EASA AD No : 2011-0075 

EASA Form 110 Page 1/2 

 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0075 

Date: 29 April 2011 

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) : 

A340-500/-600 aeroplanes 

TCDS Number : EASA.A.015 

Foreign AD : Not applicable 

Supersedure : None 

ATA 57 Wings – External Radius on Upper Horizontal Cruciform Fitting 

at Frame (FR)47 – Inspection 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus A340 aeroplanes, models -541, -542, 642 and -643, all 

manufacturer serial numbers. 

Reason: During the A340-600 EF2 fatigue test, damages occurred in external 

radius on upper horizontal cruciform in rear corner at FR47 respectively on 

Right Hand (RH) side and on Left Hand (LH) side. These damages were 

detected after tear down inspections using High Frequency Eddy Current 

method. 

This condition, if not corrected, could impair the structural integrity of the 

aeroplane. 

For the reasons described above, this AD requires to perform repetitive 

Special Detailed Inspections for early detection of cracks on upper 

horizontal cruciform fitting at FR47 on LH and RH sides, and the 

accomplishment of corrective actions, as applicable. 

Effective Date: 13 May 2011 
EASA AD No : 2011-0075 

EASA Form 110 Page 2/2 

 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Before the accumulation of the threshold defined in paragraph 1.E.(2) 

of Airbus Service Bulletin (SB) A340-57-5029, depending on 

aeroplane configuration, do a Special Detailed Inspection of the 

external radius on upper horizontal cruciform fitting at FR47 on LH 

and RH sides, in accordance with the instructions of Airbus SB 

A340-57-5029. 

(2) Repeat the inspection required by paragraph (1) of this AD at intervals 

not to exceed the interval defined in paragraph 1.E.(2) of Airbus SB 

A340-57-5029, depending on aeroplane configuration. 

(3) If any crack is found during the initial or repetitive inspections required 

by paragraph (1) or (2) of this AD, before further flight, contact Airbus 

to obtain the necessary approved instructions for corrective action and 

accomplish those instructions accordingly. 

(4) Within 90 days after the accomplishment of the inspection required by 

paragraph (1) or (2) of this AD, report to Airbus all recorded inspection 

results (including no findings) in accordance with the instructions of 

Airbus SB A340-57-5029. 

(5) Aeroplanes that have already been inspected, before the effective 

date of this AD, in accordance with Airbus Non-destructive Test 

Manual (NTM) task 57-18-07, are compliant with the requirements of 

paragraph (1) of this AD (initial inspection). After the effective date of 

this AD, inspections must be repeated in accordance with the 

requirements of paragraph (2) of this AD. 

Ref. Publications: Airbus Service Bulletin A340-57-5029 Original issue dated 25 February 

2011. 

The use of later approved revisions of this document is acceptable for 

compliance with the requirements of this AD. 

Airbus Non-destructive Test Manual (NTM) 57-18-07. 

Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. This AD was posted on 09 March 2011 as PAD 11-029 for 

consultation until 06 April 2011. No comments were received during 

the consultation period. 

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 – Airworthiness Office – EAL; 

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