EASA AD No.: 2013 - 0175

TE. CAP.00110 - 00 3 © 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.: 2013 - 0 175

Date: 02 August 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 Eu ropean 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 a n 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]

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### Design Approval Holder’s Name : AIRBUS Type/Model designation(s): A330 and A340 aeroplanes TCDS Number s : EASA. A.004, EASA

. A.015 Fo reign AD: N ot applicable Supersedure : None 

### ATA 24 Electric al Power – Generator Control Unit – 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 , 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 manufacturer serial numbers (MS N) up to MSN 13 9 1 inclusive , except MSN 0925 and 1382. Reason: During Final Assembly Line test s on an A330 aeroplane , the Generator Control Unit - Constant Speed Motor / Generator (GCU - CSM/G) failed the operational test . Investigations revealed that it is due to incorrect locking of some contacts (pins) into the GCU - CSM/G connector 1XE - A

. An inspection of other aeroplanes confirmed this production quality issue. Among the 26 pins used in GCU - CSM/G connector 1XE - A , 6 pins have been identified as potentially affected by this issue. A badly locked contact could result in a loss of continuity and lead to the non operation of the CSM/G. This condition, if not detected and corrected , and in conjunction with either an emergency electrical configuration loss of main electrical system or total engine flame out, could jeopardize the aeroplane’s safe flight

.EASA AD No.: 2013 - 0175

TE. CAP.00110 - 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. To address this condition, Airbus developed Alert Operator Transmission (AOT) A24L001 - 13 , to provide instructions for a one - time inspection. For the reason s described above , this AD requires a one - time inspection of the potentially affected connector wires of GCU - CSM / G connector 1XE - A and , depending on finding, accomplishment of applicable corrective actions

. Effective Date: 16 A ugust 2013 Required action( s) and Compliance Time(s): Required as indicated , unless accomplished previously : (1) Within 1 000 flight hours after the effective date of this AD, inspect the affected connector wires of GCU - CSM / G connector 1XE - A in accordance with the instructio ns of Airbus AOT A24L001 - 13

. (2) If , during the inspection as required by paragraph (1) of this AD, a discrepancy is detected , before next flight, accomplish the applicable corrective actions in accordance with the instructions of Airbus AOT A24L001 - 13

. R ef. Publications: Airbus AOT A24L001 - 13 d ated 25 July 2013

. The use of later approved revisions of th i s document is acceptable for compliance with the requirements of this AD. Remarks: 1. If requested and appropriately substantiated, EASA can approve Alterna tive 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 conte nt of the requirements in this AD, please contact: AIRBU S SAS

– Airworthiness Office

– EAL. Fax: + 33 5 61 93 45 80 or + 33 5 61 93 44 51. E - mail: airworthiness.A330 - A340@airbus.com

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