Airworthiness Directives; General Electric Company CT7-5, -7, and -9 Series Turboprop Engines, 17379-17381 [E7-6446]
Download as PDF
<![CDATA[
Federal Register / Vol. 72, No. 67 / Monday, April 9, 2007 / Rules and Regulations
Issued in Renton, Washington, on March
28, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–6450 Filed 4–6–07; 8:45 am]
TABLE 1.—REQUIRED MATERIAL
INCORPORATED BY REFERENCE
Airbus Service information
Date
All Operators Telex
A300–54A6037.
All Operators Telex
A310–54A2038.
Service Bulletin A300–
24–6097, including
Appendix 01.
Service Bulletin A310–
24–2100, including
Appendix 01.
February 19, 2004.
February 19, 2004.
DEPARTMENT OF TRANSPORTATION
March 3, 2006.
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20944; Directorate
Identifier 2003–NE–64–AD; Amendment 39–
15018; AD 2007–08–01]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company CT7–5, –7, and –9
Series Turboprop Engines
TABLE 2.—OPTIONAL MATERIAL
INCORPORATED BY REFERENCE
Airbus Service information
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
Date
May 12, 2006.
May 12, 2006.
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information identified in Table 3
of this AD in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51.
TABLE 3.—NEW MATERIAL
INCORPORATED BY REFERENCE
Airbus Service Bulletin
rwilkins on PROD1PC63 with RULES
A300–24–6097, including Appendix 01.
A300–54–6038 .............
A310–24–2100, including Appendix 01.
A310–54–2039 .............
Date
March 3, 2006.
May 12, 2006.
March 3, 2006.
May 12, 2006.
(2) On May 13, 2004 (69 FR 23090, April
28, 2004), the Director of the Federal Register
approved the incorporation by reference of
Airbus All Operators Telex A310–54A2038,
dated February 19, 2004; and Airbus All
Operators Telex A300–54A6037, dated
February 19, 2004.
(3) Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France, for a
copy of this service information. You may
review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
VerDate Aug<31>2005
16:25 Apr 06, 2007
Jkt 211001
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
Room PL–401 on the plaza level of the
Nassif Building, 400 Seventh Street,
SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Mark Bouyer, Engine Certification
Office, FAA, Engine and Propeller
Directorate, 12 New England Executive
Park, Burlington, MA 01803; telephone
(781) 238–7755; fax (781) 238–7199.
The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to GE CT7–5A2, –5A3, –7A,
–7A1, –9B, –9B1, and –9B2 turboprop
engines, with certain P/N and serial
number stage 2 turbine aft cooling plates
installed. We published the proposed
AD in the Federal Register on March 31,
2006 (71 FR 16248). That action
proposed to expand the population of
affected CT7 turboprop engine models
required to undergo a onetime ECI of
boltholes in certain P/N stage 2 turbine
aft cooling plates. That action also
proposed to reduce the number of
cooling plates affected by identifying
the serial numbers.
SUPPLEMENTARY INFORMATION:
March 3, 2006.
You must use the service information
identified in Table 2 of this AD to perform
the optional terminating action, if
accomplished, unless the AD specifies
otherwise.
Service Bulletin A300–
54–6038.
Service Bulletin A310–
54–2039.
BILLING CODE 4910–13–P
17379
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
General Electric Company (GE) CT7–
5A2, –5A3, –7A, –7A1, –9B, –9B1, and
–9B2, –9C, –9C3, –9D, and –9D2
turboprop engines, with certain part
number (P/N) and serial number stage 2
turbine aft cooling plates installed. That
AD currently requires a onetime eddy
current inspection (ECI) of boltholes in
certain P/N stage 2 turbine aft cooling
plates. This AD expands the population
of affected CT7 turboprop engine
models, but reduces the number of
cooling plates affected. It also requires
a onetime ECI of boltholes in certain P/
N stage 2 turbine aft cooling plates with
specific serial numbers. This AD results
from the manufacturer expanding the
list of affected engine models and
identifying the affected stage 2 turbine
aft cooling plates by serial number. We
are issuing this AD to prevent
separation of the stage 2 turbine aft
cooling plate, resulting in uncontained
engine failure and damage to the
airplane.
