96-18-16 CFM International: Amendment 39-9742. Docket 95-ANE-15.
Applicability: CFM International (CFMI) CFM56-2/-2A/-2B/-3/-3B/-3C/-5 series turbofan engines installed on, but not limited to Airbus A319 and A320 series, McDonnell Douglas DC-8 series, and Boeing 737, as well as Boeing E-3, E-6, and KC-135 (military) series aircraft.
Note: 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 (k) 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 low cycle fatigue (LCF) failure of the low pressure turbine rotor (LPTR) stub shaft and conical support, which could result in an uncontained engine failure and damage to the aircraft, accomplish the following:
(a) Reidentify CFM56-2A LPTR stub shafts, Part Numbers (P/N) 301-330-623-0 and 301-330-624-0, with Serial Numbers (S/N) listed in Table 2 of CFMI CFM56-2A Service Bulletin (SB) No. 72-338, dated November 25, 1993, in accordance with the Accomplishment Instructions of CFMI CFM56-2A SB No. 72-338, dated November 25, 1993, at the next piece-part exposure after the effective date of this AD, but not to exceed 6,400 cycles since new (CSN).
(b) Reidentify CFM56-2B LPTR stub shafts, P/N 301-330-618-0, 301-330-619-0, 301-330- 623-0, and 301-330-624-0, with S/N listed in Table 2 of CFMI CFM56-2B SBNo. 72-476, dated December 7, 1993, in accordance with the Accomplishment Instructions of CFMI CFM56-2B SB No. 72-476, dated December 7, 1993, at the next piece-part exposure after the effective date of this AD, but not to exceed 8,300 CSN.
(c) Reidentify CFM56-2 LPTR conical supports, P/N 305-056-106-0, 305-056-109-0, 305- 056-110-0, and 305-056-111-0, with S/N listed in Table 1 of CFMI CFM56-2 SB No. 72-728, Revision 2, dated December 21, 1994, in accordance with the Accomplishment Instructions of CFMI CFM56-2 SB No. 72-728, Revision 2, dated December 21, 1994, at the next piece-part exposure after the effective date of this AD, but not to exceed 18,000 CSN.
(d) Reidentify CFM56-2A LPTR conical supports, P/N 305-056-110-0 and 305-056-111-0, with S/N listed in Table 1 of CFMI CFM56-2A SB No. 72-338, dated November 25, 1993, in accordance with the Accomplishment Instructions of CFMI CFM56-2A SB No. 72-338, dated November 25, 1993, at the next piece-part exposure after the effective date of this AD, but not to exceed 5,700 CSN.
(e) Reidentify CFM56-2B LPTR conical supports, P/N 305-056-106-0, 305-056-109-0, 305- 056-110-0, and 305-056-111-0, with S/N listed in Table 1 of CFMI CFM56-2B SB No. 72-476, dated December 7, 1993, in accordance with the Accomplishment Instructions of CFMI CFM56-2B SB No. 72-476, dated December 7, 1993, at the next piece-part exposure after the effective date of this AD, but not to exceed 8,700 CSN.
(f) Reidentify CFM56-3/-3B/-3C LPTR stub shafts, P/N 301-330-618-0, 301-330-619-0, 301-330-623-0, and 301-330-624-0, with S/N listed in Table 2 of CFMI CFM56-3/-3B/-3C SB No. 72-695, dated November 25, 1993, in accordance with the Accomplishment Instructions of CFMI CFM56-3/-3B/-3C SB No. 72-695, dated November 25, 1993, as follows:
(1) For CFM56-3/-3B/-3C series engines operating at the Category A thrust rating, at the next piece-part exposure after the effective date of this AD, but not to exceed a total Category A thrust ratinglife of 20,000 CSN.
(2) For CFM56-3B/-3C series engines operating at the Category B thrust rating, at the next piece-part exposure after the effective date of this AD, but not to exceed a total Category B thrust rating life of 11,400 CSN.
(3) For CFM56-3C series engines operating at the Category C thrust rating, at the next piece-part exposure after the effective date of this AD, but not to exceed a total Category C thrust rating life of 7,900 CSN.
(g) Reidentify CFM56-3/-3B/-3C LPTR conical supports, P/N 305-056-106-0, 305-056-109- 0, 305-056-110-0, and 305-056-111-0, with S/N listed in Table 1 of CFMI CFM56-3/-3B/-3C SB No. 72-695, dated November 25, 1993, in accordance with the Accomplishment Instructions of CFMI CFM56-3/-3B/-3C SB No. 72-695, dated November 25, 1993, as follows:
(1) For CFM56-3/-3B/-3C series engines operating at the Category A thrust rating, at the next piece-part exposure after the effective date of this AD, but not to exceed a total Category A thrust rating life of 12,100 CSN.
(2) For CFM56-3B/-3C series engines operating at the Category B thrust rating, at the next piece-part exposure after the effective date of this AD, but not to exceed a total Category B thrust rating life of 9,300 CSN.
(3) For CFM56-3C series engines operating at the Category C thrust rating, at the next piece-part exposure after the effective date of this AD, but not to exceed a total Category C thrust rating life of 5,700 CSN.
(h) Remove from service CFM56-5 LPTR conical support, P/N 336-000-305-0, prior to accumulating 11,300 CSN.
(i) This action establishes new LCF retirement lives for parts reidentified in accordance with paragraphs (a) through (g) of this AD, and the new LCF retirement life noted in paragraph (h) of this AD, which are published in Chapter 05 of the applicable engine shop manual (CFM56-2 CFMI-TP.SM.4, CFM56-2A/-2B CFMI-TP.SM.6, CFM56-3 CFMI-TP.SM.5, and CFM56-5 CFMI-TP.SM.7).
(j) The Category A, B, and C thrust ratingnoted in paragraphs (f) and (g) of this AD are defined in Chapter 05 of CFM56-3 engine shop manual, CFMI-TP.SM.5.
(k) 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. 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: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office.
(l) 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.
(m) The actions required by this AD shall be done in accordance with the following CFMI SB's:
Document No.
Pages
Revision
Date
CFM56-2 SB No. 72-728
1
2
December 21, 1994
2-7
Original
November 25, 1993
8
2
December 21, 1994
9
Original
November 25, 1993
Total Pages: 9.
CFM56-2A SB No. 72-338
1-8
Original
November 25, 1993
Total Pages: 8.
CFM56-2B SB No. 72-476
1-9
Original
December 7, 1993
Total Pages: 9.
CFM56-3/-3B/-3C
SB No. 72-695
1-9
Original
November 25, 1993
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.
(n) This amendment becomes effective on December 9, 1996.