97-09-02 R2: Low pressure turbine rotor (LPTR)

97-09-02R2 CFM International: Amendment 39-13094. Docket No. 95-ANE- 64-AD. Applicability: This airworthiness directive (AD) is applicable to CFM International (CFMI) CFM56-5C2/G, -5C3/G, and -5C4 series turbofan engines. These engines are installed on, but not limited to, Airbus Industrie A340 series airplanes. Note 1: This 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 (i) 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: Compliance with this AD is required as indicated, unless already done. To prevent low cycle fatigue (LCF) failure of the high pressure turbine rotor (HPTR) front shaft, HPTR front air seal, and booster spool, which could result in an uncontained failure and damage to the airplane, do the following: (a) Remove from service HPTR front shafts, part numbers (P/Ns) 1498M40P03, 1498M40P05, and 1498M40P06, before accumulating 8,400 cycles-since-new (CSN), and replace with a serviceable part. (b) Remove from service HPTR front air seals, P/Ns 1523M34P02 and 1523M34P03, before accumulating 4,000 CSN, and replace with a serviceable part. (c) LCF retirement lives for HPTR disks P/N 1498M43P04 are now the same as originally calculated and are in accordance with the current airworthiness limitations section of Chapter 05 of the CFM56-5C Engine Shop Manual, CFMI-TP.SM.8. (d) Remove from service booster spools, P/N 337-005-210-0, before accumulating 13,000 CSN, and replace with a serviceable part. (e) For CFM56-5C4 engines, LCF retirement lives for low pressure turbine rotor (LPTR) stage 3 disks, P/Ns 337-001-602-0 and 337-001- 605-0 are now the same as originally calculated and are in accordance with the current airworthiness limitations section of Chapter 05 of the CFM56-5C Engine Shop Manual, CFMI-TP.SM.8. (f) For CFM56-5C2/G and -5C3/G engines, LCF retirement lives for LPTR stage 3 disks, P/Ns 337-001-602-0 and 337-001-605-0 are now the same as originally calculated and are in accordance with the current airworthiness limitations section of Chapter 05 of the CFM56-5C Engine Shop Manual, CFMI-TP.SM.8. (g) This action establishes the new LCF retirement lives stated in paragraphs (a) through (f) of this AD, which are published in Chapter 05 of the CFM56-5C Engine Shop Manual, CFMI-TP.SM.8. (h) For the purpose of this AD, a serviceable part is one that has not exceeded its respective new life limit as set out in this AD. Alternative Methods of Compliance (i) 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 (ECO). Operators must submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, ECO. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the ECO. Special Flight Permits (j) Special flight permits may be issued in accordance with 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 done. Effective Date (k) This amendment becomes effective on April 29, 2003.