98-12-32 CFM International: Amendment 39-10585. Docket 97-ANE-46-AD.

Applicability: CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, and -3C series turbofan engines installed on, but not limited to McDonnell Douglas DC-8 series, Boeing 737 series, as well as Boeing E-3, E-6, and KC-135 (military) 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 (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.

Compliance: Required as indicated, unless accomplished previously.

To prevent the potential for an uncontained failure of the high pressure turbine rotor (HPTR) disk, which could result in an inflight engine shutdown, aborted takeoff, or damage to the aircraft, accomplish the following:

(a)Eddy current inspect for cracks or gouges in HPTR disks, Part Numbers 1475M29P01, 1475M29P02, 9514M69P01, 9514M69P04, 9514M69P05, 9514M69P06, and 9514M69P09, with Serial Numbers listed in Table 1 of the applicable Service Bulletin (SB), as follows:

1. For CFM56-2 engines, in accordance with CFM56-2 SB No. 72-817, Revision 1, dated November 25, 1997, within 45 days after the effective date of this AD.
2. For CFM56-2A engines, in accordance with CFM56-2A SB No. 72-419, Revision 2, dated November 14, 1997, within 500 cycles in service (CIS) after the effective date of this AD, or by December 31, 1999, whichever occurs first.
3. For CFM56-2B engines, in accordance with CFM56-2B SB No. 72-561, Revision 1, dated January 31, 1997, within 500 CIS after the effective date of this AD, or by December 31, 1999, whichever occurs first.
4. For CFM56-3, -3B, and -3C engines, in accordance with CFM56-3/-3B/-3C SB No. 72-843, Revision 1, dated November 25, 1997, within 45 days after the effective date of this AD.

2. Remove from service HPTR disks found cracked or gouged, and replace with serviceable parts.
3. 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 request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office.

(d) 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 inspection requirements of this AD can be accomplished.

(e) The actions required by this AD shall be done in accordance with the following CFMI SBs:

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, 1 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 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.

(f) This amendment becomes effective on July 20, 1998.

FOR FURTHER INFORMATION CONTACT:

Glorianne Messemer, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-7132; fax (781) 238-7199.