EASA AD No.: 2013

- 0094

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

. : 201 3

- 0094

Date: 15 April 201 3

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 21A.3B. In accordanc e 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 ) exemption].


### 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 71 Power Plant

– U pper Aft M ount B olt s
– Inspection / R epair

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330

- 201, A330

- 202, A330

- 203, A330

- 301 , A330

- 302 and A330

- 303 aeroplanes, all manufacturer serial numbers

.

Reason: During a scheduled replacement of a CF6

- 80E1 engine # 1 on an A330 aeroplane

, one bolt on the aft engine mount upper beam was found totally broken. Th at bolt is one of the four bolts that attach the upper beam to the pylon.
The subsequent a nalyses o f the broken b olt and the upper beam identified the following :

- a fatigue origin area with crack propagation from the boundary of the bolt,

- a spiral groove with cold work and microstructural distortion underlying that

ex tended axially along the shank, and

- a score mark on counter

- bore edge of the upper beam

. The p reliminary root

- cause investigation shows that an unusual contact with the counter

- bore edge of the beam induce d a significant groove on the bolt during its installation in production . It is suspected that this groove led to a fatigue crack initiat ion and subsequent quick propagation leading to the complete fracture of the bolt

. As the root

- cause is still under investigation, including the installation sequence specific to this aeroplane

- engine model, the other A330 propulsion systems are not affected

. This condition, if not detected and corrected, c ould lead, in conjunction with aEASA AD No.: 2013

- 0094

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. second fractured bo lt

, to the loss of engine mount structural integrity and potential engine detachment in flight as the remaining bolts would not be able to sustain the residual fatigue and limit loads

. For the reasons described above, this AD requires a one

- time ultrasonic inspection of the four aft mount

- pylon bolts of both engine s for detection of completely sheared bolts through the bolt section and, depending on finding, accomplishment of applicable corrective actions

. This AD is considered as an interim action, pending the results of the ongoing investigations , and further AD action may follow

.

Effective Date: 22 April 2013

Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within 1 0 00 flight hours after the effective date of this AD, inspect all four aft mount

- pylon bolts of both engine s in accordance with the instructions of Airbus Alert Operators Transmission (AOT) A71L002

- 13. (2) If, during the inspection as required by paragraph (1) of this AD, a fractured bolt is detected, before next flight, contact Airbus for approved repair instructions and accomplish those instructions within the there i n defined compliance time s

. (3) Within 10 days after the accomplishment of the bolt inspection s as required by paragraph (1) of this AD , report the results (including no findings) to Airbus.

Ref. Public ations: Airbus AOT A71L002

- 13 dated 08 April 201 3

. 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 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, 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

.