99-21-19: Titanium Thrust Links

99-21-19 AIRBUS INDUSTRIE: Amendment 39-11364. Docket 99-NM-96-AD. Applicability: Model A319-131, A320-232 and -233, and A321-131 and -231 series airplanes; except those airplanes on which Airbus Modification 26506 (reference Airbus Service Bulletin A320-71-1020, dated May 25, 1998) has been accomplished in production; 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 (b) 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 prevent failure of the titanium thrust links due to the life limit of the thrust links, which in combination with other failures, could result in the separation of an engine from the airplane, accomplish the following: (a) Replace all titanium thrust links with steel thrust links in accordance with Airbus Service Bulletin A320-71-1020, dated May 25, 1998; at the later of the times specified in paragraphs (a)(1) and (a)(2) of this AD. (1) Prior to the accumulation of the total flight cycles specified for each particular model in the tables of paragraph B.(5), "Accomplishment Timescale," of the service bulletin. (2) Within 15 months after the effective date of this AD, or at the next engine removal, whichever occurs first. Alternative Methods of Compliance (b) 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, FAA, Transport Airplane Directorate. 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. Special Flight Permits (c) 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 (d) The replacement shall be done in accordance with Airbus Service Bulletin A320-71-1020, dated May 25, 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 3: The subject of this AD is addressed in French airworthiness directive 1999-050-126(B), dated February 10, 1999. (e) This amendment becomes effective on November 17, 1999.