This AD becomes effective May
14, 2007. The Director of the Federal
Register approved the incorporation by
reference of certain publications listed
in the regulations as of May 14, 2007.
ADDRESSES: You can get the service
information identified in this AD from
General Electric Aircraft Engines CT7
Series Turboprop Engines, 1000
Western Ave, Lynn, MA 01910;
telephone (781) 594–3140, fax (781)
594–4805.
DATES:
PO 00000
Frm 00027
Fmt 4700
Sfmt 4700
Examining the AD Docket
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The Docket Office (telephone
(800) 647–5227) is located on the plaza
level of the Department of
Transportation Nassif Building at the
street address stated in ADDRESSES.
Comments will be available in the AD
docket shortly after the DMS receives
them.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Clarification of ECI Requirements
GE suggests that we clarify paragraph
(f) of this AD to limit the required ECI
to stage 2 turbine aft cooling plates that
are being returned to service. This
change would eliminate any
requirement to ECI cooling plates that
are not going to be reused. We agree. If
the cooling plate is not going to be
reused, there is no need to ECI it
immediately after it is removed.
Paragraph (h) of this AD requires an ECI
of all cooling plates affected by this AD
before they are returned to service. We
made the clarification to paragraph (f).
E:\FR\FM\09APR1.SGM
09APR1
17380
Federal Register / Vol. 72, No. 67 / Monday, April 9, 2007 / Rules and Regulations
Clarification of Onetime Inspection
GE proposes that we add a
terminating action statement to clarify
that the ECI is a onetime inspection and
repetitive inspections of the stage 2
turbine aft cooling plate is unnecessary.
We do not agree. This information is
already included in paragraph (f), which
specifies that the inspection is a
onetime ECI. We did not change the AD.
Question on Compliance Threshold of
6,000 Cycles-in-Service (CIS)
GE also questions whether the
calculated compliance threshold of
6,000 CIS is viable given the amount of
time required to publish the AD. We do
not agree. The number of engine cycles
that will accumulate during the AD
review process will not change the
safety assessment that is based on the
calculated compliance time. We did not
change the AD.
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.
rwilkins on PROD1PC63 with RULES
Costs of Compliance
We estimate that this AD will affect
494 engines installed on airplanes of
U.S. registry. We also estimate that it
will take about 1 work-hour per engine
to perform the actions, and that the
average labor rate is $80 per work-hour.
Based on the number of cracks found in
the inspected engines, we estimate that
2.5 percent of the 494 engines will
require replacing stage 2 turbine aft
cooling plates because of rejection by
the onetime ECI. Required parts will
cost about $17,000 per engine. Based on
these figures, we estimate the total cost
of the AD to U.S. operators to be
$243,520.
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
VerDate Aug<31>2005
16:25 Apr 06, 2007
Jkt 211001
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, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–14247 70 FR
54835, September 19, 2005, and by
adding a new airworthiness directive,
Amendment 39–15018, to read as
follows:
I
2007–08–01 General Electric Company:
Amendment 39–15018. Docket No.
FAA–2005–20944; Directorate Identifier
2003–NE–64–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective May 14, 2007.
PO 00000
Frm 00028
Fmt 4700
Sfmt 4700
Affected ADs
(b) This AD supersedes AD 2005–18–01,
Amendment 39–14247.
Applicability
(c) This AD applies to General Electric
Company (GE) CT7–5A2/–5A3/–7A/–7A1/–
9B/–9B1/–9B2/–9C/–9C3/–9D/–9D2
turboprop engines with stage 2 turbine aft
cooling plates, part number (P/N)
6064T07P01, 6064T07P02, 6064T07P05, or
6068T36P01 installed. These engines are
installed on, but not limited to,
Construcciones Aeronauticas, SA CN–235
series and SAAB Aircraft AB SF340 series
airplanes.
Unsafe Condition
(d) This AD results from the manufacturer
expanding the list of affected engine models
and identifying the affected stage 2 turbine
aft cooling plates by serial number. We are
issuing this AD to prevent separation of the
stage 2 turbine aft cooling plate, resulting in
uncontained engine failure and damage to
the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed at the
next engine or hot section module shop visit,
but before accumulating an additional 6,000
cycles-in-service after the effective date of the
AD, unless already done.
