Federal Aviation Administration (FAA), DOT.
Notice of proposed rulemaking (NPRM).
We propose to adopt a new airworthiness directive (AD) for certain General Electric Company (GE) CF6–80C2L1F turbofan engines. This proposed AD was prompted by a reduction in the life limit of the affected engines which is the result of a revised operating profile. This proposed AD would require replacement of the high-pressure turbine (HPT) spacer/impeller, part number (P/N) 1539M12P02, at a newer, lower life limit. We are proposing this AD to correct the unsafe condition on these products.
We must receive comments on this proposed AD by March 9, 2017.
You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:
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You may examine the AD docket on the Internet at
Herman Mak, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7147; fax: 781–238–7199; email:
We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the
We will post all comments we receive, without change, to
The United States Air Force revised its operating profile for its GE CF6–80C2L1F engines. As a result of this change in operating profile, GE reduced its life limit for the HPT spacer/impeller from 20,000 to 18,000 cycles. Therefore, we are proposing to require removal of this affected HPT spacer/impeller at the new, lower life limit. This condition, if not corrected, could result in failure of the HPT spacer/impeller, uncontained release of the HPT spacer/impeller, damage to the engine, and damage to the airplane.
We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design.
This proposed AD would require replacement of the HPT spacer/impeller, P/N 1539M12P02, at a newer, lower life limit.
We estimate that this proposed AD affects 0 engines installed on airplanes of U.S. registry.
We estimate the following costs to comply with this proposed AD:
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: “General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify this proposed regulation:
(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),
(3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, and
(4) 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.
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
49 U.S.C. 106(g), 40113, 44701.
We must receive comments by March 9, 2017.
None.
This AD applies to General Electric Company (GE) CF6–80C2L1F turbofan engines with a high-pressure turbine (HPT) spacer/impeller, part number (P/N) 1539M12P02, installed.
Joint Aircraft System Component (JASC) Code 7250, Turbine/Turboprop Engine—Turbine Section.
This AD was prompted by a reduction in the life limit of the affected engines, which is the result of a revised operating profile. We are issuing this AD to prevent failure of the HPT spacer/impeller, uncontained release of the HPT spacer/impeller, damage to the engine, and damage to the airplane.
Comply with this AD within the compliance times specified, unless already done.
After the effective date of this AD, replace the HPT spacer/impeller, P/N 1539M12P02, before it exceeds 18,000 flight cycles since new.
After the effective date of this AD, do not install an HPT spacer/impeller, P/N 1539M12P02, onto any engine, or return to service any engine with an HPT spacer/impeller, P/N 1539M12P02, installed, if the HPT spacer/impeller exceeds 18,000 flight cycles since new.
The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to:
For more information about this AD, contact Herman Mak, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7147; fax: 781–238–7199; email: