Skip to Content

Rule

Airworthiness Directives; General Electric Company CF34-3A1 and -3B1 Series Turbofan Engines

Document Details

Information about this document as published in the Federal Register.

Published Document

This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

Start Preamble

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Final rule.

SUMMARY:

This amendment supersedes an existing airworthiness directive (AD), that is applicable to General Electric Company (GE) CF34-3A1 and -3B1 series turbofan engines, that currently requires revisions to the Engine Maintenance Program specified in the manufacturer's Instructions for Continued Airworthiness (ICA) for GE CF34-3A1 and -3B1 series turbofan engines. Those revisions require enhanced inspection of selected critical life-limited parts at each piece-part exposure. The existing AD also requires that an air carrier's approved continuous airworthiness maintenance program incorporate these inspection procedures. This amendment modifies the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. An FAA study of in-service events involving uncontained failures of critical rotating engine parts has indicated the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.

DATES:

Effective date April 12, 2002.

ADDRESSES:

The information referenced in this AD may be examined, by appointment, at the Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Barbara Caufield, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-7146; fax (781) 238-7199. Start Printed Page 10607

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 2000-03-03 R1, Amendment 39-12228 (66 FR 26787, May 15, 2001), which is applicable to General Electric Company CF34-3A1 and -3B1 series turbofan engines was published in the Federal Register on October 5, 2001 (66 FR 50891). That action proposed to modifiy the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements.

Comments

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA's determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

Regulatory Analysis

This final rule does not have federalism implications, as defined in Executive Order 13132, because it would not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Accordingly, the FAA has not consulted with state authorities prior to publication of this final rule.

For the reasons discussed above, I certify that this action (1) is not a “significant regulatory action” under Executive Order 12866; (2) is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES.

Start List of Subjects

List of Subjects in 14 CFR Part 39

End List of Subjects

Adoption of the Amendment

Start Amendment Part

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (

End Amendment Part Start Part

PART 39—AIRWORTHINESS DIRECTIVES

End Part Start Amendment Part

1. The authority citation for part 39 continues to read as follows:

End Amendment Part Start Authority

Authority: 49 U.S.C. 106(g), 40113, 44701.

End Authority
[Amended]
Start Amendment Part

2. Section 39.13 is amended by removing Amendment 39-12228 (

End Amendment Part

2002-05-02 General Electric Company: Amendment 39-12670. Docket No. 99-NE-49-AD. Supersedes AD 2000-03-03 R1, Amendment 39-12228.

Applicability

This airworthiness directive (AD) is applicable to General Electric Company (GE) CF34-3A1 and -3B1 series turbofan engines, installed on but not limited to Bombardier Canadair CL 600-2B19(RJ) aircraft.

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:

Inspections

(a) Within 30 days after the effective date of this AD, revise the CF34 Engine Maintenance Program, Chapter 5-21-00, of the GE CF34-3A1 and -3B1 Series Turbofan Engine Manual, SEI-756. For air carrier operations, revise the approved continuous airworthiness maintenance program, by adding the following:

“9. CF34-3A1 and CF34-3B1 Engine Maintenance Program—Mandatory Inspection Requirements.

(A) This procedure is used to identify specific piece-parts that require mandatory inspections that must be accomplished at each piece-part exposure using the applicable Chapters referenced in Table 804 for the inspection requirements. The inspection requirements listed in Table 804 are not required for any piece-part exposure resulting when the engine remains on-wing while performing maintenance practice, special procedure Number 41 listed in SEI-756, chapter 72-00-00.

(B) Piece-part exposure is defined as follows: Note: Fan disk piece-part includes the fan disk with the 56 fan pin bushings installed.

(1) For engines that utilize the “On Condition” maintenance requirements:

The part is considered completely disassembled to the piece-part level when done in accordance with the disassembly instructions in the GEAE authorized overhaul Engine Manual, and 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.

(2) For engines that utilize the “Hard Time” maintenance requirements:

The part is considered completely disassembled when done in accordance with the disassembly instructions used in the “Minor Maintenance” or “Overhaul” instructions in the GEAE engine authorized Engine Manual, and 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.

