[Federal Register: November 26, 2003 (Volume 68, Number 228)]
[Proposed Rules]
[Page 66386-66387]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26no03-18]

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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withdrawn.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]

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