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 participate 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 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]. 

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 2009 
EASA 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 occurs 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 accordance 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 provided 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 Bulletin 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 & Research Section, Certification 

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 SAS – Airworthiness Office - EAL. Fax: +33 5 61 93 45 80. 

E-mail: airworthiness.A330-A340@airbus.com .