AD 98-21-30 Airworthiness Directives; Airbus Model A300, A310, and A300-600 Series Airplanes

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

Model A300 series airplanes on which Airbus Modification 3599 or 3135 (reference Airbus Service Bulletin A300- 53-0188) has been accomplished, and all Model A310 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 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 (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 wear damage of the aft attachment fittings of the articulated seats and dummy tracks in the passenger compartment, which could cause the floor panels to sag and result in failure of flight control systems and consequent reduced controllability of the airplane, accomplish the following: (a) Perform a detailed visual inspection for wear damage of the aft attachment fittings of the articulated seats and dummy tracks in the passenger compartment, in accordance with Airbus Service Bulletins A300-53-0329, Revision 01 (for Airbus Model A300 series airplanes); A300-53-6105, Revision 01 (for Airbus Model A300-600 series airplanes); or A310-53-2101, Revision 01 (for Airbus Model A310 series airplanes), all dated October 17, 1997; at the applicable time specified in paragraph (a)(1) or (a)(2) of this AD. (1) For airplanes that have accumulated less than 12,000 total flight cycles as of the effective date of this AD: Inspect prior to the accumulation of 6,000 total flight cycles, or within 18 months after the effective date of this AD, whichever occurs later. (2) For airplanes that have accumulated 12,000 or more total flight cycles as of the effective date of this AD: Inspect within 12 months after the effective date of this AD. (b) If no wear damage is detected during the inspection required by paragraph (a) of this AD, repeat the detailed visual inspection thereafter at intervals not to exceed 6,000 flight cycles. (c) If any wear damage measuring 1 mm (0.039 in.) or less is detected during the inspection required by paragraph (a) of this AD, accomplish either paragraph (c)(1) or (c)(2) of this AD, in accordance with Airbus Service Bulletin A300-53-0329, Revision 01 (for Airbus Model A300 series airplanes); A300-53-6105, Revision 01 (for Airbus Model A300-600 series airplanes); or A310-53-2101, Revision 01 (for Airbus Model A310 series airplanes); all dated October 17, 1997; as applicable. (1) Repeat the inspection required by paragraph (a) of this AD at the interval specified in Figure 1, Sheet 1, of the applicable service bulletin, for the depth of wear damage detected. Or, (2) Prior to further flight, repair the wear damage. Thereafter, repeat the inspection required by paragraph (a) of this AD at intervals not to exceed 6,000 flight cycles. (d) If any wear damage measuring more than 1 mm (0.039 in.), and less than or equal to 2 mm (0.078 in.), is detected during the inspection required by paragraph (a) of this AD: Prior to further flight, repair in accordance with Airbus Service Bulletin A300-53- 0329, Revision 01 (for Airbus Model A300 series airplanes); A300-53- 6105, Revision 01 (for Airbus Model A300-600 series airplanes); or A310-53-2101, Revision 01 (for Airbus Model A310 series airplanes); all dated October 17, 1997; as applicable. Repeat the inspection thereafter at intervals not to exceed 6,000 flight cycles. (e) If any wear damage measuring more than 2 mm (0.078 in.) is detected during the inspection required by paragraph (a) of this AD, prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. Repeat the visual inspection thereafter at intervals not to exceed 6,000 flight cycles. (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, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintence 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. (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) Except as provided by paragraph (e) of this AD, the actions shall be done in accordance with Airbus Service Bulletin A300-53- 0329, Revision 01, dated October 17, 1997; Airbus Service Bulletin A300-53-6105, Revision 01, dated October 17, 1997; or A310-53-2101, Revision 01, dated October [[Page 55517]] 17, 1997; as applicable. 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 97-116-222(B), dated May 21, 1997. (i) This amendment becomes effective on November 20, 1998. Issued in Renton, Washington, on October 6, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-27460 Filed 10-15-98; 8:45 am] BILLING CODE 4910-13-U