C. Refer to Table 804 below for the mandatory inspection requirements.

Table 804.—Mandatory Inspection Requirements

Part nomenclatureManual/chapter section/subjectMandatory inspection
Fan Disk (all)72-21-00, INSPECTIONAll areas (FPI) Bores (ECI)
Stage 1 high pressure turbine (HPT) Rotor Disk (all)72-46-00, INSPECTIONAll areas (FPI) Bores (ECI) Boltholes (ECI) Air Holes (ECI)
Start Printed Page 10608
Stage 2 HPT Rotor Disk (all)72-46-00, INSPECTIONAll areas (FPI) Bores (ECI)
(a) Boltless Rim ConfigurationBoltholes (FPI) Air Holes (FPI)
(b) Bolted Rim ConfigurationBoltholes (ECI) Air Holes (ECI)
HPT Rotor Outer Torque Coupling (all)72-46-00, INSPECTIONAll areas (FPI) Bore (ECI)
Forward Fan Shaft (all)72-21-00, INSPECTIONAll areas (FPI)
Fan Drive Shaft (all)72-22-00, INSPECTIONAll areas (FPI)
Stage 1 Compressor; Rotor Disk (CF34-3A1) or; Stage 1 Compressor Rotor; Blisk (CF34-3B1) (all)72-33-00, INSPECTIONAll areas (FPI)
Compressor Forward Shaft (all)72-33-00, INSPECTIONAll areas (FPI)
Stage 2 Compressor Rotor Disk (all)72-33-00, INSPECTIONAll areas (FPI)
Stage 3-8 Compressor Rotor Spool (all)72-33-00, INSPECTIONAll areas (FPI)
Stage 9 Compressor Rotor Disk (all)72-33-00, INSPECTIONAll areas (FPI)
Compressor Rotor Rear Shaft (all)72-33-00, INSPECTIONAll areas (FPI)
Compressor Discharge Rotating Seal (all)72-33-00, INSPECTIONAll non-coated Areas (FPI)
Stage 10-14 Compressor Areas Rotor Spool (all)72-33-00, INSPECTIONAll non-coated (FPI)
Turbine Rear Shaft (LPT Rotor) (all)72-53-00, INSPECTIONAll areas (FPI)
Stage 3 Turbine Disk (all)72-53-00, INSPECTIONAll areas (FPI)
Stage 4 Turbine Disk (all)72-53-00, INSPECTIONAll areas (FPI)
Stage 5 Turbine Disk (all)72-53-00, INSPECTIONAll areas (FPI)
Stage 6 Turbine Disk (all)72-53-00, INSPECTIONAll areas (FPI)
Turbine Driver Cone (all)72-53-00, INSPECTIONAll areas (FPI)
FPI = Fluorescent Penetrant Inspection Method
ECI = Eddy Current Inspection”

(b) Except as provided in paragraph (c) of this AD, and notwithstanding the provisions of section 43.16 of the Federal Aviation Regulations (14 CFR 43.16), these mandatory inspections shall be performed only in accordance with the CF34 Engine Maintenance Program, Chapter 5-21-00, of the General Electric Company, CF34-3A1 and -3B1 Series Turbofan Engine Manual, SEI-756.

Alternative Method 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 requests through an appropriate FAA Principal Maintenance Inspector (PMI), 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 AD, if any, may be obtained from the ECO.

Special Flight Permits

(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 done.

Continuous Airworthiness Maintenance Program

(e) FAA-certificated air carriers that have an approved continuous airworthiness maintenance program in accordance with the recordkeeping 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 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 § 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 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 CF34-3A1 and -3B1 Series Turbofan Engine Manual.

Effective Date

(f) This amendment becomes effective on April 12, 2002.

Start Signature

Issued in Burlington, Massachusetts, on February 27, 2002.

Mark C. Fulmer,

Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. 02-5527 Filed 3-7-02; 8:45 am]

BILLING CODE 4910-13-P