Onetime Eddy Current Inspection (ECI)
(f) Perform a onetime ECI of the stage 2
turbine aft cooling plates P/N 6064T07P01,
6064T07P02, 6064T07P05, or 6068T36P01,
that are listed by serial number in Section 4,
Appendix A, of GE Alert Service Bulletin
(ASB) No. CT7–TP S/B 72–A0464, Revision
04, dated December 12, 2005, and that will
be returned to service. Use 3.B.(1) through
3.B.(3) of GE ASB No. CT7–TP S/B 72–
A0464, Revision 4, dated December 12, 2005
to perform the inspection.
(g) For stage 2 turbine aft cooling plates
that do not pass the Return to Service
Criteria, do either of the following:
(1) Replace the stage 2 turbine aft cooling
plate with a new cooling plate that has a
serial number that is not listed in Section 4,
Appendix A, of GE ASB No. CT7–TP S/B 72–
A0464, Revision 04, dated December 12,
2005, or
(2) Replace the stage 2 turbine aft cooling
plate with a cooling plate that meets the
acceptance criteria of 3.B.(1) through 3.B.(3)
of GE ASB No. CT7–TP S/B 72–A0464,
Revision 4, dated December 12, 2005.
(h) After the effective date of this AD, do
not install any stage 2 turbine aft cooling
plates with serial numbers identified in
Section 4, Appendix A, without inspecting
the cooling plate as specified in 3.B.(1)
through 3.B.(3) of GE ASB No. CT7–TP S/B
72–A0464 Revision 04, December 12, 2005.
Previous Credit
(i) Eddy current inspections of the stage 2
turbine aft cooling plate boltholes done
before the effective date of this AD that use
GE ASB No. CT7–TP S/B 72–A0464, dated
February 25, 2003; or Revision 1, dated
March 12, 2003; or Revision 2, dated May 9,
E:\FR\FM\09APR1.SGM
09APR1
Federal Register / Vol. 72, No. 67 / Monday, April 9, 2007 / Rules and Regulations
2003; or Revision 3, dated July 23, 2004,
comply with the requirements specified in
this AD.
ACTION:
Definition of Engine or Hot Section Module
Shop Visit
(j) For the purposes of this AD, an engine
or hot section module shop visit is defined
as the introduction of the engine or hot
section module into a shop that includes
separating major case flanges.
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) Contact Mark Bouyer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; email: mark.bouyer@faa.gov; telephone (781)
238–7755; fax (781) 238–7199, for more
information about this AD.
Material Incorporated by Reference
(m) You must use General Electric Alert
Service Bulletin No. CT7–TP S/B 72–A0464,
Revision 04, dated December 12, 2005, to
perform the actions required by this AD. The
Director of the Federal Register approved the
incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Contact General Electric
Aircraft Engines CT7 Series Turboprop
Engines, 1000 Western Ave, Lynn, MA
01910; telephone (781) 594–3140; fax (781)
594–4805 for a copy of this service
information. You may review copies at the
FAA, New England Region, Office of the
Regional Counsel, 12 New England Executive
Park, Burlington, MA; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/federalregister/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on
April 2, 2007.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–6446 Filed 4–6–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Office of the Secretary
14 CFR Part 331
[Docket OST–2006–25906]
rwilkins on PROD1PC63 with RULES
RIN 2105–AD61
Procedures for Reimbursement of
General Aviation Operators and
Service Providers in the Washington,
DC Area
AGENCY:
Office of the Secretary, DOT.
VerDate Aug<31>2005
16:25 Apr 06, 2007
Jkt 211001
Final rule.
SUMMARY: This rule provides
reimbursement to fixed-base general
aviation operators and providers of
general aviation ground support services
at five metropolitan Washington, DC
area airports, for the direct and
incremental financial losses they
incurred while the airports were closed
due to Federal government actions taken
after the terrorist attacks on September
11, 2001. The airports are: Ronald
Reagan Washington National Airport;
College Park Airport in College Park,
Maryland; Potomac Airfield in Fort
Washington, Maryland; Washington
Executive/Hyde Field in Clinton,
Maryland; and Washington South
Capitol Street Heliport in Washington,
DC.
DATES: This rule is effective May 9,
2007.
FOR FURTHER INFORMATION CONTACT:
Interested persons with questions about
this regulation should contact James R.
