Airworthiness Directive · Amendment 39-21305 · Fuselage
Airbus SAS Airplanes
This AD applies to Airbus SAS Model A330-301, -321, -322, -323, -341, -342, and -343 airplanes, certificated in any category, except airplanes on which Airbus Industrie Modification 46636 has been accomplished in production or which have been modified in service as specified in Airbus Service Bulletin A330-53-3090.
The FAA is superseding Airworthiness Directive (AD) 2001-16- 13, which applied to certain Airbus SAS Model A330 series airplanes. AD 2001-16-13 required a roto-test inspection of fastener holes of certain fuselage joints for cracks, reinforcement of the fuselage between certain frames, and, if necessary, a high frequency eddy current (HFEC) inspection and repair. As published, the applicability of AD 2001-16-13 inadvertently identified the model designations as serial numbers. This document corrects that error. This new AD requires a roto-test inspection of fastener holes of certain fuselage joints for cracks, reinforcement of the fuselage, and, if necessary, an HFEC inspection and repair. The FAA is issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (a) of AD 2001-16-13, with new service information. Prior to the accumulation of 15,000 total flight cycles: Perform a roto-test inspection to detect cracks of the fastener holes at frame 31, frame 37.1, and stringer 9, in accordance with Airbus Service Bulletin A330-53-3090, Revision 02, dated January 9, 2001; or Airbus Service Bulletin A330-53-3090, Revision 03, dated December 11, 2002.
This paragraph restates the requirements of paragraph (b) of AD 2001-16-13, with new service information. If no cracks are detected during the inspection performed in accordance with paragraph (g) of this AD, prior to further flight, reinforce the fuselage structure between frames 31 and 37.1, in accordance with Airbus Service Bulletin A330-53-3090, Revision 02, dated January 9, 2001; or Airbus Service Bulletin A330-53-3090, Revision 03, dated December 11, 2002.
This paragraph restates the requirements of paragraph (c) of AD 2001-16-13, with new service information and revised repair approval language. If any crack is detected during the inspection performed in accordance with paragraph (g) of this AD, prior to further flight, perform a high frequency eddy current (HFEC) inspection to determine the crack length, in accordance with Airbus Service Bulletin A330-53-3090, Revision 02, dated January 9, 2001; or Airbus Service Bulletin A330-53-3090, Revision 03, dated December 11, 2002. Prior to further flight, repair the crack in accordance with a method approved by the Direction Générale de l'Aviation Civile (or its delegated agent) or using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or the European Union Aviation Safety Agency (EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
