Airworthiness directives › 2014-16-25
AD 2014-16-25 Airworthiness Directives; Airbus Airplanes
Models named: A330-201, -202, -203, -223, -243, A330-301, -321, -322, -323, -341. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
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.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
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.
Unsafe condition
This AD was prompted by a new fatigue and damage tolerance evaluation that concluded 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.
Affected ADs
This AD replaces AD 2007-06-12, Amendment 39-14993 (72 FR 12555, March 16, 2007).
Read the original on the Federal Register →
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1