AD 97-10-01 Airworthiness Directives; Airbus Industrie Model A310 Series Airplanes

Models named: A310 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A310 series airplanes, on which Airbus Modification 10962 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 (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 failure of the flap transmission shaft due to damaged steady bearing assemblies, which could cause an uncommanded asymmetric retraction of the flap, and result in reduced controllability of the airplane, accomplish the following: (a) Prior to the accumulation of 2,000 total landings or within 500 flight hours after the effective date of this AD, whichever occurs later: Perform a visual inspection to detect damage or any discrepancy of the steady bearing assemblies of the flap transmission system, in accordance with Airbus Service Bulletin A310-27-2067, Revision 1, dated January 5, 1995. (1) If no damage or discrepancy is detected: Repeat the inspection thereafter at intervals not to exceed 2,000 landings, until the requirements of paragraph (b) of this AD are accomplished. (2) If any damage or discrepancy is detected and the groove depth of the shaft is less than 1 mm (.04 inch): Prior to the accumulation of 50 landings after detection of this discrepancy, replace the steady bearing assembly with a new, like assembly in accordance with Airbus Service Bulletin A310-27-2067, Revision 1, dated January 5, 1995. (3) If any damage or discrepancy is detected and the groove depth on the shaft is 1 mm or more: Prior to further flight, replace the steady bearing assembly with a new, like assembly, in accordance with Airbus Service Bulletin A310-27-2067, Revision 1, dated January 5, 1995. (b) Within 5 years after the effective date of this AD, replace all steady bearing assemblies of the flap transmission system with new, improved assemblies, in accordance with Airbus A310-27-2074, dated November 18, 1994. Accomplishment of the replacement constitutes terminating action for the requirements of this AD. Note 2: Airbus Service Bulletin A310-27-2074 references Lucas Liebherr Service Bulletin 551A-27-M551-03 as an additional source of service information for replacement of the steady bearing assemblies with the new, improved assemblies. (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, Standardization Branch, ANM-113, 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, Standardization Branch, ANM-113. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) 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. (e) The inspection and certain replacements shall be done in accordance with Airbus Service Bulletin A310-27-2067, Revision 1, dated January 5, 1995. Certain other replacements shall be done in accordance with Airbus Service Bulletin A310-27-2074, dated November 18, 1994. 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 [[Page 24570]] Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on June 10, 1997. Issued in Renton, Washington, on April 28, 1997. Neil D. Schalekamp, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 97-11525 Filed 5-5-97; 8:45 am] BILLING CODE 4910-13-U