AD 98-25-07 Airworthiness Directives; Airbus Model A300-600 Series Airplanes

Models named: A300-600 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A300-600 series airplanes on which Airbus Modification 10453 has not been installed; certificated in any category. 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 (e) 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 cracks in the center wing box angle fitting, which could result in the failure of the center wing box at frame 40, and consequent reduced structural integrity of the airplane, accomplish the following: (a) Prior to the accumulation of the threshold specified in Table 1 of this AD, as applicable, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later: Perform a detailed visual, eddy current, or liquid penetrant inspection to detect cracking in the angle fitting of frame 40 (both left and right), with the nut removed, in accordance with Airbus Service Bulletin A300-57-6052, Revision 1, dated July 22, 1996. Thereafter, repeat the inspections at the interval specified in Table 1 of this AD, as applicable, until the actions required by paragraph (c) of this AD have been accomplished. [[Page 68169]] Table 1 ---------------------------------------------------------------------------------------------------------------- Eddy current/ Visual liquid Threshold inspection penetrant Average flight time (AFT): flight hours/flight cycles (flight interval inspection cycles) (flight interval cycles) (flight cycles) ---------------------------------------------------------------------------------------------------------------- 2.10-2.49....................................................... 5,900 4,700 5,300 2.50-2.99....................................................... 5,600 4,400 4,900 3.00-3.49....................................................... 5,200 4,100 4,600 3.50-3.99....................................................... 4,800 3,800 4,200 4.00-4.49....................................................... 4,400 3,500 3,900 4.50-4.99....................................................... 4,000 3,200 3,500 5.00-5.49....................................................... 3,600 2,800 3,200 5.50-5.99....................................................... 3,200 2,500 2,800 6.00-6.50....................................................... 2,800 2,200 2,500 ---------------------------------------------------------------------------------------------------------------- (b) Except as provided by paragraph (d) of this AD, if any crack is found during an inspection required by paragraph (a) of this AD, prior to further flight, accomplish follow-on corrective actions in accordance with the procedures specified in Airbus Service Bulletin A300-57-6052, Revision 1, dated July 22, 1996. (c) Within 4 years after the effective date of this AD, modify the angle fitting at frame 40 (both left and right) in accordance with Airbus Service Bulletin A300-57-6053, Revision 1, dated October 31, 1995. Accomplishment of the modification constitutes terminating action for the repetitive inspections required by paragraph (a) of this AD. (d) If any crack is found during an inspection required by paragraph (a) of this AD, and the applicable service bulletin specifies to contact the manufacturer for an appropriate action: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. (e) 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (f) 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. (g) Except as provided by paragraph (d) of this AD, the actions shall be done in accordance with Airbus Service Bulletin A300-57- 6052, Revision 1, dated July 22, 1996; and Airbus Service Bulletin A300-57-6053, Revision 1, dated October 31, 1995, which contains the following list of effective pages: ---------------------------------------------------------------------------------------------------------------- Revision level shown Page No. on page Date shown on page ---------------------------------------------------------------------------------------------------------------- 1, 7-9, 11-15, 19-24, 35, 36, 41, 42, 45-47.... 1 October 31, 1995. 2-6, 10, 16-18, 25-34, 37-40, 43, 44........... Original February 21, 1995. ---------------------------------------------------------------------------------------------------------------- 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 3: The subject of this AD is addressed in French airworthiness directive (CN) 95-111-181(B) R1, dated October 23, 1996. (h) This amendment becomes effective on January 14, 1999. Issued in Renton, Washington, on December 2, 1998. John W. McGraw, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-32623 Filed 12-9-98; 8:45 am] BILLING CODE 4910-13-P