AD/A330/80 Fuselage Cone / Rear Fuselage (Cth)

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Airbus Industrie A330 Series Aeroplanes

AD/A330/80 Fuselage Cone / Rear Fuselage 12/2007 DM

Applicability:

A330-200 aircraft on which AIRBUS modification 44205 has been embodied in production, except those on which AIRBUS modification 52974 or 53223 has been embodied in production.

Requirement:

Action in accordance with the requirements of EASA AD 2007-0269.

Note:  Airbus SB A330-53-3152 original issue and A330-53-3157 original issue, or latter EASA approved revisions, refer.

Compliance:

As specified in the requirement document.

This Airworthiness Directive becomes effective on 24 October 2007.

Background:

During fatigue tests on the A340-600, multiple site damage was found in the upper side shell structure at skin and frame (FR) 84 & 85 interface, from stringer 6 to 15 LH/RH.  This damage occurred between 58,341 and 72,891 simulated flight cycles.

In order to allow early detection of cracks and to avoid possible crack propagation, this Airworthiness Directive mandates a high frequency eddy current (HFEC) inspection program and a modification to the upper shell structure.

David Villiers
Delegate of the Civil Aviation Safety Authority

11 October 2007