AD 99-25-10 Airworthiness Directives; Airbus Model A319, A320, and A321 Series Airplanes

Models named: A319-131, -132, A320-232, -233, A321-131 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A319-131 and -132, A320-232 and -233, and A321-131 series airplanes; except those on which Airbus Modification 27020 has been accomplished (reference Airbus Service Bulletin A320- 71-1021, Revision 01, dated June 10, 1998); 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 structural failure of the forward engine mount secondary load path, which, if combined with failure of the primary load path, could result in separation of the engine from the airplane, accomplish the following: Inspection and Follow-On Actions (a) Within 500 flight hours after the effective date of this AD: Perform a one-time general visual inspection of the forward engine mount assembly of the left and right engines to verify that the part number (P/N) on each assembly is correct, in accordance with Airbus Service Bulletin A320-71-1021, Revision 01, dated June 10, 1998. Note 2: For the purposes of this AD, a general visual inspection is defined as ``A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or drop-light, and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.'' (1) If the P/N on the forward engine mount assembly of the left and right engines is 740-2010-513N or 740-2010-513 with a revision of N' or higher: Within 2,250 landings following accomplishment of the inspection specified in paragraph (a) of this AD, or at the next engine removal, whichever occurs first, re-identify each assembly in accordance with the service bulletin. No further action is required by this AD. (2) If the P/N on the forward engine mount assembly of the left and right engines is different from the P/N's specified in paragraph (a)(1) of this AD, or if the P/N cannot be determined: Prior to further flight, perform a detailed visual inspection to detect any crack or failure of the thrust links on each forward engine mount assembly, in accordance with the service bulletin. (i) If no crack or failure of any thrust link on the left or right engine is detected: Within 2,250 landings following accomplishment of the inspection specified in paragraph (a)(2) of this AD, or at the next engine removal, whichever occurs first, modify each engine mount and its installation, and re-identify each forward engine mount assembly; in accordance with the service bulletin. Note 3: Simultaneous modification of both engines is not required. (ii) If any crack or failure of any thrust link on the left or right engine is detected, prior to further flight, replace the existing thrust link with a new thrust link, modify each engine mount, and re-identify each forward engine mount assembly; in accordance with the service bulletin. Note 4: Inspection and modification of the engine mount assembly accomplished prior to the effective date of this AD in accordance with Airbus Service Bulletin A320-71-1021, dated February 6, 1998, is considered acceptable for compliance with the applicable actions specified in this AD. Note 5: Airbus Service Bulletin A320-71-1021, Revision 01, dated June 10, 1998, references V2500 International Aero Engines (IAE) Service Bulletin V2500-NAC-71-0135, Revision 1, dated March 5, 1998, as an additional source of service information for accomplishment of the actions specified in this AD. Spares (b) As of the effective date of this AD, no person shall install a forward engine mount assembly on any airplane equipped with IAE V2500-A5 engines, unless the actions described in Airbus Service Bulletin A320-71-1021, dated February 6, 1998, or Revision 01, dated June 10, 1998, have been accomplished for that assembly. [[Page 68625]] Alternative Methods of Compliance (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, 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 6: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. Special Flight Permits (d) 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. Incorporation by Reference (e) The actions shall be done in accordance with Airbus Service Bulletin A320-71-1021, Revision 01, dated June 10, 1998. 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 7: The subject of this AD is addressed in French airworthiness directives 98-293-118(B), dated July 2, 1998, and 98- 293-118(B) R1, dated December 16, 1998. (f) This amendment becomes effective on January 12, 2000. Issued in Renton, Washington, on November 30, 1999. D.L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 99-31471 Filed 12-7-99; 8:45 am] BILLING CODE 4910-13-U