

additional NDT inspection and/or part replacement) and, within the 

compliance time specified in those instructions, accomplish those 

instructions accordingly.

(3) Within 30 days after the accomplishment of a DET as required by 

paragraph (1) of this AD, report the results (including no findings) to Airbus.

(4) From the effective date of this AD, it is allowed to install a forward cargo 

door having a P/N listed in Table 1 of this AD, provided that, prior to 

installation on an aeroplane, the door is inspected and, depending on

findings, corrected in in accordance with the instructions of Airbus AOT 

A52L010-14.

Ref. Publications: Airbus AOT A52L010-14 dated 30 September 2014.

The use of later approved revisions of this document 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, Certification 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.