AD 97-09-04 Airworthiness Directives; Airbus Industrie Model A320, A321, A330, and A340 Series Airplanes Equipped With Westland-Sitec Fire Shutoff Valves Having Part Number EO3000

Models named: A320, A321, A330, A340 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A320, A321, A330 and A340 series airplanes; equipped with Westland-Sitec fire shutoff valves having part number E03000; 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 has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To prevent the flow of hydraulic fluid to the engine in the event of a fire, which would fuel the fire and lead to the loss of fluid in associated hydraulic systems, causing those systems to fail, accomplish the following: (a) Within 6 months after the effective date of this AD, perform a functional test (for A320 and A321 series airplanes) or an operational test (for A330 and A340 series airplanes) on each fire shutoff valve (FSOV) for the left and right engines and immediately follow this test with a check to determine whether the FSOV motor is properly operating, in accordance with Airbus All Operators Telex (AOT) 29-15, dated May 30, 1995. (1) If a FSOV passes the applicable test and check, repeat the procedures required by paragraph (a) of this AD thereafter at intervals not to exceed 18 months. (2) If a FSOV fails the applicable test or check, prior to further flight, replace the discrepant FSOV with a FSOV modified in accordance with the service bulletins specified in paragraphs (a)(2)(i), (a)(2)(ii), and (a)(2)(iii), as applicable. Modification of the seal and the electrical actuator for the motor are to be performed at the same time. The accomplishment of these modifications constitutes terminating action for the repetitive testing and checks of this FSOV required by paragraph (a) of this AD. (i) For Airbus A320 and A321 series airplanes: Airbus Service Bulletin A320-29-1071, dated September 21, 1995. (ii) For Airbus A330 series airplanes: Airbus Service Bulletin A330-29-3018, dated January 17, 1996. (iii) For Airbus A340 series airplanes: Airbus Service Bulletin A340-29-4018, dated January 17, 1996. Note 2: The Airbus service bulletins cited in paragraphs (a)(2)(i)-(iii) of this AD refer to Westland-Sitec Service Bulletin No. E030WS-29-1, dated January 12, 1996 (valve modification), and Westland-Sitec Service Bulletin No. A06AWS-24-1, dated January 12, 1996 (electrical actuator modification), as additional sources of procedural information. (b) Within 4 years after the effective date of this AD, modify the electrical actuator for the motor and the seal of each FSOV, in accordance with the service bulletins specified in paragraphs (b)(1), (b)(2), and (b)(3) of this AD, as applicable. The accomplishment of these modifications constitutes terminating action for the repetitive tests and checks required by paragraph (a) of this AD and, thereafter, no further action is required. (1) For Airbus A320 and A321 series airplanes: Airbus Service Bulletin A320-29-1071, dated September 21, 1995. (2) For Airbus A330 series airplanes: Airbus Service Bulletin A330-29-3018, dated January 17, 1996. (3) For Airbus A340 series airplanes: Airbus Service Bulletin A340-29-4018, dated January 17, 1996. (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 tests shall be done in accordance with Airbus AOT 29-15, dated May 30, 1995. The replacement and modifications shall be done in accordance with Airbus Service Bulletin A320-29-1071, dated September 21, 1995; Airbus Service Bulletin A330-29-3018, dated January 17, 1996; and Airbus Service Bulletin A340-29-4018, dated January 17, 1996; 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. (f) This amendment becomes effective on May 29, 1997. Issued in Renton, Washington, on April 16, 1997. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 97-10320 Filed 4-23-97; 8:45 am] BILLING CODE 4910-13-U