AD 98-07-24 Airworthiness Directives; Airbus Model A340 Series Airplanes

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

Model A340 series airplanes on which Airbus Modification 42606 has not been accomplished, 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 (d) 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 fatigue cracking in the vertical support beam that supports the actuator attachment fitting of the center landing gear (CLG), which could result in reduced structural integrity of the airplane, accomplish the following: (a) Prior to the accumulation of 6,400 total flight cycles, or within 30 days after the effective date of this AD, whichever occurs later, perform a rototest inspection for fatigue cracking of the vertical support beam at the upper first fastener row of the CLG actuator attachment fitting (zones 147 and 148), in accordance with Airbus Service Bulletin A340-53-4043, Revision 02, dated July 18, 1997. (b) If the inspection accomplished in paragraph (a) of this AD reveals no cracking, accomplish either paragraph (b)(1) or (b)(2) of this AD: (1) Prior to further flight, replace the CLG actuator attachment fitting with new parts, and reinforce the vertical support beam by adding one stiffening fitting on each side, in accordance with Airbus Service Bulletin A340-53-4030, Revision 1, dated February 22, 1996. Accomplishment of the replacement and reinforcement constitutes terminating action for the requirements of this AD. Or (2) Prior to the accumulation of 11,100 total flight cycles, or within 30 days after the effective date of this AD, whichever occurs later: Repeat the rototest inspection of the vertical support beam at the upper first fastener row of the CLG actuator attachment fitting (zones 147 and 148), in accordance with Airbus Service Bulletin A340-53-4043, Revision 02, dated July 18, 1997. (i) If the inspection accomplished in paragraph (b)(2) of this AD reveals no cracking: Prior to further flight, replace the CLG actuator attachment fitting with new parts, and reinforce the vertical support beam by adding one stiffening fitting on each side, in accordance with Airbus Service Bulletin A340-53-4030, Revision 1, dated February 22, 1996. Accomplishment of the replacement and reinforcement constitute terminating action for the requirements of this AD. (ii) If the inspection accomplished in paragraph (b)(2) of this AD reveals any cracking: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate. (c) If the inspection accomplished in paragraph (a) of this AD reveals any cracking: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM- 116. (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, International Branch, ANM-116. 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 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. (e) 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. (f) The inspections and modifications required by this AD shall be done in accordance with the following Airbus service bulletins, which contain the specified list of effective pages: [[Page 16107]] ---------------------------------------------------------------------------------------------------------------- Service bulletin referenced Revision level shown on and date Page number page Date shown on page ---------------------------------------------------------------------------------------------------------------- A340-53-4043, Revision 02, 1-15...................... 02........................ July 18, 1997. July 18, 1997. A340-53-4030, Revision 1, 1, 2, 8-9, 17............. 1......................... February 22, 1996. February 22, 1996. 3-7, 10-16................ Original.................. March 13, 1995. ---------------------------------------------------------------------------------------------------------------- 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 96-105-043(B)R1, dated July 30, 1997. (g) This amendment becomes effective on April 17, 1998. Issued in Renton, Washington, on March 26, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-8543 Filed 4-1-98; 8:45 am] BILLING CODE 4910-13-U