[Federal Register: October 27, 2008 (Volume 73, Number 208)]
[Rules and Regulations]
[Page 63629-63630]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27oc08-6]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0808; Directorate Identifier 2008-NE-18-AD;
Amendment 39-15712; AD 2008-22-16]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CT58
Series Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain GE CT58 series turboshaft engines. This AD requires
recalculating the lives of certain part numbered compressor spools
using a new repetitive heavy lift (RHL) multiplying factor. This AD
results from reports of cracks originating from the inner faces of the
locking screw holes in the compressor spool. We are issuing this AD to
prevent cracks due to RHL missions. Cracks could result in an
uncontained rotor burst and damage to, or loss of, the helicopter and
serious injuries to any person onboard.
DATES: This AD becomes effective December 1, 2008.
ADDRESSES: You can get the service information identified in this AD
from GE Aircraft Engines Customer Support Center, M/D 285, 1 Neumann
Way, Evendale, OH 45215; telephone (513) 552-3272; fax (513) 552-3329;
e-mail GEAE.csc@ae.ge.com.
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: Christopher J. Richards, Aerospace
Engineer, Engine Certification Office, FAA, Engine & Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803; e-
mail: christopher.j.richards@faa.gov; telephone (781) 238-7133; fax
(781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to certain GE CT58 series
turboshaft engines. We published the proposed AD in the Federal
Register on July 23, 2008 (73 FR 42724). That action proposed to
require recalculating the cycles on certain compressor spools using new
RHL mission multipliers within 30 days after the effective date of the
proposed AD.
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 received no comments on the proposal or on
the determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.
Costs of Compliance
We estimate that this proposed AD will affect 89 engines installed
on helicopters of U.S. registry. We also estimate that it will take
about 0.5 work-hour per engine to perform the proposed actions, and
that the average labor rate is $80 per work-hour. Prorated life lost
for the compressor spools will cost about $16,972 per engine. Based on
these figures, we estimate the total cost of this AD to U.S. operators
to be $1,514,068.
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:
2008-22-16 General Electric Company (GE): Amendment 39-15712. Docket
No. FAA-2008-0808; Directorate Identifier 2008-NE-18-AD.
[[Page 63630]]
Effective Date
(a) This airworthiness directive (AD) becomes effective December
1, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to GE CT58 series turboshaft engines with a
compressor spool, part number (P/N) 5920T82G07, 6010T57G07, or
6010T57G08, installed. These engines are installed on, but not
limited to, Sikorsky S-61A, S-61L, S-61N, S-61R, S-62, and Columbia
107-II helicopters.
Unsafe Condition
(d) This AD results from reports of cracks originating from the
inner faces of the locking screw holes in the compressor spool. We
are issuing this AD to prevent cracks due to repetitive heavy lift
(RHL) missions. Cracks could result in an uncontained rotor burst
and damage to, or loss of, the helicopter and serious injuries to
any person onboard.
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.
Recalculating Compressor Spool Cycles
(f) Within 30 days after the effective date of this AD,
recalculate the life of compressor spools, P/N 5920T82G07,
6010T57G07, or 6010T57G08, using an RHL mission multiplying factor
of both 3.7 cycles per hour and 6.0 cycles per hour. GE Alert
Service Bulletin CT58 S/B 72-A0162, Revision 12, dated April 17,
2008, contains information on calculating life cycles for the
compressor spools.
Removing Compressor Spools Based on the New Recalculated Cycles
(g) Before January 1, 2010, remove the compressor spools, P/N
5920T82G07, 6010T57G07, or 6010T57G08, at the earlier of when:
(1) The compressor spool reaches its part life limit as
calculated using an RHL multiplying factor of 3.7, or
(2) You can see the spool at shop visit after it has reached its
part life limit using an RHL multiplying factor of 6.0.
(h) On January 1, 2010 and thereafter, remove the engine before
the compressor spool exceeds its part life limit as calculated using
an RHL multiplying factor of 6.0.
(i) As of January 1, 2010, don't use an RHL multiplying factor
of 3.7 to calculate the life of the compressor spool.
Installation Prohibition
(j) After the effective date of this AD, don't install any
engine that has a compressor spool installed that meets or exceeds
the life limits as calculated in paragraph (g)(1) through (g)(2) or
(h) of this AD.
Alternative Methods of Compliance
(k) 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.
Related Information
(l) GE Alert Service Bulletin CT58 S/B 72-A0162, Revision 12,
dated April 17, 2008, pertains to the subject of this AD.
(m) Contact Christopher J. Richards, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
christopher.j.richards@faa.gov; telephone (781) 238-7133; fax (781)
238-7199, for more information about this AD.
Material Incorporated by Reference
(n) None.
Issued in Burlington, Massachusetts, on October 20, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-25442 Filed 10-24-08; 8:45 am]
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