AD 95-10-03 Airworthiness Directives; Airbus Industrie Model A300, A300-600, and A310 Series Airplanes

Models named: A300, A300-600, A310 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A300, A300-600, and A310 series airplanes; as listed in Revision 1 of Airbus Industrie Service Bulletin No.'s A300-54-071, A300-54-6011, and A310-54-2016, all dated October 15, 1993; 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 use the authority provided in paragraph (d) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.

Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the lower spar of the pylon, accomplish the following: (a) For Model A300 B4-2C, B2K-3C, B2-203, B4-103, and B4-203 series airplanes: Prior to the accumulation of 9,000 total landings, or within 500 landings after the effective date of this AD, whichever occurs later, perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylon between ribs 9 and 10, in accordance with Airbus Industrie Service Bulletin No. A300-54-071, dated November 12, 1991; or Revision 1, dated October 15, 1993. (1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 2,500 landings. (2) If any crack is found that is less than or equal to 30 mm: Perform subsequent inspections and repair in accordance with the methods and times specified in the service bulletin. (3) If any crack is found that is greater than 30 mm, but less than 100 mm: Prior to the accumulation of 250 landings after crack discovery, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (4) If any crack is found that is greater than or equal to 100 mm: Prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113. (5) Accomplishment of the modification specified in Airbus Industrie Service Bulletin No. A300-54-0079, dated October 15, 1993, constitutes terminating action for the inspections required by paragraph (a) of this AD. (b) For Model A300-600 B4-620, C4-620, -622R, and -622 series airplanes: Except as provided by paragraph (b)(5) of this AD, prior to the accumulation of 4,000 total landings, or within 500 landings after the effective date of this AD, whichever occurs later, perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylon between ribs 9 and 10, in accordance with Airbus Industrie Service Bulletin No. A300-54-6011, dated November 12, 1991, as amended by Service Bulletin Change Notice O.A., dated July 10, 1992; or Revision 1, dated October 15, 1993. (1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 2,500 landings. [[Page 25606]] (2) If any crack is found that is less than or equal to 30 mm: Perform subsequent inspections and repair in accordance with the methods and times specified in the service bulletin. (3) If any crack is found that is greater than 30 mm, but less than 100 mm: Prior to the accumulation of 250 landings after crack discovery, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113. (4) If any crack is found that is greater than or equal to 100 mm: Prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113. (5) Accomplishment of the modification specified in Airbus Industrie Service Bulletin No. A300-54-6019, dated October 15, 1993, increases the threshold and repetitive interval of the inspections required by paragraph (b) of this AD to the threshold and interval specified in paragraph 2.D. of the Accomplishment Instructions of Airbus Industrie Service Bulletin No. A300-54-6011, Revision 1, dated October 15, 1993. (c) For Model A310-221, -222, -322, -324, and -325 series airplanes: Prior to the accumulation of 25,000 total landings, or within 500 landings after the effective date of this AD, whichever occurs later, perform an internal eddy current inspection to detect cracks in the lower spar axis of the pylon between ribs 9 and 10, in accordance with Airbus Industrie Service Bulletin No. A310-54-2016, dated November 12, 1991; or Revision 1, dated October 15, 1993. (1) If no crack is found, repeat the inspection thereafter at intervals not to exceed 2,500 landings. (2) If any crack is found that is less than or equal to 30 mm: Perform subsequent inspections and repair in accordance with the methods and times specified in the service bulletin. (3) If any crack is found that is greater than 30 mm, but less than 100 mm: Prior to the accumulation of 250 landings after crack discovery, repair in a accordance with a method approved by the Manager, Standardization Branch, ANM-113. (4) If any crack is found that is greater than or equal to 100 mm: Prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113. (5) Accomplishment of the modification specified in Airbus Industrie Service Bulletin No. A310-54-2022, dated October 15, 1993, constitutes terminating action for the inspections required by paragraph (c) of this AD. (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, Standardization Branch, ANM-113. 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with Secs. 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 the following Airbus Industrie service bulletins, as applicable, which contain the specified effective pages: ---------------------------------------------------------------------------------------------------------------- Revision level shown on Service bulletin referenced and date Page No. page Date shown on page ---------------------------------------------------------------------------------------------------------------- A300-54-071, November 12, 1991........ 1-19................... Original............... November 12, 1991. A300-54-071, Revision 1, October 15, 1-20................... 1...................... October 15, 1993. 1993. A300-54-0079, October 15, 1993........ 1-16................... Original............... October 15, 1993. A300-54-6011, November 12, 1991....... 1-17................... Original............... November 12, 1991. Service Bulletin Change Notice O.A., (This document is not Original............... July 10, 1992. A300-54-6011, July 10, 1992. numbered). A300-54-6011, Revision 1, October 15, 1-10, 12-19............ 1...................... October 15, 1993. 1993. 11..................... Original............... November 12, 1991. A300-54-6019, October 15, 1993........ 1-11................... Original............... October 15, 1993. A310-54-2016, November 12, 1991....... 1-17................... Original............... November 12, 1991. A310-54-2016, Revision 1, October 15, 1-10, 12, 17........... 1...................... October 15, 1993. 1993. 11, 13-16.............. Original............... November 12, 1991. A310-54-2022, October 15, 1993........ 1-11................... Original............... October 15, 1993. ---------------------------------------------------------------------------------------------------------------- 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. (g) This amendment becomes effective on June 12, 1995. Issued in Renton, Washington, on April 28, 1995. James V. Devany, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 95-10986 Filed 5-11-95; 8:45 am] BILLING CODE 4910-13-U