Airworthiness Directive · Amendment 39-19312 · Fuselage
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2018-18-16. Comply with the one in force.
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 on which Airbus Modification 44360 has been embodied in production.
(1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
(2) Airbus Model A340-212, -213, -312, and -313 airplanes.
We are superseding Airworthiness Directive (AD) 2017-07-07, which applied to certain Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes. AD 2017-07-07 required repetitive inspections of certain fastener holes, and related investigative and corrective actions if necessary. This AD retains the requirements of AD 2017-07-07 and expands the applicability. This AD was prompted by a report of cracking at fastener holes located at frame (FR) 40 on the lower shell panel junction. We are issuing this AD to address the unsafe condition on these products.
Accomplish the actions required by paragraph (h) of this AD at the times specified in paragraphs (g)(1) and (g)(2) of this AD, as applicable.
(1) For airplanes having serial numbers 0176 through 0915 inclusive: Within the compliance times defined in table 1 to paragraph (g)(1) of this AD, and, thereafter, at intervals not to exceed the compliance times defined in Airbus Service Bulletin A330-53-3215, Revision 03, dated January 22, 2018 (“A330-53-3215, R3”); or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016 (“A340-53-4215, R2”); as applicable, depending on airplane utilization and configuration. As of the effective date of this AD, where paragraph 1.E. “Compliance,” of A330-53-3215, R3 specifies weight variant (WV) 050 in the condition column of table 1, configuration 003, for the purposes of this AD, WV060 and WV080 are also included.
(2) For all airplanes except those identified in paragraph (g)(1) of this AD: Before exceeding the applicable compliance time “threshold” defined in paragraph 1.E., “Compliance,” of A330-53-3215, R3; or A340-53-4215, R2; as applicable, depending on airplane utilization and configuration and to be counted from airplane first flight, and, thereafter, at intervals not to exceed the compliance times specified in paragraph 1.E., “Compliance” of A330-53-3215, R3; or A340-53-4215, R2; as applicable, depending on airplane utilization and configuration. Where paragraph 1.E. “Compliance,” of A330-53-3215, R3 specifies weight variant WV050 in the condition column of table 1, configuration 003, for the purposes of this AD, WV060 and WV080 are also included.
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 left-hand and right-hand sides, in accordance with the Accomplishment Instructions of A330-53-3215, R3; or A340-53-4215, R2; as applicable.
(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; or A340-53-4215, R2; as applicable, except where A330-53-3215, R3; or A340-53-4215, R2; specifies to contact Airbus for repair instructions, and specifies that action as “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'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; or A340-53-4215, R2; as applicable; and A330-53-3215, R3; or A340-53-4215, R2; 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'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's EASA DOA indicates otherwise.
Although A330-53-3215, R3 and A340-53-4215, R2, specify to submit certain information to the manufacturer, and specify that action as “RC,” this AD does not include that requirement.
