Airworthiness Directive · Amendment 39-17949 · Fuselage
Airbus Airplanes
This AD applies to Airbus Model A330-201, -202, -203, -223, and -243 airplanes; and Model A330-301, -321, -322, -323, -341, -342, and -343 airplanes, certificated in any category, except those on which Airbus Modification 49202 has been embodied in production.
We are superseding Airworthiness Directive (AD) 2007-06-12 for certain Airbus Model A330-200 and A330-300 airplanes. This new AD reduces the compliance times for reinforcing the structure of the center fuselage. This AD was prompted by a new fatigue and damage tolerance evaluation that revealed the compliance time for an existing reinforcement of the fuselage has to be reduced. We are issuing this AD to prevent fatigue cracking of the fuselage, which could result in reduced structural integrity of the fuselage.
For Airbus Model A330-301, A330-321, A330-322, A330-323, A330-341, A330-342, and A330-343 airplanes, except those on which Airbus Modification 41652S11819 has been incorporated in production: At the time specified in paragraph (g)(1) or (g)(2) of this AD, whichever occurs later, install butt straps at FR53.3 on the fuselage skin between left-hand (LH) and right-hand (RH) stringer (STR) 13, and do all related investigative and corrective actions before further flight. Except as provided by paragraph (h) of this AD, do all actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3127, Revision 02, including Appendix 01, dated December 7, 2011.
(1) At the applicable time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
(i) For airplanes with a short-range mission as specified in Airbus Service Bulletin A330-53-3127, Revision 02, including Appendix 01, dated December 7, 2011: Within 15,300 flight cycles or 46,100 flight hours, whichever occurs first, after the first flight of the airplane.
(ii) For airplanes with a long-range mission as specified in Airbus Service Bulletin A330-53-3127, Revision 02, including Appendix 01, dated December 7, 2011: Within 13,200 flight cycles or 79,300 flight hours, whichever occurs first after the first flight of the airplane.
(2) Within 24 months after the effective date of this AD, but not to exceed 14,700 total flight cycles or 51,400 total flight hours, whichever occurs earlier.
For Airbus Model A330-301, -321, -322, -323, -341, -342, and -343 airplanes, except those on which Airbus Modification 41652S11819 has been incorporated in production: If any crack is detected during the related investigative actions (rototest) required by 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). If approved by the DOA, the approval must include the DOA-authorized signature.
For airplanes specified in paragraph (c) of this AD on which Airbus Modification 41652S11819 has been embodied in production: At the time specified in paragraph (i)(1) or (i)(2) of this AD, whichever occurs later, install butt straps at FR53.3 on the fuselage skin between LH and RH STR13; and do all related investigative and other specified actions before further flight, as applicable. Do all actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3143, Revision 05, dated May 29, 2012, including Appendix 1; except, if any crack is detected during a related investigative action (rototest), before further flight, repair the crack 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). If approved by the DOA, the approval must include the DOA-authorized signature.
(1) At the applicable times specified in the “threshold” column of the table in 1.E. “Compliance” of Airbus Service Bulletin A330-53-3143, Revision 05, including Appendix 01, dated May 29, 2012. Where paragraph 1.E. “Compliance” of Airbus Service Bulletin A330-53-3143, Revision 05, dated May 29, 2012, specifies a time in the “threshold” column, this AD requires compliance within the corresponding times after the first flight of the airplane.
(2) Within 24 months after the effective date of this AD, but not to exceed 17,600 total flight cycles or 61,600 total flight hours, whichever occurs earlier.
