AD 98-09-30 Airworthiness Directives; Airbus Model A330-301 Series Airplanes

Models named: A330-301 series. Read the applicability below — it usually turns on serial or part numbers too.

Airbus Model A330-301 series airplanes equipped with Pratt & Whitney or General Electric engines on which Airbus Modification 44649 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 fuel from leaking into the pylon primary structure and into the engine nacelle core zone, which could result in a fire in the engine; accomplish the following: (a) Within 500 flight hours after the effective date of this AD, perform a one-time visual inspection to measure the clearances between the engine forward feed pipe and the shroud sleeve of the left- and right-hand engine pylons, in accordance with Airbus Service Bulletin A330-28-3046, Revision 01, dated November 12, 1996. If the measured clearance is greater than 6 millimeters (mm), no further action is required by this AD. (b) If the measured clearance is less than or equal to 6 mm, prior to further flight, perform an operational test to check for fuel leaks in accordance with Airbus Service Bulletin A330-28-3046, Revision 01, dated November 12, 1996. (1) If no leaking is found, repeat the operational test thereafter at intervals not to exceed 500 flight hours until the requirements of paragraph (c) of this AD are accomplished. (2) If any leaking is found, prior to further flight, replace the shroud sleeve with a new improved part in accordance with Airbus Service Bulletin A330-28-3045, dated August 9, 1996. Accomplishment of this replacement constitutes terminating action for the repetitive operational testing requirements of this AD. (c) For any airplane on which the measured clearance is less than or equal to 6 mm and no leaking is found during any operational test required by paragraph (b) of this AD: Within 1 year after the effective date of this AD, replace the shroud sleeve with a new improved part in accordance with Airbus Service Bulletin A330-28- 3045, dated August 9, 1996. Accomplishment of this modification constitutes terminating action for the repetitive operational testing requirements of paragraph (b) of this AD. (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, 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, 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 Secs. 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 replacement shall be done in accordance with Airbus Service Bulletin A330-28-3045, dated August 9, 1996. The inspection and operational test (if accomplished) shall be done in accordance with Airbus Service Bulletin A330-28-3046, Revision 01, dated November 12, 1996. 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 96-174-034(B)R1, dated January 2, 1997. (g) This amendment becomes effective on May 20, 1998. Issued in Renton, Washington, on April 24, 1998. Gary L. Killion, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-11563 Filed 5-4-98; 8:45 am] BILLING CODE 4910-13-U