EASA AD No.: 2009-0113

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2009-0113

Date: 27 May 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 partic ipate 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 ens ured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which an AD applies, except in a ccordance 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) :
A380 aeroplanes

TCDS Number : EASA.A.110

Foreign AD : Not applicable

Supersedure : None



### ATA 57 Wings – Movable Flap Track Fairing number 4 (MFTF #4) – Inspection / Replacement

Manufacturer(s): AIRBUS (formerly AIRBUS INDUSTRIE)
Applicability: AIRBUS A380 aeroplanes, -841, -842 and -861 models, all serial numbers.

Reason: As a result of the Movable Flap Tr ack Fairing (MFTF) #6 crack findings (ref. AD 2008-0216), a detailed review has been launched for all MFTF #2 to #6.This investigation has revealed some cracking at MFTF #4 pivot supportring. This condition, if not corrected, coul d lead to in-flight loss of MFTF #4, potentially resulting in injuries to persons on the ground. To prevent the risk of a MFTF #4 detachment, this AD requires an inspection programme and/or replacement of the fa irings in order to ensure they are removed from service before any crack becomes critical.

Effective Date: 10 June 2009
Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1.) Perform the following actions on Left Hand and Right Hand MFTF #4 in accordance with instructions of AIRBUS Service Bulletin (SB) A380-57-8016:

• special detailed (Ultrasonic and High-Frequency Eddy Current) inspections of the filet radii of pivot bracket support rings and the monolithic Carbon Fibre Reinforced Pl astic (CFRP) structure in the pivot support area,EASA AD No.: 2009-0113

EASA Form 110 Page 2/2 or

• replacement of the MFTF #4, For -841 and -842 aeroplane models : Before the MFTF #4 has accumulated 600 Total Flight Cycles (FC) since its first installation on an aeroplane, For -861 aeroplane model : Before the MFTF #4 has accumulated 300 Total FC since its first installation on an aeroplane,

(2.) Further to the special detailed inspections performed in accordance with paragraph (1.) of this AD :

• In case there is no finding, repeat the inspections defined in paragraph (1.) of this AD at intervals not exceeding : For -841 and -842 aeroplane models : 60 FC; For -861 aeroplane model : 30 FC.

• In case of findings, before next flight, replace the MFTF #4 in accordance with instructions of AIRBUS SB A380-57-8016, and thereafter perform the actions defined in paragraph (1.) and (2.) of this AD within the applicable thresholds.

(3.) Reporting to Airbus: In case of MFTF #4 replacement, submit a report including the following information to Airbus within 30 days after the MFTF #4 removal :

• the removed MFTF #4 serial number.

• the associated aeroplane Manufacturer Serial Number (MSN).

• the number of FC accumulated by the MFTF #4 at the time of removal.

Ref. Publications: AIRBUS Service Bulle tin A380-57-8016 at original issue. 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 subst antiated, EASA can approve Alternative Methods of Compliance for this AD. 2. The required actions and the risk allowance have granted the issuance of a Final AD with Request for Comments, postponing the public consultation process after publication. 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 - EANA (Airworthiness Office), E-mail: account.airworth-A380@airbus.com and Nicolas.Cordeau@airbus.com ; Phone +33 562110253 ; Fax :+33 562 110 307.