AD 95-21-09 Airworthiness Directives; Airbus Model A300 and A300-600 Series Airplanes

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

All Model A300 and A300-600 series airplanes, 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 (f) of this AD 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 asymmetry of the No. 2 flaps, accomplish the following: Note 2: Paragraph (a) of this AD restates the requirement for an initial and repetitive inspections contained in paragraph A. of AD 85-07-04. Therefore, for operators who have previously accomplished at least the initial inspection in accordance with AD 85-07-04, paragraph (a) of this AD requires that the next scheduled inspection be performed within the intervals specified in (a)(1), (a)(2), or (a)(3), as applicable, after the last inspection performed in accordance with paragraph A. of AD 85-07-04. Note 3: Measurement of crack length is performed by measurement of the probe displacement (perpendicular to symmetry plane of beam) between defect indication appearance and its complete disappearance. The bolt hole indication should not be interpreted as an indication of a defect. These two indications appear very close together because the defects originate from the bolt holes. (a) For Model A300 series airplanes: Prior to the accumulation of 15,000 total landings, or within the next 120 days after May 9, 1985 (the effective date of AD 85-07-04, amendment 39-5027), whichever occurs later, inspect for cracking of the base steel member and light alloy side members of the No. 2 flap beams, left hand and right hand, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-116, Revision 6, dated July 16, 1993. Note 4: Inspections required by paragraph (a) of this AD that have been accomplished prior to the effective date of this AD in accordance with Airbus Service Bulletin A300-57-116, Revision 1, dated August 27, 1983; Revision 2, dated April 24, 1984; Revision 3, dated July 20, 1984; Revision 4, dated August 13, 1986; or Revision 5, dated July 10, 1989; as applicable; are considered acceptable for compliance with the applicable action specified in this amendment. (1) If no cracking is detected: Except as provided by paragraph (c) of this AD, repeat the inspection at intervals not to exceed 1,700 landings until the requirements of paragraph (b) of this AD are accomplished. (2) If any crack is detected that is less than or equal to 4 mm: Repeat the inspection at intervals not to exceed 250 landings, until the requirements of paragraph (b) of this AD are accomplished. (3) If any crack is detected that exceeds 4 mm: Prior to further flight, replace the flap beam in accordance with the service bulletin, and prior to the accumulation of 15,000 flight cycles on the replaced flap beam, perform the ultrasonic inspection as required by paragraph (b) of this AD. (b) For Model A300 series airplanes: Prior to the accumulation of 15,000 total landings, or within the next 1,000 landings after the effective date of this AD, whichever occurs later, perform an ultrasonic inspection to detect cracking of the No. 2 flap beams, in accordance with Airbus Service Bulletin No. A300-57-116, Revision 6, dated July 16, 1993. Accomplishment of this inspection terminates the inspection required by paragraph (a) of this AD. (1) If no cracking is detected: Except as provided by paragraph (c) of this AD, repeat the ultrasonic inspections thereafter at intervals not to exceed 1,700 landings. (2) If any crack is detected beyond the bolt hole, and that crack is less than or equal to 4 mm in length: Repeat the ultrasonic inspections thereafter at intervals not to exceed 250 landings. (3) If any crack is detected beyond the bolt hole and that crack is greater than 4 mm in length: Prior to further flight, replace the flap beam in accordance with the service bulletin, and prior to the accumulation of 15,000 flight cycles on the replaced flap beam, perform the ultrasonic inspection as required by this paragraph. (c) For Model A300 series airplanes: After accomplishing the initial inspection required by paragraph (b) of this AD, accomplishment of either paragraph (c)(1) or (c)(2) of this AD extends the fatigue life of the No. 2 flap track beam as specified in those paragraphs, provided that no cracking is detected during any inspection required by paragraph (a) or (b) of this AD. (1) Removal of any damage and the installation of larger diameter bolts on the No. 2 flap track beam (Modification No. 4740), in accordance with Airbus Service Bulletin No. A300-57-128, Revision 3, dated January 26, 1990, extends the interval for the first repetitive inspection required by paragraph (b) of this AD from 1,700 landings to 12,000 landings, provided that Modification No. 4740 is accomplished prior to the accumulation of 16,700 total landings on the flap beams. Following accomplishment of the first repetitive inspection, subsequent repetitive inspections shall be performed at intervals not to exceed 1,700 