Airworthiness Directive · Amendment 39-15717 · Fuselage
Airbus Model A330-200, A330-300, and A340-300 Series Airplanes
Superseded. A later AD replaced this one: AD 2015-23-06. Comply with the one in force.
This AD applies to Airbus Model A330-200, A330-300, and A340-300 series airplanes; certificated in any category; all certified models, all serial numbers; on which Airbus Modification 44205 has been embodied in production, except those on which Airbus Modification 52974 or 53223 has been embodied in production.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
Unless already done, do the following actions.
(1) For Airbus Model A330-300 and A340-300 series airplanes, except Model A340-300 weight variant (WV) 027 airplanes: At the applicable compliance time specified in paragraph (f)(2) of this AD, perform a HFEC inspection of the upper shell structure between FR80 and FR86, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-53-3168 or A340-53-4174, both Revision 01, both dated February 15, 2008, as applicable.
(i) If no crack is detected, repeat the inspection thereafter within the intervals specified in paragraph 1.E.(2) of Airbus Mandatory Service Bulletin A330-53-3168 or A340-53-4174, both Revision 01, both dated February 15, 2008, as applicable.
(ii) If any crack is detected during any inspection required by this AD: Before next flight, contact Airbus for repair instructions and do applicable repairs.
(iii) Doing the modification of the upper shell structure in accordance with Airbus Service Bulletin A330-53-3159 or A340-53-4165, both dated September 19, 2007, as applicable, ends the inspections required by paragraph (f)(1) of this AD.
(2) Do the actions required by paragraph (f)(1) of this AD at the later of the compliance times specified in paragraph (f)(2)(i) and (f)(2)(ii) of this AD.
(i) Within the compliance times specified in paragraph 1.E.(2) of Airbus Mandatory Service Bulletin A330-53-3168 or A340-53-4174, both Revision 01, both dated February 15, 2008, as applicable.
(ii) Within 3 months after the effective date of this AD.
(3) At the applicable time specified in paragraphs (f)(3)(i), (f)(3)(ii), and (f)(3)(iii) of this AD or within 3 months after the effective date of this AD, whichever occurs later, modify the upper shell structure between FR80 and FR86 (including doing eddy current inspections for cracking of certain fastener rows and applicable corrective actions) in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-53-3160, dated July 9, 2007; or Airbus Mandatory Service Bulletin A340-53-4172, dated July 10, 2007; as applicable. Do all applicable corrective actions before further flight.
(i) For Model A330-200 airplanes, WV 020 through WV 027: Prior to the accumulation of 13,500 total flight cycles.
(ii) For Model A330-200 airplanes, WV 050 through WV 055: Prior to the accumulation of 10,700 total flight cycles or 59,300 total flight hours, whichever occurs first.
(iii) For Model A340-300 airplanes, WV 027: Prior to the accumulation of 14,200 total flight cycles.
(4) Inspections accomplished before the effective date of this AD according to Airbus Mandatory Service Bulletins A330-53-3168 and A340-53-4174, both dated September 19, 2007, as applicable, are considered acceptable for compliance with the corresponding actions specified in this AD.
Note: This AD differs from the MCAI and/or service information as follows: Although the MCAI allows further flight after cracks are found during compliance with the required action, this AD requires that you repair the crack(s) before further flight.
