EASA AD No.: 2009-0152

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2009-0152

Date: 14 July 2009

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 opera te an aircraft to which an AD applies, except in accordance with t he requirements of that AD unless otherwise specified by the Age ncy [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) exemptio n]. 

### Type Approval Holder’s Name :
AIRBUS Type/Model designation(s) :
A380 aeroplanes

TCDS Number : EASA.A.110

Foreign AD : Not applicable

Supersedure : This AD supersedes EASA AD 2008-0216 dated 09 December 2008



### ATA 57 Wings – Movable Flap Track Fairing – Inspection / Replacement

Manufacturer(s): Airbus

Applicability: Airbus A380 aeroplanes, -841, -842 and -861 models, all serial numbers, except those on which Airbus modification 68729 has been embodied in production.
Reason: During the flight test campai gn of the A380-861 model (Engine Alliance powered), some cracks were found on the Movable Flap Track Fairing number 6 (MFTF#6). These cracks were located at the pivot attachment support-ring and at the U-frame in the attachment area to aft-kinematic. In addition, delamination has been observed within the monolithic Carbon Fibre Reinforced Plastic (CFRP) structure around the pivot support-ring. This condition, if not corrected, could lead to in-flight loss of the MFTF#6, potentially resulting in injuries to persons on the ground. To prevent the risk of a MFTF#6 det achment, EASA AD 2008-0 216 required an inspection programme in order to detect cracks before they become critical and in case of findings to replace the MFTF#6. This AD, which supers edes EASA AD 2008-0216 :

 cancels the MFTF#6 General Visual Inspection requirement,

 refers to Airbus Service Bulletin A380-57-8014 Revision 1,

 requires the reporting to AIRBUS in case of MFTF#6 replacement,EASA AD No.: 2009-0152

EASA Form 110 Page 2/3  introduces an optional terminating action.
Effective Date: 28 July 2009

Required action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Perform the following actions on Left Hand (LH) and Right Hand (RH) MFTF#6 in accordance with the instructions of Airbus Service Bulletin (SB) A380-57-8014 Revision 1:

 special detailed (ultrasonic and High-Frequency Eddy Current) inspections of the filet radii of pivot supports, monolithic CFRP structure and radii of U-Frame,

or

 replacement of the MFTF#6, For -841 and -842 aeroplane models : Before the MFTF#6 has accumulated 500 Total Flight Cycles (FC) since its first installation on an aeroplane. For -861 aeroplane model : Before the MFTF#6 has accumulated 100 Total FC since its first installation on an aeroplane. Aeroplanes which have been inspected, before the effective date of this AD, in accordance with Airbus SB A380-57 -8014 at Original Issue are compliant with the inspection requirements of paragraph (1) of this AD. (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 : 50 FC , For -861 aeroplane model :10 FC.

 In case of findings, before next flight, replace the MFTF#6 in accordance with the instructions of Airbus SB A380-57-8014 Revision 1 and repeat the inspection at the thresholds defined in paragraph (1) of this AD. (3) Reporting to Airbus: In case of MFTF #6 replacement, submit a report including the following information to Airbus within 30 days after the MFTF#6 removal :

 the removed MFTF#6 serial number.

 the associated aeroplane Manufacturer Serial Number (MSN).

 the number of FC accumulated by t he MFTF#6 at the time of removal. (4) The installation of reinforced LH/RH MFTF#6 in accordance with the instructions of Airbus SB A380 57-80 17 cancels the requirements of this AD.
Ref. Publications: Airbus Service Bulletin A380-57-8014 Revision 1, Airbus Service Bulletin A380 57-8017 Original Issue. The use of later approved revisions of these documents is acceptable for compliance with the requirements of this AD.EASA AD No.: 2009-0152

EASA Form 110 Page 3/3 Remarks: 1. If requested and appropriately subs tantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. The required actions and the risk a llowance 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 tec hnical content of the requirements in this AD, please contact: AIRBUS SAS - EANA (Airworthiness Office); Phone +33 562110253 ; Fax :+33 562 110 307; E-mail: account.airworth-A380@airbus.com and Nicolas.Cordeau@airbus.com

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