Dann, U.S. Department of
Transportation, Office of General
Counsel, 400 7th Street, SW., Room
10102, Washington, DC 20590;
telephone 202–366–9154. Interested
persons with questions about how to
apply for assistance, the status of
application reviews, etc. should contact
Tim Carmody, U.S. Department of
Transportation, Office of Aviation
Analysis, 400 7th Street, SW., Room
6417, Washington, DC 20590; telephone
202–366–2348. Application materials
and data sources that may assist
applicants in preparing applications are
available at the Department of
Transportation, Office of the Secretary’s
Web site at https://ostpxweb.dot.gov/
aviation/ under ‘‘Programs,’’
and then ‘‘General Aviation Operator
and Services Reimbursement:
Procedures for Reimbursement of
General Aviation Operators and Service
Providers in the Washington, DC Area.’’
SUPPLEMENTARY INFORMATION: Following
the terrorist attacks on the United States
on September 11, 2001, general aviation
activity in the Washington, DC
metropolitan area was suspended. Five
airports were most affected: Ronald
Reagan Washington National Airport
(DCA); College Park Airport in College
Park, Maryland; Potomac Airfield in
Fort Washington, Maryland;
Washington Executive/Hyde Field in
Clinton, Maryland; and Washington
South Capitol Street Heliport in
Washington, DC. While DCA and the
three Maryland airports have since been
reopened to transient general aviation
traffic, the volume of general aviation
activity has not returned to
PO 00000
Frm 00029
Fmt 4700
Sfmt 4700
17381
pre-September 11, 2001 levels due to
continuing security restrictions, and the
South Capitol Street Heliport was not
reopened to general aviation traffic and
is now used exclusively by the
Washington DC Metropolitan Police.
Because of the reduction in general
aviation activity at these locations, the
fixed-base operators and service
providers that supported general
aviation were also affected, with many
claiming that they were incurring
sustained and significant financial
losses due to the closures.
These fixed-base operators and
service providers were not eligible for
either compensation or loan guarantees
under the Air Transportation Safety and
System Stabilization Act, Pub. L. 107–
42 (Sept. 22, 2001), which had been
enacted to provide compensation to ‘‘air
carriers’’ who had incurred financial
losses due to the terrorist attacks. Under
that program, approximately $4.6 billion
has been paid to qualifying air carriers.
In 2003, the United States House of
Representatives Committee on
Appropriations requested that the
Department of Transportation (DOT)
prepare a report detailing the
documented financial losses by holders
of real property leases at the five
affected airports that were attributable
to the Federal actions since September
11, 2001. (House Report 108–243, July
30, 2003, p. 8.) The Committee stated
that such a report would assist the
Congress in considering ‘‘potential
federal reimbursement for a portion of
these unusual financial losses.’’ In
October 2005, the Secretary of
Transportation submitted to the
Committee the requested report, which
was entitled: Estimated Financial Losses
to Selected General Aviation Entities in
the Washington, DC Area Final Report
(October 2005 DOT study). A copy of
this Report has been placed onto the
Office of the Secretary’s Web site, at the
address noted above. (See FOR FURTHER
INFORMATION CONTACT).
The October 2005 DOT study
identified sixteen general aviation
leaseholders at the five airports, and
estimated the financial losses that each
incurred during its study period (which
ran from September 11, 2001 to January
23, 2004) due to the Federal actions
taken after the terrorist attacks. The
estimates reflected the difference in net
income stated on a pre-tax basis
between what the companies projected
for the study period and the actual pretax net income for that period, and
included both losses in pre-tax net
income and one-time costs attributable
directly to compliance with new
restrictions or regulations resulting from
the terrorist attacks. In formulating its
E:\FR\FM\09APR1.SGM
09APR1
]]>Agencies
[Federal Register Volume 72, Number 67 (Monday, April 9, 2007)]
[Rules and Regulations]
[Pages 17379-17381]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-6446]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20944; Directorate Identifier 2003-NE-64-AD;
Amendment 39-15018; AD 2007-08-01]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CT7-5, -7, and
-9 Series Turboprop Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for General Electric Company (GE) CT7-5A2, -5A3, -7A, -7A1, -9B, -
9B1, and -9B2, -9C, -9C3, -9D, and -9D2 turboprop engines, with certain
part number (P/N) and serial number stage 2 turbine aft cooling plates
installed. That AD currently requires a onetime eddy current inspection
(ECI) of boltholes in certain P/N stage 2 turbine aft cooling plates.
