EASA AD No.: 2009-0240

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2009-0240

Date: 05 November 2009

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 parti cipate in the activities of EASA under Article 66 of that Regulation.
This AD is issued in accordance with EC 1702/2003, 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 a pplicable ADs. Consequently, no person may operate an aircraft to which an AD applies, except in accordance wi th 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]. 

### Type 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 – Forward and Aft ward Mount Pylon Bolts – Inspection / Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330 aeroplanes, models -223, -321, -322 and -323, all manufacturer serial numbers.
Reason: During accomplishment of Damage Tolerant - Airworthiness Limitation Item task 712106-01-01 from A330 ALS Part 2, an A330 operator found a Fluorescent Penetrant Inspection (FPI ) indication in the head of the shank filet radius in one of the Pratt & Whitney (PW) forward (FWD) engine mount pylon bolts. Investigation has confirmed that this FPI indication was due to a quality manufacturing process issue which led to a bolt non-conformance and is also applicable to aft ward (AFT) mount pylon bolts. Dual-bolt fractures could lead to inability for mount assembly to sustain loads which may lead to an engine mount failure and consequently to engine separation from the aeroplane during flight, which would constitute an unsafe condition. This AD requires a one time detailed visual inspection of the FWD and AFT mount pylon bolts on all A330 aeroplanes fitted with PW engines (8 bolts per engine) and replacement of any affected bolt.

Effective Date: 19 November 2009EASA AD No.: 2009-0240

EASA Form 110 Page 2/2 Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previously, (1) Before the accumulation of 8 000 Total Flight Cycles (FC) or 24 000 Total Flight Hours (FH), whichever oc curs first, since the aeroplane first flight,

or Within 24 months after the effective date of this AD, for aeroplanes which have already exceeded, at the effective date of this AD, 8 000 Total FC or 24 000 Total FH, whichever occurs first, since the aeroplane first flight: Perform a detailed visual inspection of FWD and AFT mount pylon bolts on both engines for Part Number (PN), Serial Number (SN) and Lot Number (LN) identification in ac cordance with the instructions of Airbus Service Bulletin (SB) A330-71-3020. (2) If the identified PN, SN, LN correspond to the suspect bolts in accordance with the list provi ded in SB A330-71-3020, before next flight, remove the affected bolt and replace with serviceable bolts, in accordance with the instructions of SB A330-71-3020. (3) If the bolt PN, SN or LN is unreadable, it must be considered as a suspect bolt and before next flight it must be removed and replaced with serviceable bolt, in accordance with the instructions of SB A330-71-3020. (4) From the effective date of this AD, do not install any FWD and AFT mount pylon bolt on an aeroplane, unless this bolt has been identified as a non suspect bolt in accordance with the instructions of SB A330-71-3020.

Ref. Publications: Airbus Service Bulle tin A330-71-3020 at original issue. The use of later approved revisions of this document is acceptable for compliance with the requirements of the AD.

Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 29 June 2009 as PAD 09-085 for consultation until 29 July 2009. The Comment Response Document can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the te chnical content of the requirements in this AD, please contact: AIRBUS SAS – Airworthiness Office - EAL. Fax: +33 5 61 93 45 80. E-mail: airworthiness.A330-A340@airbus.com

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