AD 98-03-06 SUPERSEDED

98-03-06 AIRBUS INDUSTRIE: Amendment 39-10298. Docket 97-NM-178-AD.

Applicability: Model A300-600 series airplanes, as listed in Airbus Service Bulletin A300-57A6087, dated August 5, 1997; and Model A300 series airplanes, as listed in Airbus Service Bulletin A300-57A0234, dated August 5, 1997; 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 (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.

Compliance: Required as indicated, unless accomplished previously.

To detect and correct cracks in Gear Rib 5 of the main landing gear attachment fittings at the lower flange, which could result in reduced structural integrity of the airplane, accomplish the following:

(a) For Model A300 series airplanes that have accumulated more than 27,000 flight cycles as of the effective date of this AD: Except as provided by paragraph (b) of this AD, within 40 flight cycles after the effective date of this AD, perform a detailed visual inspection to detect cracks in Gear Rib 5 of the main landing gear attachment fittings at the lower flange, in accordance with Airbus Service Bulletin A300-57A0234, dated August 5, 1997. Thereafter, repeat the inspection at intervals not to exceed 40 flight cycles, until the actions required by paragraph (b) are accomplished.

(b) For all airplanes: Perform a detailed visual and a high frequency eddy current inspection to detect cracks in Gear Rib 5 of the main landing gear attachment fittings at the lower flange, in accordance with Airbus Service Bulletin A300-57A6087 (for Model A300-600 series airplanes) or A300-57A0234 (for Model A300 series airplanes), both dated August 5, 1997; as applicable; at the time specified in paragraph (b)(1) or (b)(2) of this AD, as applicable. Accomplishment of the inspection required by this paragraph terminates the inspections required by paragraph (a) of this AD.

(1) For airplanes that have accumulated 20,000 or more total flight cycles as of the effective date of this AD: Inspect within 500 flight cycles after the effective date of this AD.

(2) For airplanes that have accumulated less than 20,000 total flight cycles as of the effective date of this AD: Inspect prior to the accumulation of 18,000 total flight cycles, or within 1,500 flight cycles after the effective date of this AD, whichever occurs later.

(c) If any crack is detected during any inspection required by this AD, prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate.

(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 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.

(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.

(f) The actions shall be done in accordance with Airbus Service Bulletin A300-57A6087, dated August 5, 1997; or Airbus Service Bulletin A300-57A0234, dated August 5, 1997; 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 3: The subject of this AD is addressed in French airworthiness directive (CN) 97- 274-230(B), dated September 24, 1997.

(g) This amendment becomes effective on March 9, 1998.