[Federal Register Volume 73, Number 246 (Monday, December 22, 2008)]
[Rules and Regulations]
[Pages 78175-78178]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-29722]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24261; Directorate Identifier 2006-NE-12-AD;
Amendment 39-15768; AD 2008-26-02]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CT7-8A
Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for certain GE CT7-8A turboshaft engines. That AD currently
requires initial and repetitive inspections of the electrical chip
detectors for the No. 3 bearing. This AD requires removing from service
certain GE CT7-8A turboshaft engines within 6,200 cycles-since-new.
This AD results from investigation for the root causes of two failures
of the No. 3 bearing. We are issuing this AD to prevent failure of the
No. 3 bearing due to contamination by aluminum oxide, which could
result in a possible in-flight shutdown of the engines and loss of
control or forced landing of the aircraft.
DATES: This AD becomes effective January 26, 2009.
ADDRESSES: You can get the service information identified in this AD
from General Electric Aircraft Engines CT7 Series Turboshaft Engines,
1000 Western Ave., Lynn, MA 01910; telephone (781) 594-6726; fax (781)
594-1583.
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 Richards, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803; e-
mail: christopher.j.richards@faa.gov; telephone (731) 238-7133; fax
(781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by
superseding AD 2006-06-51, Amendment 39-14566 (71 FR 19627, April 17,
2006), with a proposed AD. The proposed AD applies to certain GE CT7-8A
turboshaft engines. We published the proposed AD in the Federal
Register on March 19, 2008 (73 FR 14731). That action proposed to:
Delete the requirements to inspect the electrical chip
detector, and
Require removing any engine that has a serial number (SN)
listed in Table
[[Page 78176]]
1 of the proposed AD within 6,200 cycles-since-new (CSN) unless the
front frame was flushed and the No. 3 bearing replaced, and
Prohibit installing any engine that has a SN listed in
Table 1 of the proposed AD unless the front frame was flushed and the
No. 3 bearing replaced.
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 comments received.
Request for Changes to Contact Information for Service Information
One commenter, GE, asks that we change a typographical error in the
contact information for the service information from Turboprop to
Turboshaft. They also inform us they changed the contact telephone and
fax numbers.
We agree. We changed Turboprop to Turboshaft, and we changed the
contact telephone and fax numbers to (781) 594-6726 and (781) 594-1583
respectively.
Request for Changes to Actions Since AD 2006-06-51 Was Issued
The same commenter asks us to change the second bulleted item in
Actions Since AD 2006-06-51 Was Issued section and to delete the third
bulleted item.
We partially agree. Adding ``within 6,200 cycles-since-new (CSN)
unless * * * replaced'' is more clear. However, that section appears in
the preamble of the NPRM only. The final rule doesn't contain that
section so we can't make the requested change to the preamble.
Request To Remove the Prohibition Against Installing Engines After the
Effective Date of This AD
The same commenter asks us to remove the paragraph prohibiting
reinstallation of an engine until this AD has been complied with. The
commenter states there should be no restriction on reinstalling an
engine already in the field that might have been temporarily removed
for maintenance or used as a spare engine. The commenter states when
these engines are sent to an Engine Overhaul Shop (within 6,200 CSN)
they will get their front frame flushed and No. 3 bearing replaced.
Therefore, within the 6,200 CSN compliance requirement, there should be
no restriction to reinstalling the engines listed in Table 1 of the
proposed AD.
We agree. We have deleted the installation prohibition from the
regulatory text of the final rule.
Request To Reference the Latest Revision of Service Bulletin CT7-8 S/B
72-0017
The same commenter asks us to change the Relevant Service
Information section and the Related Information paragraph to include
Service Bulletin (SB) CT7-8 S/B 72-0017, Revision 01, dated February
15, 2008, and SB CT7-8 S/B 72-0017, Revision 02, dated May 14, 2008.
The commenter states that GE issued SB CT7-8 S/B 72-0017, Revision 01,
dated February 15, 2008, and SB CT7-8 S/B 72-0017, Revision 02, dated
May 14, 2008, after we issued the NPRM.
We partially agree. We added SB CT7-8 S/B 72-0017, Revision 02,
dated May 14, 2008, to the Related Information paragraph (i) and
changed paragraph (g) to state ``remove the engine from service and
flush the front frame and replace the No. 3 bearing. GE Aircraft
Engines Service Bulletin No. CT7-8 S/B 72-0017, Revision 02, dated May
14, 2008 or earlier revision, contains information on flushing the
front frame and replacing the No. 3 bearing.'' However, the Relevant
Service Information section appears in the preamble of the NPRM only.
The final rule doesn't contain that section so we can't make the
requested change to the preamble.
Request To Add Compliance Times to the Related Service Information
Paragraph
The same commenter asks us to change the Related Service
Information paragraph to include the compliance time of ``within 6,200
CSN or at the next shop visit, whichever occurs first.'' The commenter
recommends inserting this information to provide a brief explanation of
the intent of GE CT7-8 Service Bulletin 72-0017.
We don't agree. We already specify the compliance times in the
regulatory text. The purpose of the Related Service Information
paragraph is to provide a user with additional information that they
can use when complying with the regulatory requirements of the AD.
