2002-23-02: Airworthiness Limitations Section (ALS) - Critical Life-Limited Parts

2002-23-02 General Electric Company: Amendment 39-12946. Docket No. 2002-NE-13-AD. Applicability: This airworthiness directive (AD) is applicable to General Electric Company CF34-8C1 turbofan engines. These engines are installed on, but not limited to, Bombardier Aerospace CRJ700 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 (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: Compliance with this AD is required as indicated, unless already done. To prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane, do the following: (a) Within the next 30 days after the effective date of this AD, revise the Time Limits Section (TLS) of the manufacturer's Engine Manual (EM), GEK 105091 and for air carrier operations revise the approved continuous airworthiness maintenance program, by adding the following: "MANDATORY INSPECTIONS (1) Perform inspections of the parts listed in the following Table 801 at each piece-part opportunity in accordance with the instructions provided in the applicable manual provisions: Table 801.--Mandatory Inspection Requirements Part nomenclature Manual/Chapter Section /Subject Mandatory Inspection Fan Disk 72-21-15, INSPECTION All areas (FPI).1 Bores (ECI).2 Fan Drive Shaft 72-22-00, INSPECTION All areas (FPI).1 Stage 1 High Pressure Turbine (HPT) Rotor Disk 72-51-06, INSPECTION All areas (FPI).1 Bores (ECI).2 Boltholes (ECI).2 Air Holes (ECI).2 HPT Rotor Outer Torque Coupling 72-51-10, INSPECTION All non-coated areas (FPI).1 Bores (ECI).2 Stage 2 HPT Rotor Disk 72-51-14, INSPECTION All areas (FPI).1 Bores (ECI).2 HPT Shaft 72-51-03, INSPECTION All non-coated areas (FPI).1 Stage 1 and Stage 2 High Pressure Compressor (HPC) Rotor Blisks. 72-33-01, INSPECTION All areas (FPI).1 HPC Forward Shaft 72-33-02, INSPECTION All areas (FPI).1 Stage 3 HPC Rotor Blisk 72-33-03, INSPECTION All areas (FPI).1 HPC Aft Shaft Spool 72-33-05, INSPECTION All non-coated areas (FPI).1 HPC Discharge Rotating Seal 72-33-08, INSPECTION All non-coated areas (FPI).1 Stage 3 Low Pressure Turbine (LPT) Rotor Disk 72-57-10, INSPECTION All areas (FPI).1 Stage 4 LPT Rotor Disk 72-57-16, INSPECTION All areas (FPI).1 Rear LPT Shaft 72-57-23,INSPECTION All areas (FPI).1 Stage 5 LPT Rotor Disk 72-57-20, INSPECTION All areas (FPI).1 Stage 6 LPT Rotor Disk 72-57-28, INSPECTION All areas (FPI).1 1 FPI = Fluorescent Penetrant Inspection Method 2 ECI = Eddy Current Inspection Method (2) For the purposes of these mandatory inspections, piece-part opportunity means: (i) The part is considered at "piece-part opportunity", when it is completely disassembled 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 section 43.16 of the Federal Aviation Regulations (14 CFR 43.16), these mandatory inspections shall be performed only in accordance with the TLS of the GECF34-8C1 EM. 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 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 (d) Special flight permits may be issued in accordance with Sec. Sec. 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. Continuous Airworthiness Maintenance Program (e) FAA-certificated air carriers that have an approved continuous airworthiness maintenance programin accordance with the record keeping requirement of Sec. 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 CF34 Engine Maintenance Program and the air carrier's continuous airworthiness program. Alternatively, 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 Sec. 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 Sec. 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 engine manual changes are made and air carriers have modified their continuous airworthiness maintenance plans to reflect the Engine Maintenance Program requirements specified in the GE CF34-8C1 Engine Manual. Effective Date (f) This amendment becomes effective on December 26, 2002.