Airworthiness Directive · Amendment 39-19517 · Fuselage
Airbus SAS Airplanes
This AD applies to the airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD; all manufacturer serial numbers.
(1) Airbus SAS Model A330-223F airplanes.
(2) Airbus SAS Model A330-243F airplanes.
We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-223F and Model A330-243F airplanes. This AD was prompted by a report of cracking at fastener holes located at a certain frame on the lower shell panel junction. This AD requires repetitive special detailed inspections (rototest) of certain fastener holes located at the lower shell junction of a certain frame on both left- hand (LH) and right-hand (RH) sides, and applicable related investigative and corrective actions. We are issuing this AD to address the unsafe condition on these products.
Accomplish the actions required by paragraph (h) of this AD before exceeding the compliance time “threshold” defined in paragraph 1.E., “Compliance,” of Airbus Service Bulletin A330-53-3215, Revision 03, dated January 22, 2018 (“A330-53-3215, R3”), depending on airplane utilization and configuration and to be counted from airplane first flight, and, thereafter, at intervals not to exceed the compliance times defined in paragraph 1.E., “Compliance,” of A330-53-3215, R3, depending on airplane utilization and configuration.
At the applicable compliance times specified in paragraph (g) of this AD: Accomplish a special detailed inspection of the 10 fastener holes located at FR40 lower shell panel junction on both LH and RH sides, in accordance with the Accomplishment Instructions of A330-53-3215, R3.
(1) If, during any inspection required by the introductory text of paragraph (h) of this AD, any crack is detected, before further flight, accomplish all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of A330-53-3215, R3, except where A330-53-3215, R3 specifies to contact Airbus for repair instructions, and specifies that action as Required for Compliance (RC), this AD requires repair before further flight using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or European 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.
(2) If, during any inspection required by the introductory text of paragraph (h) of this AD, the diameter of a fastener hole is found to be outside the tolerances of the transition fit as specified in A330-53-3215, R3, as applicable; and A330-53-3215, R3; specifies to contact Airbus for repair instructions, and specifies that action as “RC,” before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(3) Accomplishment of corrective actions, as required by paragraph (h)(1) of this AD, does not constitute terminating action for the repetitive inspections required by the introductory text of paragraph (h) of this AD.
(4) Accomplishment of a repair on an airplane, as required by paragraph (h)(2) of this AD, does not constitute terminating action for the repetitive inspections required by the introductory text of paragraph (h) of this AD for that airplane, unless the method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA indicates otherwise.
Although A330-53-3215, R3, specifies to submit certain information to the manufacturer, and specifies that action as RC, this AD does not include that requirement.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
