97-13-04: Inspect Thrust Reverser Control Lever Springs

97-13-04 AIRBUS INDUSTRIE: Amendment 39-10050. Docket 96-NM-165-AD. Supersedes AD 96-04-05, Amendment 39-9517. Applicability: Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4- 203 series airplanes, equipped with General Electric CF6-50 series engines or Pratt & Whitney JT9D-59A engine; 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 hasnot been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To detect broken or deformed thrust reverser control lever springs before they lead to uncommanded deployment of a thrust reverser and consequent reduced controllability of the airplane, accomplish the following: RESTATEMENT OF REQUIREMENTS OF AD 96-04-05, AMENDMENT 39-9517: (a) Within 500 flight hours after March 22, 1996 (the effective date AD 96-04-05, amendment 39-9517), perform a mechanical integrity inspection to detect discrepancies of the thrust reverser control lever spring having part number (P/N) A2791294520000, and an operational test to verify the integrity of the flight inhibition circuit of the thrust reverser system, in accordance with Airbus All Operators Telex (AOT) 78-03, Revision 1, dated July 20, 1994. (1) If no discrepancies are detected, no further action is required by paragraph (a) of thisAD. (2) If the control lever spring is found broken or out of tolerance, prior to further flight, replace it with a new control lever spring or deactivate the associated thrust reverser in accordance with the AOT. (3) If the flight inhibition circuit of the thrust reverser system fails the operational test, prior to further flight, determine the origin of the malfunction, in accordance with the AOT. (i) If the origin of the malfunction is identified, prior to further flight, repair the flight inhibition circuit in accordance with the AOT. (ii) If the origin of the malfunction is not identified, prior to further flight, replace the relay having P/N 125GB or 124GB, and repeat the operational test, in accordance with the AOT. If the malfunction is still present, prior to further flight, inspect and repair the wiring in accordance with the AOT. If the malfunction is still present following the inspection and repair, prior to further flight, deactivate the associated thrust reverser in accordance with the AOT. NEW REQUIREMENTS OF THIS AD: (b) Within 60 days after the effective date of this AD, replace the left and right control levers of the thrust reverser with new control levers equipped with new springs, in accordance with Airbus Service Bulletin A300-78-0015, Revision 2, dated May 24, 1996, as revised by Change Notice 2.A., dated May 24, 1996. After replacement, no further action is required by this AD. NOTE 2: Accomplishment of the replacement in accordance with either the original issue or Revision 1 of Airbus Service Bulletin A300-78-0015 is not considered acceptable for compliance with the applicable action specified in this AD. (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 actions shall be done in accordance with Airbus All Operators Telex (AOT) 78-03, Revision 1, dated July 20, 1994; and Airbus Service Bulletin A300-78-0015, Revision 2, dated May 24, 1996, as revised by Change Notice 2.A., dated May 24, 1996, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page Change Notice 2.A. -- May 24, 1996 1, 3-16, 19 2 May 24, 1996 21 November 22, 1995 17, 18 Original May 17, 1995 The incorporation by reference of Airbus AOT 78-03, Revision 1, dated July 20, 1994, was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of March 22, 1996 (61 FR 6503, February 21, 1996). The incorporation by reference of Airbus Service Bulletin A300-78-0015, Revision 2, dated May 24, 1996, as revised by Change Notice 2.A., dated May 24, 1996, is 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. (f) This amendment becomes effective on July 30, 1997.