[Federal Register: April 1, 2009 (Volume 74, Number 61)]
[Rules and Regulations]
[Page 14719-14720]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01ap09-3]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1206; Directorate Identifier 2008-NE-19-AD;
Amendment 39-15869; AD 2009-07-10]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF6-80A Series
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
General Electric Company (GE) CF6-80A series turbofan engines with a
high-pressure turbine rotor (HPTR) stage 1 disk, part number (P/N)
9367M45G06, installed. This AD requires removing any HPTR stage 1 disk,
P/N 9367M45G06, before exceeding 2,075 cycles-since-new (CSN). This AD
results from an error by GE that incorrectly cited a cyclic life of
12,600 CSN for the HPTR stage 1 disk, P/N 9367M45G06. We are issuing
this AD to prevent the HPTR stage 1 disk from exceeding its part life,
which could cause fatigue cracks to start and grow. These cracks could
result in a possible uncontained disk failure and damage to the
airplane.
DATES: This AD becomes effective May 6, 2009.
ADDRESSES: The Docket Operations office is located at the 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 Park, 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 CF6-80A series
turbofan engines with a HPTR stage 1 disk, P/N 9367M45G06, installed.
We published the proposed AD in the Federal Register on November 14,
2008 (73 FR 67433). That action proposed to require removing any HPTR
stage 1 disk, P/N 9367M45G06, before exceeding 2,075 CSN.
[[Page 14720]]
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 10 engines installed on
airplanes of U.S. registry. We also estimate that it will take about
110 work-hours per engine to perform the actions, and that the average
labor rate is $80 per work-hour. Required parts will cost about
$437,000 per engine. Based on these figures, we estimate the total cost
of the AD to U.S. operators to be $4,458,000.
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:
2009-07-10 General Electric Company: Amendment 39-15869. Docket No.
FAA-2008-1206; Directorate Identifier 2008-NE-19-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 6,
2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric Co. (GE) CF6-80A, CF6-
80A1, CF6-80A2, and CF6-80A3 turbofan engines with a high-pressure
turbine rotor (HPTR) stage 1 disk, part number (P/N) 9367M45G06,
installed. These engines are installed on, but not limited to,
Airbus A310 series and Boeing 767 series airplanes.
Unsafe Condition
(d) This AD results from an error by GE that incorrectly cited a
cyclic life of 12,600 CSN in the Airworthiness Limitations Section
(ALS) of the Instructions for Continued Airworthiness (ICA) for the
HPTR stage 1 disk, P/N 9367M45G06. We are issuing this AD to prevent
the HPTR stage 1 disk from exceeding its part life, which could
cause fatigue cracks to start and grow. These cracks could result in
a possible uncontained disk failure 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 HPTR Stage 1 Disks, P/N 9367M45G06
(f) After the effective date of this AD, remove HPTR stage 1
disks, P/N 9367M45G06, from service before exceeding the new,
reduced life limit of 2,075 cycles-since-new.
Alternative Methods of Compliance
(g) 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
(h) Under 14 CFR part 39.23, we are prohibiting any special
flight permits.
Related Information
(i) Contact Robert Green, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238-7199,
for more information about this AD.
Material Incorporated by Reference
(j) None.
Issued in Burlington, Massachusetts, on March 25, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E9-7280 Filed 3-31-09; 8:45 am]
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