Airworthiness Directives; General Electric Company (GE) CT7-8A Turboshaft Engines, 78175-78178 [E8-29722]
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Federal Register / Vol. 73, No. 246 / Monday, December 22, 2008 / Rules and Regulations
78175
TABLE 1—AFFECTED EXHAUST MUFFLERS BY GROUP, P/N, AND SN
Group
P/N
SN
(1) A ..................
979402
(2) B ..................
979402
979404
02.0001 through 02.0322, 03.0002, 03.0005, 03.0011, 03.0015, 03.0017, 03.0028, 03.0029, 03.0037,
03.0038, 03.0040, 03.0050, 03.0069, 03.0072, 03.0073, 03.0078, 03.0080 through 03.0086, 03.0088
through 03.0090, 03.0092 through 03.0101, 03.0103, and 03.0108.
03.0001, 03.0003, 03.0004, 03.0006, 03.0007 through 03.0010, 03.0012 through 03.0014, 03.0016, 03.0018
through 03.0027, 03.0030 through 03.0036, 03.0039, 03.0041 through 03.0049, 03.0051 through 03.0068,
03.0070, 03.0071, 03.0074 through 03.0077, 03.0079, 03.0087, 03.0091, 03.0102, and 03.0104 through
03.0107.
03.0200 through 04.0799.
Reason
(d) Occurrence of cracks in the exhaust
muffler in the area of the exhaust bottom and
exhaust flange were reported, which could
lead to toxic contamination inside the cabin.
We are issuing this AD to prevent carbon
monoxide contamination in the cockpit,
which can adversely affect the pilot, and
possibly result in loss of control of the
aircraft.
Actions and 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.
Initial Visual Inspection
Group A Exhaust Mufflers
(f) For exhaust mufflers specified in Group
A of Table 1 of this AD, within 50 hours of
operation after the effective date of this AD,
do the following:
(1) Perform a visual inspection around the
fillet weld of the exhaust inlet flange and
around the weld of the exhaust outlet for
evidence of leakage or cracks. Information on
inspecting the exhaust muffler can be found
in Bombardier-Rotax GmbH 914 F Service
Bulletin (SB) No. SB–914–028 R1, dated
November 8, 2004.
(2) If you see evidence of an exhaust leak
or cracks, replace the exhaust muffler.
Alternative Methods of Compliance
(AMOCs)
(j) The Manager, Engine Certification
Office, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Related Information
(k) Refer to MCAI EASA Airworthiness
Directive 2006–0127, dated May 18, 2006,
and Bombardier-Rotax GmbH 914 F Service
Bulletin No. SB–914–028 R1, dated
November 8, 2004, for related information.
Contact Bombardier-Rotax GmbH,
Gunskirchen, Austria; telephone: 7246–601–
423; fax: 7246–601–760, or go to: https://
www.rotax-aircraft-engines.com, for a copy of
this service bulletin.
(l) Contact Richard Woldan, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park; Burlington, MA
01803; telephone (781) 238–7136; fax (781)
238–7199, for more information about this
AD.
Material Incorporated by Reference
(m) None.
Issued in Burlington, Massachusetts, on
December 11, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E8–30049 Filed 12–19–08; 8:45 am]
BILLING CODE 4910–13–P
Group B Exhaust Mufflers
(g) For exhaust mufflers specified in Group
B of Table 1 of this AD, within 50 hours of
operation after the effective date of this AD,
do the following:
(1) Perform a visual inspection around the
weld of the exhaust outlet for evidence of
leakage or cracks. Information on inspecting
the exhaust muffler can be found in
Bombardier-Rotax GmbH 914 F Service
Bulletin No. SB–914–028 R1, dated
November 8, 2004.
(2) If you see evidence of an exhaust leak
or cracks, replace the exhaust muffler.
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Repetitive Visual Inspections
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
(h) Within 50 hours of operation since the
last inspection, perform the actions specified
in paragraphs (f)(1) through (f)(2) and (g)(1)
through (g)(2) of this AD.
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
FAA AD Differences
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
(i) None.
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16:38 Dec 19, 2008
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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 inflight 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
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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 https://
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
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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
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16:38 Dec 19, 2008
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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
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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 cyclessince 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
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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
Accordingly, under the authority
delegated to me by the Administrator,
■
78177
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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
Engine Serial Number
947205
947206
947207
947208
947209
947210
947211
947212
947214
947215
947217
947218
947219
947220
947221
947223
947225
947228
947230
947232
947233
947235
947238
947240
947241
947242
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.
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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
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21:38 Dec 19, 2008
Jkt 217001
947243
947244
947245
947247
947248
947249
947250
947253
947254
947255
947256
947258
947260
947261
947262
947263
947265
947274
947277
947278
947279
947280
947284
947285
the front frame was flushed and the No. 3
bearing was replaced.
Prohibition Against Reinstalling a No. 3
Bearing
Engines With SNs listed in Table 1 of This
AD
(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.
(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.
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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
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Federal Register / Vol. 73, No. 246 / Monday, December 22, 2008 / Rules and Regulations
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]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2008–0005; Airspace
Docket No. 08–AAL–1]
Revision of Class E Airspace; Ruby,
AK
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SUMMARY: This action corrects an error
in the airspace description contained in
a Final Rule that was published in the
Federal Register on Monday, November
10, 2008 (73 FR 66515). Airspace Docket
No. 08–AAL–1.
