AD 2017-07-07 Airworthiness Directives; Airbus Airplanes

Models named: A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to the airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD, having serial numbers 0176 through 0915 inclusive. (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes. (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes.

Comply with this AD within the compliance times specified, unless already done.

Within the compliance times defined in table 1 to the introductory text of paragraph (g) of this AD, and, thereafter, at intervals not to exceed the compliance times defined in Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016; or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016; as applicable, depending on airplane utilization and configuration: Accomplish a special detailed inspection of fastener holes located at FR40 lower shell panel junction on both left-hand (LH) and right-side (RH) sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016; or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016; as applicable. Table 1 to the Introductory Text of Paragraph ( g ) of this AD— Compliance Time for Initial Inspection   Compliance time (whichever occurs later, A or B) A Before exceeding the compliance time “threshold” defined in table 1 of Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016; or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016; as applicable, depending on airplane utilization and configuration and to be counted from airplane first flight B For Model A330 airplanes: Within 2,400 flight cycles or 24 months, whichever occurs first after the effective date of this AD For Model A340 airplanes: Within 1,300 flight cycles or 24 months, whichever occurs first after the effective date of this AD (1) If, during any inspection required by the introductory text of paragraph (g) 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 Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016; or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016; as applicable, except where Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016; or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016, specifies to contact Airbus for repair instructions, and specifies that action as “RC” (Required for Compliance), this AD requires repair before further flight using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (2) If, during any inspection required by the introductory text of paragraph (g) of this AD, the hole diameter is not within tolerance of the transition fit as nominal, or first oversize, or second oversize, or next nominal, as applicable, and Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016; or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016, specifies to contact Airbus for repair instructions, and specifies that action as “RC” (Required for Compliance), before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (3) Accomplishment of corrective actions, as required by paragraph (g)(1) of this AD, does not constitute terminating action for the repetitive inspections required by the introductory text of paragraph (g) of this AD. (4) Accomplishment of a repair on an airplane, as required by paragraph (g)(2) of this AD, does not constitute terminating action for the repetitive inspections required by the introductory text of paragraph (g) of this AD for that airplane, unless the method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA indicates otherwise.

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 detect and correct cracking at FR40 on the lower shell panel junction; such cracking could lead to reduced structural integrity of the fuselage.

None.