Airworthiness Directives; General Electric Company Turbofan Engines

[Federal Register Volume 82, Number 109 (Thursday, June 8, 2017)]
[Rules and Regulations]
[Pages 26579-26580]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-11780]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9490; Directorate Identifier 2016-NE-26-AD; 
Amendment 39-18914; AD 2017-11-15]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for General 
Electric Company (GE) CF6-80C2L1F turbofan engines. This AD was 
prompted by a reduction in the life limit of the affected engines which 
is the result of a revised operating profile. This AD requires 
replacement of the high-pressure turbine (HPT) spacer/impeller, part 
number (P/N) 1539M12P02, at a newer, lower life limit. We are issuing 
this AD to correct the unsafe condition on these products.

DATES: This AD is effective July 13, 2017.

ADDRESSES: See the For Further Information Contact section.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9490; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Document Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION 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: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain GE CF6-80C2L1F 
turbofan engines. The NPRM published in the Federal Register on January 
23, 2017 (82 FR 7734) (``the NPRM''). The NPRM was prompted by a 
reduction in the life limit of the affected engines which is the result 
of a revised operating profile. The NPRM proposed to require 
replacement of the HPT spacer/impeller, P/N 1539M12P02, at a newer, 
lower life limit. 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To Revise Compliance

    GE Aviation requested that we indicate in the compliance section of 
this AD that the affected HPT spacer/impeller is installed on GE CF6-
80C2L1F engines only. GE Aviation commented that this P/N impeller is 
also installed on other models of the CF6-80C2 engine.
    We disagree. We believe that the applicability section is clear 
that this AD applies to GE CF6-80C2L1F turbofan engines with a HPT 
spacer/impeller, P/N 1539M12P02, installed. We did not change this AD.

Miscellaneous Comment

    An individual commenter indicated that the proposal showed the 
FAA's commitment to ``staying on top of changes in the industry.'' The 
commenter noted, however, that although GE has updated the life 
expectancy of this part, it may still be a long time before it needs to 
be replaced. The commenter indicated, therefore, that the FAA's action 
may be ``over zealous'' and lead to ``large scale waste.''
    We disagree. We are issuing this AD to prevent failure of an engine 
rotating part, which could lead to failure of the part, uncontained 
release of the part, damage to the engine, and damage to the airplane. 
We did not change this AD.

Support for the NPRM

    An individual commenter supported the NPRM.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD as proposed.

Costs of Compliance

    We estimate that this AD affects 0 engines installed on airplanes 
of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
              Action                      Labor cost             Parts cost           product        operators
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Replacement of HPT spacer/impeller  0 work-hours x $85     $19,320 (pro-rated            $19,320              $0
 at reduced life.                    per hour = $0.         cost of part).
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    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.

[[Page 26580]]

    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.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):
2017-11-15 General Electric Company: Amendment 39-18914; Docket No. 
FAA-2016-9490; Directorate Identifier 2016-NE-26-AD.

(a) Effective Date

    This AD is effective July 13, 2017.

(b) Affected ADs

    None.

(c) Applicability

    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.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine/
Turboprop Engine--Turbine Section.

(e) Unsafe Condition

    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.

(f) Compliance

    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.

(g) Installation Prohibition

    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.

(h) Alternative Methods of Compliance (AMOCs)

    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: [email protected].

(i) Related Information

    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: [email protected].

(j) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on May 23, 2017.
Carlos A. Pestana,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-11780 Filed 6-7-17; 8:45 am]
BILLING CODE 4910-13-P

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