EASA AD No.: 2010 - 0024 

EASA Form 110 Page 1/3 

 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0024 

Date: 12 February 2010 

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) : 

A330 and A340-200/-300 aeroplanes 

TCDS Number : EASA.A.004, EASA.A.015 

Foreign AD : None 

Supersedure : This AD supersedes EASA AD 2006-0315R1 dated 26 October 2006. 

ATA 57 Wings – Centre Wing Box – Keel Beam Fastener Holes at 

Frame FR40 - Inspection 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus A330 aeroplanes, models -201, -202, - 203, - 223, -243, -301, -

302, -303, -321, -322, -323, -341, -342 and -343, all manufacturer serial 

numbers, except those on which Airbus modification 55306 or 55792 

has been embodied in production. 

Airbus A340 aeroplanes, models -211, -212, -213, -311, -312, -313, all 

manufacturer serial numbers, except those on which Airbus modification 

55306 or 55792 has been embodied in production. 

This AD is not applicable to Airbus A340 -200/-300 aeroplanes repaired 

in accordance with Repair Drawing R57115053 or R57115051 or 

R57115047 (installation of Titanium Doubler on both sides) which are 

affected by EASA AD 2006-0314. 

Reason: During A330 and A340 aeroplanes fatigue tests, cracks appeared on the 

right (RH) and left (LH) sides between the crossing area of the keel beam 

fitting and the front spar of the Centre Wing Box (CWB). This condition, if 

not corrected, could lead to keel beam rupture which would affect the area 

structural integrity. 

In order to maintain the structural integrity of the aeroplane, EASA AD 

2006-0315R1 required repetitive special detailed inspections on the 

horizontal flange of the keel beam in the area of first fastener hole aft of 

FR40. 

This AD, which supersedes EASA AD 2006-0315R1: 
EASA AD No.: 2010 - 0024 

EASA Form 110 Page 2/3 

 

- retains the inspection requirements of EASA AD 2006-0315R1, 

- extends the AD applicability to aeroplanes which have embodied 

Airbus modification 49202, and 

- modifies the inspection thresholds and intervals. 

Effective Date: 26 February 2010 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated : 

(1) Unless already accomplished, 

Within the mandatory thresholds (Flight cycles (FC) or Flight hours 

(FH), whichever occurs first), mentioned in paragraph 1.E. (2) of 

Airbus SB A340-57-4089 Revision 03 or Airbus SB A330-57-3081 

Revision 03, as applicable, depending on the aeroplane 

configuration, carry out a Special Detailed Inspection of the hole(s) of 

the horizontal flange of the keel beam located on FR40 datum on RH 

and/or LH side of the fuselage, in accordance with the instructions of 

Airbus SB A340-57-4089 Revision 03 or Airbus SB A330-57-3081 

Revision 03, as applicable. 

Inspection in accordance with Airbus Technical Disposition Ref. 

F57D03012810 or 582.0651/2002 satisfies the inspection requirements 

for the first rotating probe inspection which is requested at the 

inspection threshold of this AD. 

Note 1: In order to prevent large repairs or heavy maintenance, Airbus 

recommends to perform the inspection required by paragraph (1) 

of this AD in accordance with the recommended thresholds 

mentioned in § 1.E. (2) of Airbus SB A340-57-4089 Revision 03 or 

Airbus SB A330-57-3081 Revision 03, as applicable. 

(2) In case of any crack finding, before next flight, contact Airbus in 

order to get repair instructions and accomplish them within the 

compliance time defined in these instructions. 

(3) Should no crack be detected: 

(3.1) Apply the actions indicated in the associated accomplishment 

instructions of Airbus SB A340-57-4089 Revision 03 or Airbus SB 

A330-57-3081 Revision 03, as applicable, 

(3.2) Repeat the inspections of paragraph (1) of this AD at intervals not 

to exceed the mandatory intervals given in paragraph 1.E. (2) of 

Airbus SB A340-57-4089 Revision 03 or Airbus SB A330-57-3081 

Revision 03, as applicable, and apply the associated corrective 

actions in accordance with the instructions of Airbus SB 

A340-57-4089 Revision 03 or Airbus SB A330-57-3081 Revision 

03, as applicable. 

Note 2: In order to prevent large repairs or heavy maintenance, Airbus 

recommends to perform the repetitive inspections required by 

paragraph 3.2 of this AD in accordance with the recommended 

intervals mentioned in § 1.E. (2) of Airbus SB A340-57-4089 

Revision 03 or Airbus SB A330-57-3081 Revision 03, as 

applicable. 
EASA AD No.: 2010 - 0024 

EASA Form 110 Page 3/3 

 

(4) Inspections accomplished, before the effective date of this AD, in 

accordance with the instructions of Airbus SB A330-57-3081 Revision 

00, 01 or 02, or Airbus SB A340-57-4089 Revision 00, 01 or 02, as 

applicable, are considered acceptable for compliance with the 

requirements of paragraph (1), (2) and (3) of this AD. However, after 

the effective date of this AD, the repetitive inspections must be 

accomplished in accordance with the instructions of Airbus SB 

A330-57-3081 Revision 03 or Airbus SB A340-57-4089 Revision 03, 

as applicable. 

(5) For aeroplanes that have already been modified, before the effective 

date of this AD, in accordance with Airbus SB A330-57-3098 at 

original issue or Airbus SB A340-57-4106 at original issue, as 

applicable, and on which a crack was detected at hole 5 before 

oversizing of the keel beam (in accordance with instructions in 

paragraph 3.B (1)(b) step 3 of Airbus SB A330-57-3098 at original 

issue or Airbus SB A340-57-4106 at original issue), within 30 days 

after the effective date of this AD, contact Airbus for further 

instructions (additional work) and apply the associated instructions 

within the compliance time defined in these instructions. 

(6) Except as indicated in paragraph (5) of this AD, accomplishment of 

Airbus SB A330-57-3090 or Airbus SB A340-57-4098 or Airbus SB 

A330-57-3098 at original issue or Revision 01 or Airbus SB 

A340-57-4106 at original issue or Revision 01, as applicable, cancels 

the requirements of this AD. 

Ref. Publications: Airbus Service Bulletin A330-57-3081 Revision 03; 

Airbus Service Bulletin A340-57-4089 Revision 03; 

Airbus Service Bulletin A330-57-3098 at Original issue, Revision 01; 

Airbus Service Bulletin A340-57-4106 at Original issue, Revision 01; 

Airbus Service Bulletin A330-57-3090 at Original issue; 

Airbus Service Bulletin A340-57-4098 at Original issue. 

The use of later approved revisions of these documents 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. This AD was issued as PAD 09-115 on 30 September 2009 for 

consultation until 29 October 2009. The Comment Response 

Document can be found at http://ad.easa.europa.eu/. 

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.