EASA AD No.: 2008-0140 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2008 - 0140 

Date: 28 July 2008 

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 Airworthiness Directive applies, except in accordance with the requirements of that 

Airworthiness Directive 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 aircraft 

TCDS Number : EASA A.015 

Foreign AD : Not applicable 

Supersedure : None 

ATA 54 Nacelles/Pylons – Pylon Pyramid Attachment Areas aft of Rib1 

- Inspection 

Manufacturer(s): AIRBUS (formerly AIRBUS INDUSTRIE) 

Applicability: AIRBUS A340 aircraft, models -211, -212, -213, - 311, - 312 and -313, all 

serial numbers except those on which AIRBUS Modification 49203 has 

been embodied in production. 

Reason: Further to accomplishment of A340 ALI tasks 545104, which require a 

rototest inspection as per Non Destructive Testing Manual (NTM) 54-51-

04 of engine pylon pyramid attachment areas at aft end of lower arms 

between Rib1 and Rib2 (2 fastener locations/pylon), four findings have 

been reported and repaired. 

Further investigations made on performances of High Frequency Eddy 

Current (HFEC) inspection techniques in steel led to the conclusion that 

existing NTM procedure 54-51-04 by rototest is not reliable because this 

method is not adapted to the ferromagnetic materials and therefore 

findings reported up to now using this procedure can be considered as 

uncertain. 

Therefore, a new inspection procedure using Ultra Sonic (US) testing 

without fastener removal has been developed. 

In order to comply with certification requirements, this Airworthiness 

Directive (AD) requires performing the new US inspection on all A340-

200/-300 pre-modification 49203 (reinforcements of pylon primary 

structure for enhanced A340). 
EASA AD No.: 2008-0140 

EASA Form 110 Page 2/3 

Effective Date: 11 August 2008 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated: 

1. Unless already accomplished, perform a special detailed inspection of 

pylon pyramid attachment areas at aft end of lower arms between Rib 1 

and Rib 2 without fastener removal (2 fastener locations/pylon) in 

accordance with instructions given in AIRBUS Service Bulletin (SB) A340-

54-4010, with the following threshold : 

• Pending on Weight Variant (WV), before accumulation of threshold X1 

Flight Cycles (FC) or X2 Flight Hours (FH), whichever occurs first: 

Threshold X1 FC Threshold X2 FH WV 

13 000 60 000 000 thru 004 

11 470 77 400 020, 021, 023 thru 026, 

028 thru 030, PRE 49203

11 000 30 000 027 

• For aircraft belonging to WV 000 thru 004 already inspected in 

accordance with ALI task 545104-01-01 (using rototest procedure): 

within 2 680 FC or 19 200 FH from this rototest inspection, whichever 

occurs first, without exceeding 15 280 FC or 76 400 FH since first flight 

whichever occurs first. 

2. If any fatigue crack has been detected, before next flight contact AIRBUS 

to get the repair instructions and apply the associated corrective actions. 

3. If no fatigue crack has been detected, repeat this inspection at interval not 

exceeding Y1 FC or Y2 FH whichever occurs first, pending on WV: 

Interval Y1 FC Interval Y2 FH WV 

1 900 9 500 000 thru 004 

1 700 8 500 020, 021, 023 thru 026, 

028 thru 030, PRE 

49203 

1 700 8 500 027 

Note: This AD cancels A340 ALI tasks 545104-01-01 and 545104-01-02 and 

545104-01-06. 

Ref. Publications: AIRBUS Service Bulletin A340-54-4010 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 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. 
EASA AD No.: 2008-0140 

EASA Form 110 Page 3/3 

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 – Airworthiness Office - EAL Fax: +33 5 61 93 45 80.