Airworthiness Directive · Amendment 39-18322 · Fuselage
Airbus Airplanes
This AD applies to Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-311, -312, and -313 airplanes; certificated in any category; all manufacturer 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 superseding Airworthiness Directive (AD) 2008-22-20 for certain Airbus Model A330-200, A330-300, and A340-300 series airplanes. AD 2008-22-20 required repetitive high frequency eddy current (HFEC) inspections for cracking, repair if necessary, and modification of the upper shell structure of the fuselage. This new AD shortens certain compliance times. This AD was prompted by a determination from a fatigue and damage tolerance evaluation that the compliance times must be reduced. We are issuing this AD to prevent fatigue cracking of the upper shell structure of the fuselage, which could result in reduced structural integrity of the airplane.
For Model A330-300 and A340-300 airplanes, except Model A340-300 WV 027 airplanes: At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of the upper shell structure between frame (FR) 80 and FR86, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011; as applicable. Repeat the inspection thereafter at the applicable time specified in paragraph 1.E., “COMPLIANCE,” of Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011; as applicable.
(1) For airplanes that, as of the effective date of this AD, have not been inspected in accordance with Airbus Service Bulletin A330-53-3168; or Airbus Service Bulletin A340-53-4174; as applicable: Inspect at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
(i) Before reaching the applicable threshold specified in paragraph 1.E., “COMPLIANCE,” of Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011; as applicable for airplane model, configuration, and utilization, since the airplane's first flight.
(ii) Within the threshold defined in paragraph 1.E, “COMPLIANCE,” of Airbus Service Bulletin A330-53-3168, Revision 01, dated February 15, 2008; or Airbus Service Bulletin A340-53-4174, Revision 01, dated February 15, 2008; as applicable for airplane model, configuration, and utilization since the airplane's first flight; or within 12 months after the effective date of this AD; whichever occurs first.
(2) For airplanes that, as of the effective date of this AD, have been inspected in accordance with Airbus Service Bulletin A330-53-3168; or Airbus Service Bulletin A340-53-4174; as applicable: Inspect at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Within the applicable interval specified in paragraph 1.E., “COMPLIANCE,” of Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011; as applicable; to be counted from the last inspection.
(ii) Within 12 months after the effective date of this AD without exceeding the intervals defined in paragraph 1.E, “COMPLIANCE,” of Airbus Service Bulletin A330-53-3168, Revision 01, dated February 15, 2008; or Airbus Service Bulletin A340-53-4174, Revision 01, dated February 15, 2008; as applicable for airplane model, configuration, and utilization to be counted from the last inspection.
If any crack is detected during any HFEC inspection required by the introductory text to paragraph (g) of this AD: Before further flight, repair 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). Accomplishment of a repair for a specific area, as required by this paragraph, is terminating action for the repetitive HFEC inspections required by the introductory text to paragraph (g) of this AD, as applicable, for that specific repaired area only. The need and definition of subsequent repetitive inspections (if any) for that specific repaired area will be defined in the applicable repair 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).
For Airbus Model A330-300 and A340-300 airplanes, except Model A340-300 WV 027 airplanes: Modification, which includes inspections and applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3159, Revision 02, dated March 29, 2010; or Airbus Service Bulletin A340-53-4165, Revision 02, dated March 29, 2010; as applicable; terminates the repetitive HFEC inspections required by the introductory text to paragraph (g) of this AD, except where Airbus Service Bulletin A330-53-3159, Revision 02, dated March 29, 2010; or Airbus Service Bulletin A340-53-4165, Revision 02, dated March 29, 2010; as applicable; specifies to contact the manufacturer, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
Within the compliance times specified in paragraph (j)(1) or (j)(2) of this AD, whichever occurs later: Do all applicable actions, including an eddy current rotating probe test and an HFEC inspection for cracks, and modify the airplane upper shell structure between FR80 and FR86; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012.
(1) Within the compliance times identified in paragraph 1.E., “COMPLIANCE,” of Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012, as applicable for airplane configuration and utilization since the airplane's first flight.
(2) Within 12 months after the effective date of this AD without exceeding the threshold defined in paragraph 1.E, “COMPLIANCE,” of Airbus Service Bulletin A330-53-3160, Revision 02, dated March 29, 2010, since the airplane's first flight.
For Model A340-300 airplanes, WV 027 only: Before the accumulation of 14,200 total flight cycles from the airplane's first flight, do all applicable inspections and modify the airplane upper shell structure between FR80 and FR86; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-53-4172, Revision 01, dated July 8, 2009.
If any crack is detected during the inspection required by the introductory text to paragraph (j) of this AD, or paragraph (k) of this AD, 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; concurrently with modification required by paragraph the introductory text to paragraph (j) of this AD, or paragraph (k) of this AD.
(1) For the purposes of this AD, the term “Threshold,” as used in paragraph 1.E., “COMPLIANCE,” of the service information specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD means the total flight cycles or flight hours accumulated since the airplane's first flight.
(2) For the purposes of this AD, the term “Interval” as used in paragraph 1.E., “COMPLIANCE,” of the service information specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD means the total flight cycles or flight hours accumulated since the last inspection, as applicable.
(i) Airbus Service Bulletin A330-53-3168, dated September 19, 2007.
(ii) Airbus Service Bulletin A330-53-3168, Revision 01, dated February 15, 2008.
(iii) Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011.
(iv) Airbus Service Bulletin A340-53-4174, dated September 19, 2007.
(v) Airbus Service Bulletin A340-53-4174, Revision 01, dated February 15, 2008.
(vi) Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011.
