EASA AD No.: 2014
- 0228

TE. CAP.00110

- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## 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 E U 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 ope rate an aircraft to which an AD applies, except in accordance with the requ irements 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 Number s : EASA.A.004, EASA.A.015
F oreign 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

- 223 F, A330

- 243, A330

- 243 F, 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 ha s 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 f irst finding was detected during scheduled maintenance , while t he second one was found during an i nspection prompted by the first finding. S ubsequent analyses of these cracks identified that the fir st crack initiate d at frame 20B , which is the first primary load path, leading to excessive loads at frame 20A and consequent cracking. Nevertheless, on the o ther aeroplane, a crack w as detected on frame 20A only. R upture 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 th ese 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

TE. CAP.00110

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 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 door s, a one - time detai led 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: 0 3 November 2014 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) W ithin 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. Public ations: Airbus AOT A52L010

- 14 dated 30 September 2014

. The u se 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 t he 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 A D 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

.