landings. Or (2) Cold working of the bolt holes and the installation of larger diameter bolts on the No. 2 flap track beam (Modification No. 5815), in accordance with Airbus Service Bulletin No. A300-57-141, Revision 7, dated July 16, 1993, extends the interval for the first repetitive inspection required by paragraph (b) of this AD from 1,700 landings to the interval specified in paragraph (c)(2)(i) or (c)(2)(ii) of this AD. (i) If interference fit bolts that are 15/32-inch in diameter are fitted, the interval for the first repetitive inspection required by paragraph (b) of this AD is extended to 22,000 landings, provided that Modification 5815 is accomplished prior to the accumulation of 16,700 total landings on the flap beam. Following accomplishment of the first repetitive inspection required by paragraph (b) of this AD, subsequent repetitive inspections shall be performed at intervals not to exceed 1,700 landings. Or (ii) If interference fit bolts that are 7/16- or 3/8-inch in diameter are fitted, the interval for the first repetitive inspection required by paragraph (b) of this AD is extended to 33,000 landings, provided that Modification 5815 is accomplished prior to the accumulation of 16,700 total landings on the flap beam. Following accomplishment of the first repetitive inspection required by paragraph (b) of this AD, subsequent repetitive inspections shall be performed at intervals not to exceed 1,700 landings. (d) For Model A300-600 series airplanes: Prior to the accumulation of 15,000 total [[Page 53849]] landings, or within the next 1,000 landings after the effective date of this AD, whichever occurs later, perform an ultrasonic inspection to detect cracking of the No. 2 flap track beams, in accordance with Airbus Service Bulletin No. A300-57-6005, Revision 2, dated December 16, 1993. (1) If no cracking is detected, repeat the ultrasonic inspections thereafter at intervals not to exceed 1,700 landings. (2) If any crack is detected beyond the bolt hole and that crack is less than or equal to 4 mm in length: Repeat the ultrasonic inspections thereafter at intervals not to exceed 250 landings. (3) If any crack is detected beyond the bolt hole and that crack is greater than 4 mm in length: Prior to further flight, replace the flap beam in accordance with the service bulletin, and prior to the accumulation of 15,000 landings on the replaced flap beam, perform the ultrasonic inspection required by paragraph (d) of this AD. (e) For Model A300-600 series airplanes: Installation of oversized transition fit bolts in cold-worked holes, in accordance with Airbus Service Bulletin No. A300-57-6006 (Modification 5815), Revision 4, dated July 25, 1994, constitutes terminating action for the repetitive inspection requirements of paragraph (d) of this AD, provided that no cracking is detected during any inspection required by paragraph (d) of this AD, and provided that the installation is accomplished prior to the accumulation of 15,000 total landings. If any bolt requires oversizing above 7/16-inch diameter during accomplishment of this installation, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Note 5: If Airbus Service Bulletin No. A300-57-6005, Revision 2, dated December 16, 1993, is accomplished concurrently with Airbus Service Bulletin No. A300-57-6006 , Revision 3, dated December 16, 1993 (Modification 5815), the ultrasonic inspection for cracking required by paragraph (d) of this AD need not be performed since the eddy current inspection detailed for Modification 5815 is more comprehensive. (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, 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 6: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (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. (h) The actions shall be done in accordance with the following Airbus service bulletins, which contain the specified list of effective pages: ---------------------------------------------------------------------------------------------------------------- Revision level - Service bulletin referenced and date- Page No. shown on page Date shown on page ---------------------------------------------------------------------------------------------------------------- A300-57-116, Revision 6, July 16, 1993.... 1-11 6 July 16, 1993. A300-57-128, Revision 3, January 26, 1990. 1 3 January 26, 1990. 2-5 1 February 7, 1986. 6-14 Original August 27, 1983. A300-57-141, Revision 7, July 16, 1993.... 1-24 7 July 16, 1993. A300-57-6005, Revision 2, December 16, 1-4 2 December 16, 1993. 1993-. 5-7, 9 1 February 26, 1993. 8 Original August 13, 1986. A300-57-6006, Revision 4, July 25, 1994... 1, 2, 5, 7 4 July 25, 1994. 3, 4, 6, 8-20 3 December 16, 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. (i) This amendment becomes effective on November 17, 1995. Issued in Renton, Washington, on October 3, 1995. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 95-25029 Filed 10-17-95; 8:45 am] BILLING CODE 4910-13-U