[Federal Register: July 1, 2009 (Volume 74, Number 125)]
[Rules and Regulations]
[Page 31350-31351]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01jy09-3]
[[Page 31350]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0121; Directorate Identifier 2008-NE-36-AD;
Amendment 39-15958; AD 2009-14-08]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF6-
80C2B5F Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE
CF6-80C2B5F turbofan engines. This AD requires removing certain part
number (P/N) high-pressure compressor rotor (HPCR) stages 11-14 spool/
shafts before they exceed a new, reduced life limit. This AD results
from an internal GE audit that compared the life limited parts
certification documentation to the airworthiness limitations section
(ALS) of the instructions for continuing airworthiness (ICA). We are
issuing this AD to prevent HPCR stages 11-14 spool/shaft fatigue cracks
caused by exceeding the life limit, which could result in a possible
uncontained failure of the HPCR spool/shaft and damage to the airplane.
DATES: This AD becomes effective August 5, 2009.
ADDRESSES: The Docket Operations office is located at Docket Management
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue,
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.
FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Part, Burlington, MA 01803; e-mail:
robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to GE CF6-80C2B5F turbofan
engines. We published the proposed AD in the Federal Register on
February 20, 2009 (74 FR 7831). That action proposed to require
removing certain P/N HPCR stages 11-14 spool/shafts before they exceed
a new, reduced life limit.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office
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 street address for
the Docket Operations office (telephone (800) 647-5527) is provided in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment received. The
commenter supports the proposal.
Conclusion
We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD as proposed.
Costs of Compliance
We estimate that this AD will affect one engine installed on an
airplane of U.S. registry. We also estimate that the actions would
require no work-hours per engine. No parts are required. Based on these
figures, we estimate there is no cost of this AD to U.S. operators.
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.
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
We have determined that 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); and
(3) 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.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration 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:
2009-14-08 General Electric Company: Amendment 39-15958. Docket No.
FAA-2009-0121; Directorate Identifier 2008-NE-36-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective August
5, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric Company (GE) CF6-80C2B5F
turbofan engines with a high-pressure compressor rotor (HPCR) stages
11-14 spool/shaft, part number (P/N) 1703M74G03, installed. These
engines are installed on, but not limited to, Boeing 747 series
airplanes.
Unsafe Condition
(d) This AD results from an internal GE audit that compared the
life limited parts certification documentation to the airworthiness
limitations section (ALS) of the instructions for continuing
airworthiness (ICA). We are issuing this AD to prevent HPCR stages
11-14 spool/shaft fatigue cracks caused by exceeding the life limit,
which could result in a possible uncontained failure
[[Page 31351]]
of the HPCR spool/shaft and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
New Reduced Life Limit for the HPCR Stages 11-14 Spool/Shaft
(f) Remove any CF6-80C2B5F turbofan engine that has an HPCR
stages 11-14 spool/shaft, P/N 1703M74G03, before the spool/shaft
meets or exceeds the new, reduced life cycle limit of 19,500 cycles.
Installation Prohibition
(g) After the effective date of this AD, do not install any CF6-
80C2B5F turbofan engine that has an HPCR stages 11-14 spool/shaft,
P/N 1703M74G03, that meets or exceeds 19,500 cycles.
Alternative Methods of Compliance
(h) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Special Flight Permits
(i) Under 14 CFR part 39.23, we are prohibiting special flight
permits for this AD.
Related Information
(j) Robert Green, Aerospace Engineer, Engine Certification
Office, FAA, Engine & Propeller Directorate, 12 New England
Executive Part, Burlington, MA 01803; e-mail: robert.green@faa.gov;
telephone (781) 238-7754; fax (781) 238-7199.
Material Incorporated by Reference
(k) None.
Issued in Burlington, Massachusetts, on June 25, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E9-15513 Filed 6-30-09; 8:45 am]
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