EASA AD No.:2010-0044

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0044 [Correction: 25 March 2010]

Date: 17 March 2010

Note: This Airworthiness Directive (AD) is i ssued 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) :
A340-200/-300 aeroplanes

TCDS Number : EASA.A.015

Foreign AD : Not applicable

Supersedure : None



### ATA 78 Exhaust – Thrust Reverser Actuation System Doors – Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A340 aeroplanes, models -211, -212, -213, -311, -312 and -313, all manufacturer serial numbers.
Reason: Two A340-300 aeroplanes experienced one single door opening of engine number (n°) 3 Thrust Reverser (TR) pivoting door during climb. These events were the result of a primary lock ma lfunction and incorrect engagement of the secondary lock. While investigations on root cause of t hese events were conducted, preventive actions have been required by EASA AD 2008-0074, AD 2009-0063 and AD 2009-0133. The root cause has now been identified as being a combined failure of the thrust reverser pivoting door primary lock and actuator. Deployment of one TR door in flight, particularly during the take-off or go around, could result in heavy buffet at low speed, or could significantly reduce take off performance, which would constitute an unsafe condition. Investigations have also identified that 10 TR pivoting doors of the 16 installed on each aeroplane may cause such effects. These are: - Outboard engines ( n° 1 and 4): all 4 pivoting doors of each engine. - Inboard engines ( n° 2 and 3): upper inboard pivoting door of each engine.
In order to reinforce the thrust revers er locking mechanism, this AD requires installation of a new modified primary lock and a new modified actuator on the 10 critical thrust reverser pivoting doors.EASA AD No.:2010-0044

EASA Form 110 Page 2/2 This AD correction is issued to amend the engines numbering in Picture 1 of the “Required action and Compliance Time” section of this AD.

Effective Date: 31 March 2010

Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) No later than 28 February 2011, do the actions specified in paragraph (3) of this AD on the upper inboard thrust reverser pivoting door of each engine, as identified by the label in Picture 1 below. (2) No later than 31 December 2012, do the actions specified in paragraph (3) of this AD on the upper outboard thrust reverser pivoting doors of engines n°1 and n°4, and lower thrust reverser pivoting doors (inboard and outboard) of engines n°1 and n° 4 as identified by the label in Picture 1 below. (3) Replace the primary lock in accordance with the instructions defined in Airbus Service Bulletin (SB) A340-78-4037,
and Remove the installed shim and replace the actuator in accordance with the instructions defined in Airbus SB A340-78-4038.

Picture 1

Ref. Publications: Airbus Service Bulle tin A340-78-4037 at Original issue; Airbus Service Bulletin A340-78-4038 at Original issue. The use of later approved revisions of these documents is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately subs tantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 05 February 2010 as PAD 10-016 for consultation until 05 March 2010. 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 tec hnical 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

. Engine n ° 4

Engine n ° 2 Engine n ° 3 En g ine n ° 1 Engine n ° 4 En g ine n ° 4 En g ine n ° 4 En g ine n ° 1

En g ine n ° 2 Engine n ° 2