EASA PAD No.: 2014

- 0 062

TE.CAP.0011 0

- 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

. : 2014

- 0 062

Date: 11 March 201 4

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 accordan ce 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 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) exempt ion]

. 

### Design Approval Holder’s Name:
AIRBUS Type/Model designation(s):
A330 aeroplanes

TCDS Number: EASA.A.004

F oreign AD: Not applicable

Supersedure: None



### ATA 78 Exhaust

– Thrust Reverser Cowl Door Hinge Sleeve s
–

Identification / Replacement

Manufacturer(s): Airbus (f ormerly Airbus Industrie)

Applicability: Airbus A330

- 243, A330

- 243F, A330

- 341, A330

- 342, and A330

- 343 aeroplane s , all manufacturer serial numbers

.

Reason: A manufacturing discrepancy (lack of heat treatment) on a batch of the N°3 and N °4 hinge sleeves installed on Thrust Reverser Unit (TRU) was identified

. Those parts are only installed on A330 aeroplanes equipped with Rolls

- Royce (RR) Trent 700 engines. This condition, if not corrected

, in case of a Fan Blade Off event due to high vibration level, co uld cause in

- flight loss of some heavy components of the TRU
, possibly result ing in injury to persons on the ground

. As current h inge sleeves are not serialized , it is not possible to identify the TRU hinge sleeves which did not receive the heat treatment

. The part supp lier has developed an identification procedure for these TRU hinge sleeve s in order to identify the affected hinge sleeves, and to allow a better part traceability in the future.
For the reason de scribe d above, this AD requires identification and replacement of the affected TRU hinge sleeves

.

Effective Date: 25 March 2014EASA PAD No.: 2014

- 0 062

TE.CAP.0011 0

- 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. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within 12 months after the effective date of this AD, identify and, if found to be affected, replace the hinge sleeves N°3 and N°4 o f the TRU cowl door in accordance with the instruction s of Airbus Service Bulletin (SB) A330

- 78

- 3021 Revision 01

. (2) Aeroplanes on which Airbus Modification 202463 has been embodied in production or a eroplane s modified in accordance with the instruction s of Airbus SB A330

- 78

- 3021 at o riginal issue, are compliant with the requirement of paragraph (1) of this AD. (3) From the effective date of this AD, installation of a TRU is allowed, provided that, prior to installation, it is determined, in accordance with the instruction s of Airbus SB A330

- 78

- 3021 , that the cowl door hinge sleeves installed on the TRU are not affected by the requirements of this AD.

Ref. Public ations: Airbus SB A330

- 78

- 3021 at o riginal issue dated 17 October 2012, or Revision 01 dated 30 July 2013

. The use of later approved revisions of thi s 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. This AD was posted on 19 September 2013 as PA D 13

- 144 for consultation until 17 October 2013, and re

- published on 18 December 2013 as PAD 1 3

- 144 R1 for additional consultation until 01 January 2014 . 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 t his AD, please contact: AIRBUS

– Airworthiness Office

– EIA L ; E

- mail: airworthiness.A330

- A340@airbus.com

.