AD 2000-12-01 Airworthiness Directives; Airworthiness Directives; CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5B, -5C, and -7B Series Turbofan Engines

CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5B, -5C, and -7B series turbofan engines, installed on but not limited to McDonnell Douglas DC-8 series, Boeing 737 series, Airbus Industrie A319, A320, A321, and A340 series, as well as Boeing C-135, E-3, E-6, KC-135, KE-3, and RC-135 (military) series airplanes. 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.

Required as indicated, unless accomplished previously. To prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane, accomplish the following: Inspections (a) Within the next 30 days after the effective date of this AD, revise the Airworthiness Limitations Section (chapter 05-00-00) of Engine Shop Manual (ESM) CFMI-TP.SM.4 for CFM56-2 series engines, ESM CFMI-TP.SM.6 for CFM56-2A/-2B series engines, ESM CFMI-TP.SM.5 for CFM56-3/-3B/-3C series engines, ESM CFMI-TP.SM.7 for CFM56-5 series engines, ESM CFMI-TP.SM.9 for CFM56-5B series engines, ESM CFMI-TP.SM.8 for CFM56-5C series engines, and ESM CFMI-TP.SM.10 for CFM56-7B series engines, and for air carrier operations, revise the approved continuous airworthiness maintenance program, by adding the following: “MANDATORY INSPECTIONS (1) Perform inspections of the following parts at each piece-part opportunity in accordance with the Inspection/Check section instructions provided in the applicable manual sections listed below:   Engine models Part name Engine manual section Inspection All Fan Disk (All Part Number (P/N)) 72-21-03 Disk Fluorescent Penetrant Inspection (FPI) and Disk Bore and Dovetail Eddy Current Inspection (ECI). CFM56-2/-2A/-2B/-3/-3B/-3C High Pressure Turbine (HPT) Disk (All P/N) 72-52-02 Disk FPI and Disk Bore and Rim Bolt Hole(s) ECI. CFM56-5/-5B/-5C/-7B HPT Disk (All P/N) 72-52-02 Disk FPI and Disk Bore ECI. CFM56-2A/-2B/-3/-3B/-3C HPT Front Rotating Air Seal (All P/N) 72-52-03 Seal FPI and Seal Bore and Bolt Hole(s) ECI. CFM56-5/-5B/-5C/-7B HPT Front Rotating Air Seal (All P/N) 72-52-03 Seal FPI and Seal Bore ECI and Seal Bolt Hole(s) Focused FPI. CFM56-2 HPT Front Rotating Air Seal (All P/N) 72-52-03 Seal FPI and Seal Bore ECI and Seal Bolt Hole(s) ECI or focused FPI as applicable. (2) For the purposes of these mandatory inspections, piece-part opportunity means: (i) The part is considered completely disassembled when accomplished in accordance with the disassembly instructions in the manufacturer's engine manual; and (ii) The part has accumulated more than 100 cycles in service since the last piece-part opportunity inspection, provided that the part was not damaged or related to the cause for its removal from the engine.” (b) Except as provided in paragraph (c) of this AD, and notwithstanding contrary provisions in § 43.16 of the Federal Aviation Regulations (14 CFR 43.16), these mandatory inspections shall be performed only in accordance with the Airworthiness Limitations Section of the manufacturer's ESM. Alternative Methods of Compliance (c) 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 Engine Certification Office (ECO). Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector (PMI), who may add comments and then send it to the 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. Ferry Flights (d) 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 accomplished. Continuous Airworthiness Maintenance Program (e) FAA-certificated air carriers that have an approved continuous airworthiness maintenance program in accordance with the record keeping requirement of § 121.369(c) of the Federal Aviation Regulations (14 CFR 121.369(c)) must maintain records of the mandatory inspections that result from revising the Airworthiness Limitations Section of the applicable ESM and the air carrier's continuous airworthiness program. Alternately, certificated air carriers may establish an approved system of record retention that provides a method for preservation and retrieval of the maintenance records that include the inspections resulting from this AD, and include the policy and procedures for implementing this alternate method in the air carrier's maintenance manual required by § 121.369(c) of the Federal Aviation Regulations (14 CFR 121.369(c)); however, the alternate system must be accepted by the appropriate PMI and require the maintenance records be maintained either indefinitely or until the work is repeated. Records of the piece-part inspections are not required under § 121.380(a)(2)(vi) of the Federal Aviation Regulations (14 CFR 121.380(a)(2)(vi)). All other operators must maintain the records of mandatory inspections required by the applicable regulations governing their operations. Note 3: The requirements of this AD have been met when the ESM changes are made and air carriers have modified their continuous airworthiness maintenance plans to reflect the requirements in the applicable ESM. Effective Date (f) This amendment becomes effective on December 11, 2000. Issued in Burlington, Massachusetts, on June 5, 2000. Diane S. Romanosky, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 00-14788 Filed 6-12-00; 8:45 am] BILLING CODE 4910-13-U