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 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) : 

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 campaign 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 detachment, EASA AD 2008-0216 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 supersedes 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 the 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 57-8017 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 substantiated, 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 & 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 - EANA (Airworthiness Office); Phone 

+33 562110253 ; Fax :+33 562 110 307; 

E-mail: account.airworth-A380@airbus.com and 

Nicolas.Cordeau@airbus.com .