EASA AD No.: 2013-0094

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Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0094

Date: 15 April 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 

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 21A.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 aeroplanes

TCDS Number: EASA.A.004 

Foreign AD: Not applicable

Supersedure: None

ATA 71 Power Plant – Upper Aft Mount Bolts – Inspection / Repair

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. That bolt 

is one of the four bolts that attach the upper beam to the pylon.

The subsequent analyses of the broken bolt 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 

extended axially along the shank, and

- a score mark on counter-bore edge of the upper beam.

The preliminary root-cause investigation shows that an unusual contact with the 

counter-bore edge of the beam induced a significant groove on the bolt during its 

installation in production. It is suspected that this groove led to a fatigue crack 

initiation 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, could lead, in conjunction with a 
EASA AD No.: 2013-0094

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2

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second fractured bolt, 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 engines 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 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 all four 

aft mount-pylon bolts of both engines 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 therein defined 

compliance times.

(3) Within 10 days after the accomplishment of the bolt inspections as required 

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

Airbus.

Ref. Publications: Airbus AOT A71L002-13 dated 08 April 2013.

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, 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.