DATES: Effective Date: 0901 UTC,
January 15, 2009.
FOR FURTHER INFORMATION CONTACT: Gary
Rolf, AAL–538G, Federal Aviation
Administration, 222 West 7th Avenue,
Box 14, Anchorage, AK 99513–7587;
telephone number (907) 271–5898; fax:
(907) 271–2850; e-mail:
gary.ctr.rolf@faa.gov. Internet address:
https://www.faa.gov/about/office_org/
headquarters_offices/ato/service_units/
systemops/fs/alaskan/rulemaking/.
SUPPLEMENTARY INFORMATION:
History
Federal Register Docket No. FAA–
2008–0005, Airspace Docket No. 08–
AAL–1, published on Monday,
November 10, 2008 (73 FR 66515),
revised Class E airspace at Ruby, AK.
An error was discovered in the airspace
description defining the lateral confines
of the Class E (700 foot) description. The
controlled airspace extending to the
northeast along the 051° bearing from
16:38 Dec 19, 2008
Jkt 217001
Correction to Final Rule
Accordingly, pursuant to the authority
delegated to me, the airspace
description of the Class E airspace
published in the Federal Register,
Monday, November 10, 2008 (73 FR
66515), FAA Docket No. 2008–0005,
Airspace Docket No. 08–AAL–1, page
66516, column 2 is corrected as follows:
■
§ 71.1
*
[Corrected]
*
*
*
*
AAL AK E5 Ruby, AK [Corrected]
Ruby, Ruby Airport, AK
(Lat. 64°43′38″ N., long. 155°28′11″ W.)
That airspace extending upward from 700
feet above the surface within a 6.4-mile
radius of the Ruby Airport, AK, and within
4 miles either side of the 051° bearing from
the Ruby Airport, AK, extending from the
6.4-mile radius to 20.3 miles northeast of the
Ruby Airport, AK; and that airspace
extending upward from 1,200 feet above the
surface within a 70-mile radius of the Ruby
Airport, AK.
*
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; correction.
VerDate Aug<31>2005
the airport will only cover 4 miles either
side of the 051° bearing (instead of 8
miles), and will only cover 50% of what
was described. This action corrects that
error.
*
*
*
*
Issued in Anchorage, AK, on December 4,
2008.
Anthony M. Wylie
Manager, Alaska Flight Services Information
Area Group.
[FR Doc. E8–30170 Filed 12–19–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2008–0998; Airspace
Docket No. 08–AAL–29]
Revision of Class E Airspace;
Ketchikan, AK
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: This action revises Class E
airspace at Ketchikan, AK to provide
adequate controlled airspace to contain
aircraft executing Standard Instrument
Approach Procedures (SIAPs). Seven
SIAPs, two Standard Instrument
Departure Procedures (SIDs) and a
textual Obstacle Departure Procedure
(ODP) are being amended or drafted for
the Ketchikan International Airport.
This action revises existing Class E
airspace upward from 700 feet (ft.) and
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1,200 ft. above the surface at Ketchikan
International Airport, Ketchikan, AK.
DATES: Effective Date: 0901 UTC, March
12, 2009. The Director of the Federal
Register approves this incorporation by
reference action under title 1, Code of
Federal Regulations, part 51, subject to
the annual revision of FAA Order
7400.9 and publication of conforming
amendments.
FOR FURTHER INFORMATION CONTACT: Gary
Rolf, AAL–538G, Federal Aviation
Administration, 222 West 7th Avenue,
Box 14, Anchorage, AK 99513–7587;
telephone number (907) 271–5898; fax:
(907) 271–2850; e-mail:
gary.ctr.rolf@faa.gov. Internet address:
https://www.faa.gov/about/office_org/
headquarters_offices/ato/service_units/
systemops/fs/alaskan/rulemaking/.
SUPPLEMENTARY INFORMATION:
History
On Friday, October 17, 2008, the FAA
proposed to amend part 71 of the
Federal Aviation Regulations (14 CFR
part 71) to revise Class E airspace
upward from 700 ft. above the surface
and from 1,200 ft. above the surface at
Ketchikan, AK (73 FR 61749). The
action was proposed in order to create
Class E airspace sufficient in size to
contain aircraft while executing
instrument procedures for the Ketchikan
International Airport. Class E controlled
airspace extending upward from 700 ft.
and 1,200 ft. above the surface in the
Ketchikan International Airport area is
revised by this action.
Interested parties were invited to
participate in this rulemaking
proceeding by submitting written
comments on the proposal to the FAA.
No comments were received. The rule is
adopted as proposed with the following
exception. The airport location has been
updated to reflect new data obtained in
a recent survey.
The area will be depicted on
aeronautical charts for pilot reference.
The coordinates for this airspace docket
are based on North American Datum 83.
The Class E airspace areas designated as
700/1,200 ft. transition areas are
published in paragraph 6005 of FAA
Order 7400.9S, Airspace Designations
and Reporting Points, signed October 3,
2008, and effective October 31, 2008,
which is incorporated by reference in 14
CFR 71.1. The Class E airspace
designations listed in this document
will be published subsequently in the
Order.
The Rule
This amendment to 14 CFR part 71
revises Class E airspace at the Ketchikan
International Airport, Alaska. This Class
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Agencies
[Federal Register Volume 73, Number 246 (Monday, December 22, 2008)]
[Rules and Regulations]
[Pages 78175-78178]
From the Federal Register Online via the Government Printing 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 https://
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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