AD 2001-06-03 Airworthiness Directives; Airbus Model A330-301, -321, -322 Series Airplanes; and Model A340 Series Airplanes

Models named: A330-301, -321, -322 series, A340 series. Read the applicability below — it usually turns on serial or part numbers too.

All Model A330-301, -321, and -322 series airplanes; and all Model A340 series airplanes; certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been 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 (c) 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 the propagation of fatigue cracking of the top wing skin and the torsion box of the aft passenger/crew doors, which could lead to reduced structural capability of the airplane, accomplish the following: Modifications (a) Do the modifications (including reaming, drilling, and cold expanding specified fastener holes; replacing fasteners; and performing high frequency eddy current inspections to detect cracking); as specified and at the applicable times in paragraphs (a)(1), (a)(2), and (a)(3) listed in Table 1 of this AD, as follows: Table 1.—Required Actions Modify Before the airplane accumulates For model Per Airbus service bulletin (1) The top wing skin and rear spar flange between wing ribs 9 and 11 (i)17,200 total flight cycles or 53,500 total flight hours, whichever occurs first A330 A330-57-3054, Revision 02, dated November 22, 1999.   (ii) 7,200 total flight cycles or 31,700 total flight hours, whichever occurs first A340 A340-57-4061, Revision 02, dated November 23, 1999. (2) The top wing skin and the rear spar flange between wing ribs 2 and 7 (i) 13,200 total flight cycles or 41,000 total flight hours, whichever occurs first A330 A330-57-3053, Revision 01, dated June 15, 1999.   (ii) 9,100 total flight cycles or 45,500 total flight hours, whichever occurs first A340, pre-Modification 41300 A340-57-4060, Revision 01, dated November 8, 1999.   (iii) 8,700 total flight cycles or 43,500 total flight hours, whichever occurs first A340, post-Modification 41300 A340-57-4060, Revision 01, dated November 8, 1999. (3) The cover plate of the torsion box of the aft passenger/crew door (i) 10,000 total flight cycles A330 A330-53-3054, Revision 01, dated May 17, 1999.   (ii) 8,750 total flight cycles A340 A340-53-4072, dated June 29, 1998. Note 2: Accomplishment, prior to the effective date of this AD, of a modification in accordance with a service bulletin listed in Table 2 of this AD is also acceptable for compliance with the applicable requirements of paragraph (a) of this AD, as follows:. Table 2.—Additional Acceptable Service Bulletins Applicable paragraph of this AD Model Applicable service bulletin Revison level Date (a)(1) A330 A330-57-3054 Original 01 May 29, 1998. June 3, 1999.   A340 A340-57-4061 Original 01 May 29, 1998. October 29, 1998. (a)(2) A330 A330-57-3053 Original September 23, 1998.   A340 A340-57-4060 Original June 3, 1999. (a)(3) A330 A330-53-3054 Original June 29, 1998. Repair (b) If any crack or assembly difference is found during any inspection required by paragraph (a) of this AD, and the applicable service bulletin specifies to contact Airbus for appropriate actopm: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Generale de l'Aviation Civile (DGAC). Alternative Methods of Compliance (c) 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 send it 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 (d) Special flight permits may be issued in accordance with §§ 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 (e) Except as required by paragraph (b) of this AD: The actions shall be done in accordance with the Airbus service bulletins listed in Table 3 of this AD, as follows: Table 3.—Service Bulletins for Incorporation by Reference Service bulletin number Revision level Date A330-57-3054 02 Nov. 22, 1999. A340-57-4061 02 Nov. 23, 1999. A330-57-3053 01 June 15, 1999. A340-57-4060 01 Nov. 8, 1999. A330-53-3054 01 May 17, 1999. A340-53-4072 Original June 29, 1998. 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 the French airworthiness directives identified in Table 4 of this AD, as follows: Table 4.—French Airworthiness Directives Airworthiness directive Date 2000-124-113(B) March 8, 2000. 2000-123-138(B) March 8, 2000. 2000-122-112(B) March 8, 2000. 2000-121-137(B) R1 October 4, 2000. 2000-135-117(B) March 22, 2000. 2000-136-142(B) March 22, 2000. Effective Date (f) This amendment becomes effective on April 9, 2001. Issued in Renton, Washington, on March 12, 2001. Vi L. Lipski, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-6644 Filed 3-22-01; 8:45 am] BILLING CODE 4910-13-U