AD 2001-07-02 Airworthiness Directives; Airbus Model A330-301, -321, -322, -341, and -342 Series Airplanes; and Model A340-211, -212, -213, -311, -312, and -313 Series Airplanes

Models named: A330-301, -321, -322, -341, -342 series, A340-211, -212, -213, -311, -312. Read the applicability below — it usually turns on serial or part numbers too.

Model A330-301, -321, -322, -341, and -342 series airplanes, and Model A340-211, -212, -213, -311, -312, and -313 series airplanes, certificated in any category, except those on which Airbus Modification 41849 or 44932 (reference Service Bulletin A330-53-3074, Revision 01, for Model A330 series airplanes; or A340-53-4085 Revision 01, for Model A340 series airplanes; both dated May 19, 1998) has been accomplished. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To prevent propagation of fatigue cracking, which could result in reduced structural integrity of the door frames, accomplish the following: Inspection (a) Conduct an eddy current rotating probe test procedure on the holes for doorstop fitting number 5 (left and right) on frame 73A, as specified in paragraph (a)(1) or (a)(2), as applicable, of this AD. (1) For Model A330 series airplanes: Prior to the accumulation of 13,000 total flight cycles, conduct the test in accordance with Airbus Service Bulletin A330-53-3074, Revision 01, dated May 19, 1998. (2) For Model A340 series airplanes: Prior to the accumulation of 8,000 total flight cycles, conduct the test in accordance with Airbus Service Bulletin A340-53-4085, Revision 01, dated May 19, 1998. Repairs (b) If any crack is detected during the inspection required by paragraph (a) of this AD, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent). Terminating Action (c) Before further flight following the inspection required in paragraph (a) of this AD, cold expand the holes for (left and right) doorstop fitting number 5 and install bushings, in accordance with Airbus Service Bulletin A330-53-3074, Revision 01 (for Model A330 series airplanes), or Airbus Service Bulletin A340-53-4085, Revision 01 (for Model A340 series airplanes), both dated May 19, 1998, as applicable. Accomplishment of this action constitutes terminating action for the requirements of this AD. Note 2: Inspection and modification accomplished prior to the effective date of this AD, in accordance with Airbus Service Bulletin A330-53-3074, dated November 17, 1997 (for Model A330 series airplanes), or Airbus Service Bulletin A340-53-4085, dated November 17, 1997 (for Model A340 series airplanes), as applicable, are considered acceptable for compliance with the applicable action specified in this AD. Alternative Methods of Compliance (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then forward the requests and added comments to the Manager, International Branch, ANM-116. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. Special Flight Permits (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. Incorporation by Reference (f) Except as required by paragraph (b) of this AD, the actions shall be done in accordance with Airbus Service Bulletin A330-53-3074, Revision 01, dated May 19, 1998; or Airbus Service Bulletin A340-53-4085, Revision 01, dated May 19, 1998; as applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Note 4: The subject of this AD is addressed in French airworthiness directives 2000-126-114(B), dated March 8, 2000, and 2000-125-139(B), dated March 8, 2000. Effective Date (g) This amendment becomes effective on April 20, 2001. Issued in Renton, Washington, on March 26, 2001. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-7960 Filed 4-4-01; 8:45 am] BILLING CODE 4910-13-U