[Federal Register Volume 68, Number 228 (Wednesday, November 26, 2003)]
[Proposed Rules]
[Pages 66386-66387]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-29571]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 86-ANE-12-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric CF6-80C2 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Proposed rule; withdrawal.

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SUMMARY: This action withdraws a notice of proposed rulemaking (NPRM) 
that proposed a new airworthiness directive (AD), applicable to General 
Electric (GE) CF6-80C2 series turbofan engines. That action would have 
required imposing a life limit on certain forward engine mount thrust 
links. Since that NPRM was issued, the FAA has determined that the 
affected parts are no longer eligible for installation, and therefore, 
the unsafe condition is not likely to exist or develop on other 
products of the same type design. Accordingly, the proposed rule is 
withdrawn.

FOR FURTHER INFORMATION CONTACT: Karen Curtis, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; telephone (781) 238-
7192; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to add a new airworthiness 
directive (AD), applicable to GE CF6-80C2 series turbofan engines, was 
published in the Federal Register on July 11, 1986 (51 FR 25208). The 
proposed rule would have required imposing a life limit on certain 
forward engine mount thrust links. The forward engine mount frame 
thrust links, part numbers (P/Ns) 9383M45G01 and 9383M45G02, and the 
forward engine mount platform thrust links, P/Ns 9383M45G03 and 
9383M45G04, would have been life-limited to 5,000 cycles-since-new 
(CSN). That action was prompted by the results of low-cycle-fatigue 
test results that determined certain forward engine mount frame and 
platform thrust links had a finite low-cycle-fatigue life limit. GE 
Service Bulletin (SB) 72-022, dated April 26, 1988, introduced a 
redesigned forward engine thrust mount system. The proposed actions 
were intended to prevent fracture of forward mount thrust links, which 
could result in the mount's inability to carry design loads.

[[Page 66387]]

    Since that NPRM was issued, the FAA has determined that all 
affected engines are in compliance with the proposed AD by having 
complied with GE SB 72-022, dated April 26, 1989. The SB was issued as 
a Category 3, Campaign Change, and GE recommended that this SB be done 
at the next shop visit. In addition, the FAA has determined that the 
affected parts are no longer eligible for installation, and therefore, 
the unsafe condition is not likely to exist or develop on other 
products of the same type design. Accordingly, the proposed rule is 
withdrawn.
    Withdrawal of this notice of proposed rulemaking applies only to 
the NRPM, and does not prevent us from issuing another notice in the 
future, nor does it commit us to any course of action in the future.
    This action is not covered under Executive Order 12866, the 
Regulatory Flexibility Act, or DOT Regulatory Policies and Procedures 
(44 FR 11034, February 26, 1979) because it only withdraws a notice of 
proposed rulemaking, and it is neither a proposed nor a final rule.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Withdrawal

    The notice of proposed rulemaking, Docket No. 86-ANE-12-AD, 
published in the Federal Register on July 11, 1986 (51 FR 25208), is 
withdrawn.

    Issued in Burlington, Massachusetts, on November 20, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-29571 Filed 11-25-03; 8:45 am]
BILLING CODE 4910-13-P