AD 2001-08-12 Airworthiness Directives; Airbus Model A340 Series Airplanes Equipped With CFM International CFM56-5C Engines

Models named: A340 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A340 series airplanes, certificated in any category, equipped with CFM International CFM56-5C engines. 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 (f) 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 detect and correct cracking of the pivoting door roller fittings on the thrust reversers, which could result in failure of the primary locking mechanism of the thrust reversers during flight, leading to reduced controllability of the airplane, accomplish the following: Inspections (a) Except as required by paragraph (b) of this AD, perform a special detailed inspection of the pivoting door roller fittings for cracks, using the eddy current or the fluorescent penetrant procedure. The inspection must be performed in accordance with Airbus Service Bulletin A340-78-4017, dated October 14, 1999, and must be performed at the later of the times specified in paragraphs (a)(1) and (a)(2). (1) Prior to the accumulation of 7,000 total flight hours or 1,200 total flight cycles, whichever occurs first; or (2) Within 500 flight hours after the effective date of this AD. Note 2: ROHR Alert Service Bulletin RA340A78-57, Revision 1, dated May 18, 1999, is an additional source of service information for accomplishment of the special detailed inspection and replacement of the pivoting door roller fittings on the thrust reversers. (b) Whenever a high engine vibration advisory occurs: Prior to the next flight, perform a special detailed inspection of the pivoting door roller fittings for cracks, using an eddy current or fluorescent penetrant procedure, in accordance with Airbus Service Bulletin A340-78-4017, dated October 14, 1999. Corrective Action (c) If no crack is detected during any inspection of the pivoting door roller fittings on the thrust reversers as required by paragraph (a) or (b) of this AD, repeat the inspection at intervals not to exceed 500 flight hours. (d) If a crack is detected during any inspection of the pivoting door roller fittings on the thrust reversers as required by paragraph (a) or (b) of this AD, prior to further flight, accomplish either paragraph (d)(1) or (d)(2) of this AD. (1) Replace the fittings which are cracked with new fittings and repeat the inspection required by paragraph (a) at intervals not to exceed 500 flight hours; or (2) Replace all 4 fittings with new fittings and repeat the inspection required by paragraph (a) every 7,000 flight hours or 1,200 flight cycles, whichever comes first. (e) If the inspection required by paragraph (a) or (b) cannot be performed, or if the inspection is performed and a fitting is found to be cracked, but it cannot be replaced prior to the next flight, perform a secondary lock functional test in accordance with Aircraft Maintenance Manual (AMM) 78-31-41-720-050 and deactivate the thrust reversers in accordance with AMM 78-30-00-040-802 and the FAA-approved Master Minimum Equipment List. Note 3: Operators are reminded of the limit of three calendar days imposed on deactivation of thrust reversers not modified in accordance with BFGoodrich AOW/CFM56-97-017 and Airbus All Operators Telex (AOT) A340/AOT 78-06, dated May 28, 1998. Alternative Methods of Compliance (f) 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, Transport Airplane Directorate, FAA. 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 4: 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 (g) 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 (h) Except as provided by paragraph (e) of this AD, the actions must be done in accordance with Airbus Service Bulletin A340-78-4017, dated October 14, 1999. 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 5: The subject of this AD is addressed in French airworthiness directive 1998-543-105(B) R2, dated November 17, 1999. Effective Date (i) This amendment becomes effective on May 11, 2001. Issued in Renton, Washington, on April 16, 2001. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-9878 Filed 4-25-01; 8:45 am] BILLING CODE 4910-13-P