Request To Remove an Engine SN From Table 1 of the AD
The same commenter asks us to remove engine SN 947266 from Table 1
of the AD. The commenter states that they added that engine to the
``completed compliance list'' in Revision 01 of GE Aircraft Engines
CT7-8 Service Bulletin 72-0017.
We agree. We removed engine SN 947266 from Table 1 of the AD.
Request To Replace the Phrase ``Remove the Engine From Service''
The same commenter asks us to replace the phrase ``remove the
engine from service'' in paragraph (g) with ``Comply with GE Aircraft
Engines CT7-8 Service Bulletin 72-0017 Rev 00 or Rev 01 or Rev 02,
unless the front frame was flushed and the No. 3 bearing was replaced
previously.'' The commenter recommends the change to clarify the
requirements by stating that each engine listed in Table 1 of the AD
must comply with the requirements of GE Aircraft Engines CT7-8 Service
Bulletin 72-0017 within 6,200 CSN.
We partially agree. We determined paragraph (g) is clear because it
states the actions apply to engines with SNs listed in Table 1 and
because paragraph (e) requires performing the actions unless the
actions have already been done. However, we did change paragraph (g)
from ``within 6,200 cycles-since new, remove engine from service'' to
``within 6,200 cycles-since new, remove the engine from service and
flush the front frame and replace the No. 3 bearing. GE CT7-8 Shop
Manual, GEK 10517, and GE Aircraft Engines Service Bulletin No. CT7-8
S/B 72-0017, Revision 02, dated May 14, 2008, or earlier revision,
contain information on flushing the front frame and replacing the No. 3
bearing.'' We also added a new paragraph (h) to prohibit installing any
No. 3 bearing removed as required by paragraph (g).
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect 29 engines installed on
helicopters of U.S. registry. We also estimate that it
[[Page 78177]]
will take about 66.0 work-hours per engine to perform the required
actions, and that the average labor rate is $80 per work-hour. Required
parts will cost about $3,476 per engine. Based on these figures, we
estimate the total cost of the AD to U.S. operators to be $253,924.
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 removing Amendment 39-14566 (71 FR
19627, April 17, 2006) and by adding a new airworthiness directive,
Amendment 39-15768, to read as follows:
2008-26-02 General Electric Company: Amendment 39-15768. Docket No.
FAA-2006-24261; Directorate Identifier 2006-NE-12-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
26, 2009.
Affected ADs
(b) This AD supersedes AD 2006-06-51, Amendment 39-14566.
Applicability
(c) This AD applies to General Electric Company (GE) CT7-8A
turboshaft engines that have a serial number (SN) listed in Table 1
of this AD. These engines are installed on, but not limited to,
Sikorsky S92 helicopters.
Table 1--Affected Engines by Serial Number
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Engine Serial Number
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947205 947215 947230 947243 947254 947265
947206 947217 947232 947244 947255 947274
947207 947218 947233 947245 947256 947277
947208 947219 947235 947247 947258 947278
947209 947220 947238 947248 947260 947279
947210 947221 947240 947249 947261 947280
947211 947223 947241 947250 947262 947284
947212 947225 947242 947253 947263 947285
947214 947228
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from investigation for the root causes of
two failures of the No. 3 bearing. We are issuing this AD to prevent
failure of the No. 3 bearing due to contamination by aluminum oxide,
which could result in a possible in-flight shutdown of the engines
and loss of control or forced landing of the aircraft.
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.
(f) No further action is required if:
(1) Your engine has a SN that is not listed in Table 1 of this
AD, or
(2) Your engine has a SN listed in Table 1 of this AD, but the
engine log specifies that the front frame was flushed and the No. 3
bearing was replaced.
Engines With SNs listed in Table 1 of This AD
(g) For engines with a SN listed in Table 1 of this AD, within
6,200 cycles-since-new, remove the engine from service and flush the
front frame and replace the No. 3 bearing. GE CT7-8 Shop Manual, GEK
10517, contains information on replacing the No. 3 bearing and GE
Aircraft Engines Service Bulletin No. CT7-8 S/B 72-0017, Revision
02, dated May 14, 2008, or earlier revision, contains information on
flushing the front frame and replacing the No. 3 bearing.
Prohibition Against Reinstalling a No. 3 Bearing
(h) After the effective date of this AD, do not install any No.
3 bearing removed as a requirement of paragraph (g) of this AD.
Alternative Methods of Compliance
(i) The Manager, Engine Certification Office, FAA, 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
(j) GE CT7-8 Shop Manual, GEK 10517, and GE Aircraft Engines
Service Bulletin No. CT7-8 S/B 72-0017, Revision 02, dated May 14,
2008 and earlier revisions pertain to the subject of this AD.
Contact General Electric Aircraft Engines CT7 Series Turboshaft
[[Page 78178]]
Engines, 1000 Western Ave., Lynn, MA 01910; telephone (781) 594-
6726; fax (781) 594-1583, for a copy of this service information.
(k) Contact Christopher Richards, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
christopher.j.richards@faa.gov; telephone (731) 238-7133; fax (781)
238-7199, for more information about this AD.
Material Incorporated by Reference
(l) None.
Issued in Burlington, Massachusetts, on December 9, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-29722 Filed 12-19-08; 8:45 am]
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