AD 97-06-01

97-06-01 CFM International: Amendment 39-9958. Docket 95-ANE-65. Applicability: CFM International (CFMI) CFM56-5, -5B, and -5C series turbofan engines, installed on but not limited to Airbus A320, A321, and A340 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 (h) 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. Compliance: Required as indicated, unless accomplished previously. To prevent a failure of the stage 1 disk of the high pressure compressor rotor (HPCR) stage 1-2 spool, which could result in an uncontained engine failure and damage to the aircraft, accomplish the following: (a) For CFM56-5, -5B, and -5C engines that have a stationary number 3 bearing aft air/oil seal, Part Number (P/N) 1364M71G02, installed, inspect the stage 1 disk of the HPCR stage 1-2 spool in accordance with the Accomplishment Instructions of CFM56-5 Service Bulletin (SB) No. 72-440, CFM56-5B SB No. 72-064, or CFM56-5C SB No. 72-229, all Revision 2, dated June 23, 1995, as applicable, as follows: (1) If the disk has not been previously inspected prior to the effective date of this AD, inspect prior to accumulating 2,200 cycles since new (CSN). (2) If the disk has been previously inspected prior to the effective date of this AD, and the disk was found not to be rubbed or scratched, reinspect prior to accumulating 2,200 cycles since last inspection (CSLI). (b) Thereafter, for disks that have been inspected in accordance with paragraph (a)(1) or (a)(2) of this AD, inspect in accordance with the Accomplishment Instructions of CFM56-5 SB No. 72-440, CFM56-5B SB No. 72-064, or CFM56-5C SB No. 72-229, all Revision 2, dated June 23, 1995, as applicable, at intervals not to exceed 2,200 CSLI. (c) Remove from service HPCR stage 1-2 spools with rubbed or scratched stage 1 disks and replace with a serviceable part, as follows: (1) For spools with less than 2,200 CSN on the effective date of this AD, at the next engine shop visit after the effective date of this AD, or prior to accumulating 2,200 CSN, whichever occurs first. (2) For spools with 2,200 CSN or more on the effective date of this AD, at the next engine shop visit after the effective date of this AD, or prior to accumulating 2,200 CSLI, whichever occurs first. (d) Remove from service stationary number 3 aft air/oil seals, P/N 1364M71G02, at the next engine shop visit after the effective date of this AD, and replace with a serviceable part. Compliance with this paragraph constitutes terminating action to the inspection requirements of paragraphs (a)(1), (a)(2), and (b) of this AD. (e) For the purpose of this AD, a serviceable HPCR stage 1-2 spool is defined as a spool without a rub or scratch indication on the stage 1 disk, a P/N 1834M55G01 spool, or a spool that has accomplished the stage 1 disk rework in accordance with any revision level of CFM56-5 SB No. 72-442, CFM56-5B SB No. 72-066, or CFM56-5C SB No. 72-230, as applicable. (f) For the purpose of this AD, a serviceable stationary number 3 bearing aft air/oil seal is defined as any seal other than a P/N 1364M71G02 seal. (g) For the purpose of this AD, an engine shop visit is defined as the induction of an engine into the shop for any reason. (h) An alternative method of compliance or adjustment of the compliance time that providesan acceptable level of safety may be used if approved by the Manager, Engine Certification Office. The request should be forwarded 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. (i) 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 aircraft to a location where the requirements of this AD can be accomplished. (j) The actions required by this AD shall be done in accordance with the following CFMI SBs:

Document No Pages Revision Date CFM56-5 SB No. 72-440 1-9 2 June 23, 1995 Total pages: 9.

CFM56-5B SB No. 72-064 1-9 2 June 23, 1995 Total pages: 9.CFM56-5C SB No. 72-229 1-9 2 June 23, 1995 Total Pages: 9.

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 CFM International, Technical Publications Department, One Neumann Way, Cincinnati, OH 45215; telephone (513) 552-2981, fax (513) 552-2816. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief 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. (k) This amendment becomes effective on June 3, 1997.