This AD expands the population of affected CT7 turboprop engine models,
but reduces the number of cooling plates affected. It also requires a
onetime ECI of boltholes in certain P/N stage 2 turbine aft cooling
plates with specific serial numbers. This AD results from the
manufacturer expanding the list of affected engine models and
identifying the affected stage 2 turbine aft cooling plates by serial
number. We are issuing this AD to prevent separation of the stage 2
turbine aft cooling plate, resulting in uncontained engine failure and
damage to the airplane.
DATES: This AD becomes effective May 14, 2007. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of May 14, 2007.
ADDRESSES: You can get the service information identified in this AD
from General Electric Aircraft Engines CT7 Series Turboprop Engines,
1000 Western Ave, Lynn, MA 01910; telephone (781) 594-3140, fax (781)
594-4805.
You may examine the AD docket on the Internet at https://dms.dot.gov
or in Room PL-401 on the plaza level of the Nassif Building, 400
Seventh Street, SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mark Bouyer, Engine Certification
Office, FAA, Engine and Propeller Directorate, 12 New England Executive
Park, Burlington, MA 01803; telephone (781) 238-7755; 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 CT7-5A2, -5A3, -7A, -
7A1, -9B, -9B1, and -9B2 turboprop engines, with certain P/N and serial
number stage 2 turbine aft cooling plates installed. We published the
proposed AD in the Federal Register on March 31, 2006 (71 FR 16248).
That action proposed to expand the population of affected CT7 turboprop
engine models required to undergo a onetime ECI of boltholes in certain
P/N stage 2 turbine aft cooling plates. That action also proposed to
reduce the number of cooling plates affected by identifying the serial
numbers.
Examining the AD Docket
You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
Facility between 9 a.m. and 5 p.m., Monday through Friday, except
Federal holidays. The Docket Office (telephone (800) 647-5227) is
located on the plaza level of the Department of Transportation Nassif
Building at the street address stated in ADDRESSES. Comments will be
available in the AD docket shortly after the DMS receives them.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Clarification of ECI Requirements
GE suggests that we clarify paragraph (f) of this AD to limit the
required ECI to stage 2 turbine aft cooling plates that are being
returned to service. This change would eliminate any requirement to ECI
cooling plates that are not going to be reused. We agree. If the
cooling plate is not going to be reused, there is no need to ECI it
immediately after it is removed. Paragraph (h) of this AD requires an
ECI of all cooling plates affected by this AD before they are returned
to service. We made the clarification to paragraph (f).
[[Page 17380]]
Clarification of Onetime Inspection
GE proposes that we add a terminating action statement to clarify
that the ECI is a onetime inspection and repetitive inspections of the
stage 2 turbine aft cooling plate is unnecessary. We do not agree. This
information is already included in paragraph (f), which specifies that
the inspection is a onetime ECI. We did not change the AD.
Question on Compliance Threshold of 6,000 Cycles-in-Service (CIS)
GE also questions whether the calculated compliance threshold of
6,000 CIS is viable given the amount of time required to publish the
AD. We do not agree. The number of engine cycles that will accumulate
during the AD review process will not change the safety assessment that
is based on the calculated compliance time. We did not change the AD.
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 494 engines installed on
airplanes of U.S. registry. We also estimate that it will take about 1
work-hour per engine to perform the actions, and that the average labor
rate is $80 per work-hour. Based on the number of cracks found in the
inspected engines, we estimate that 2.5 percent of the 494 engines will
require replacing stage 2 turbine aft cooling plates because of
rejection by the onetime ECI. Required parts will cost about $17,000
per engine. Based on these figures, we estimate the total cost of the
AD to U.S. operators to be $243,520.
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, Incorporation by
reference, 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 39-14247 70 FR
54835, September 19, 2005, and by adding a new airworthiness directive,
Amendment 39-15018, to read as follows:
2007-08-01 General Electric Company: Amendment 39-15018. Docket No.
FAA-2005-20944; Directorate Identifier 2003-NE-64-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 14,
2007.
