AD 99-04-03 Airworthiness Directives; International Aero Engines AG (IAE) V2500-A5/-D5 Series Turbofan Engines

Models named: V2522- A5, V2524-A5, V2527-A5, V2527E-A5, V2530-A5, V2533-A5, V2525-D5, V2528-D5 turbofan. Read the applicability below — it usually turns on serial or part numbers too.

International Aero Engines AG (IAE) Models V2522- A5, V2524-A5, V2527-A5, V2527E-A5, V2530-A5, V2533-A5, V2525-D5, V2528-D5 turbofan engines, installed on but not limited to Airbus Industrie A319, A320, A321 series and McDonnell Douglas MD-90 series aircraft. Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines 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 (e) 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 high pressure compressor (HPC) stage 9-12 drum failure, which could result in an uncontained engine failure and damage to the aircraft, accomplish the following: (a) Remove from service HPC stage 9-12 drums, part number (P/N) 6A4156, operated in a single engine model at a single thrust rating prior to accumulating the new, reduced cyclic life limits, which are dependent upon the engine installation and thrust rating, as described in Table 1 of IAE Service Bulletin (SB) No. V2500-ENG-72- 0293, dated December 19, 1997, and replace with a serviceable part. (b) Remove from service HPC stage 9-12 drums, P/N 6A4156, installed in engines which operate at a mixture of thrust ratings, prior to accumulating the cyclic life limit of the highest thrust rating employed, as described in Table 1 of IAE SB No. V2500-ENG-72- 0293, dated December 19, 1997, and replace with a serviceable part. The use of an HPC stage 9-12 drum, P/N 6A4156, at a higher thrust rating for even a single flight invokes the cyclic life limit applicable for the higher thrust rating. (c) Remove from service HPC stage 9-12 drums, P/N 6A4156, removed from one engine model and installed into another engine model or operated at different thrust ratings prior to accumulating the applicable component cyclic life limit for the engine model with the highest thrust rating, as described in Table 1 of IAE SB No. V2500-ENG-72-0293, dated December 19, 1997, regardless of the cycles in service at this rating, and replace with a serviceable part. (d) This AD establishes new cyclic retirement life limits for HPC stage 9-12 drums, part number (P/N) 6A4156. Thereafter, except as provided in paragraph (e) of this AD, no alternative cyclic retirement life limits may be approved for HPC stage 9-12 drums, P/N 6A4156. (e) 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, Engine Certification Office. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (f) 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 aircraft to a location where the requirements of this AD can be accomplished. (g) The cyclic retirement life limits shall be determined in accordance with the following International Aero Engines SB: ---------------------------------------------------------------------------------------------------------------- Document No. Pages Revision Date ---------------------------------------------------------------------------------------------------------------- V2500-ENG-72-0293.................... 1-7 Original................ December 19, 1997. Total pages: 7 ---------------------------------------------------------------------------------------------------------------- [[Page 6788]] 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 Rolls-Royce Commercial Aero Engine Limited, P. O. Box 31, Derby, England, DE2488J, Attention: Publication Services ICL-TP. Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on April 12, 1999. Issued in Burlington, Massachusetts, on February 1, 1999. David A. Downey, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 99-3037 Filed 2-10-99; 8:45 am] BILLING CODE 4910-13-P