Affected ADs
(b) This AD supersedes AD 2005-18-01, Amendment 39-14247.
Applicability
(c) This AD applies to General Electric Company (GE) CT7-5A2/-
5A3/-7A/-7A1/-9B/-9B1/-9B2/-9C/-9C3/-9D/-9D2 turboprop engines with
stage 2 turbine aft cooling plates, part number (P/N) 6064T07P01,
6064T07P02, 6064T07P05, or 6068T36P01 installed. These engines are
installed on, but not limited to, Construcciones Aeronauticas, SA
CN-235 series and SAAB Aircraft AB SF340 series airplanes.
Unsafe Condition
(d) This AD results from the manufacturer expanding the list of
affected engine models and identifying the affected stage 2 turbine
aft cooling plates by serial number. We are issuing this AD to
prevent separation of the stage 2 turbine aft cooling plate,
resulting in uncontained engine failure and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed at the next engine or hot section module shop visit,
but before accumulating an additional 6,000 cycles-in-service after
the effective date of the AD, unless already done.
Onetime Eddy Current Inspection (ECI)
(f) Perform a onetime ECI of the stage 2 turbine aft cooling
plates P/N 6064T07P01, 6064T07P02, 6064T07P05, or 6068T36P01, that
are listed by serial number in Section 4, Appendix A, of GE Alert
Service Bulletin (ASB) No. CT7-TP S/B 72-A0464, Revision 04, dated
December 12, 2005, and that will be returned to service. Use 3.B.(1)
through 3.B.(3) of GE ASB No. CT7-TP S/B 72-A0464, Revision 4, dated
December 12, 2005 to perform the inspection.
(g) For stage 2 turbine aft cooling plates that do not pass the
Return to Service Criteria, do either of the following:
(1) Replace the stage 2 turbine aft cooling plate with a new
cooling plate that has a serial number that is not listed in Section
4, Appendix A, of GE ASB No. CT7-TP S/B 72-A0464, Revision 04, dated
December 12, 2005, or
(2) Replace the stage 2 turbine aft cooling plate with a cooling
plate that meets the acceptance criteria of 3.B.(1) through 3.B.(3)
of GE ASB No. CT7-TP S/B 72-A0464, Revision 4, dated December 12,
2005.
(h) After the effective date of this AD, do not install any
stage 2 turbine aft cooling plates with serial numbers identified in
Section 4, Appendix A, without inspecting the cooling plate as
specified in 3.B.(1) through 3.B.(3) of GE ASB No. CT7-TP S/B 72-
A0464 Revision 04, December 12, 2005.
Previous Credit
(i) Eddy current inspections of the stage 2 turbine aft cooling
plate boltholes done before the effective date of this AD that use
GE ASB No. CT7-TP S/B 72-A0464, dated February 25, 2003; or Revision
1, dated March 12, 2003; or Revision 2, dated May 9,
[[Page 17381]]
2003; or Revision 3, dated July 23, 2004, comply with the
requirements specified in this AD.
Definition of Engine or Hot Section Module Shop Visit
(j) For the purposes of this AD, an engine or hot section module
shop visit is defined as the introduction of the engine or hot
section module into a shop that includes separating major case
flanges.
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) Contact Mark Bouyer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New England Executive Park,
Burlington, MA 01803; e-mail: mark.bouyer@faa.gov; telephone (781)
238-7755; fax (781) 238-7199, for more information about this AD.
Material Incorporated by Reference
(m) You must use General Electric Alert Service Bulletin No.
CT7-TP S/B 72-A0464, Revision 04, dated December 12, 2005, to
perform the actions required by this AD. The Director of the Federal
Register approved the incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact General Electric Aircraft Engines CT7 Series Turboprop
Engines, 1000 Western Ave, Lynn, MA 01910; telephone (781) 594-3140;
fax (781) 594-4805 for a copy of this service information. You may
review copies at the FAA, New England Region, Office of the Regional
Counsel, 12 New England Executive Park, Burlington, MA; or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call 202-741-6030, or
go to: https://www.archives.gov/federal-register/cfr/ibr-
locations.html.
Issued in Burlington, Massachusetts, on April 2, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-6446 Filed 4-6-07; 8:45 am]
BILLING CODE 4910-13-P
