Airworthiness Directives; General Electric Company (GE) CF6-80A Series Turbofan Engines, 16754-16755 [E9-8263]
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16754
Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Rules and Regulations
disease. Entities that possessed the
select agents and toxins added in the
final rule and that had not been
registered were now required to register
under the select agent regulations.
To minimize the disruption of
research or educational projects (e.g.,
teaching demonstrations) involving
listed select agents or toxins, the final
rule provided any individual or entity
possessing newly added select agents or
toxins as of the effective date of the final
rule, November 17, 2008, with
additional time to reach full compliance
with the select agent regulations. The
responsible official at all entities that
possessed a new agent or toxin was
required to provide notice to APHIS
regarding their possession of the new
agent(s) and toxin(s) by November 17,
2008. The final rule also stated that, by
April 14, 2009, all previously
unregistered entities must be registered
and thus in compliance with the
regulations.2
Since the publication of the final rule,
some entities have notified us that they
use virulent Newcastle disease virus for
bird vaccines, in research on cancer
treatment in humans, and as a vector of
antigenic proteins that enhance immune
response to cancer and to diseases (e.g.,
influenza and avian influenza). This
notice informs the public that we are
extending the compliance date for
registration of entities that are newly
required to register to July 13, 2009, to
give us additional time to determine
how best to regulate those entities.
Authority: 7 U.S.C. 8401; 7 CFR 2.22, 2.80,
371.3, and 371.4.
Done in Washington, DC, this 8th day of
April 2009.
Kevin Shea,
Acting Administrator, Animal and Plant
Health Inspection Service.
[FR Doc. E9–8383 Filed 4–10–09; 8:45 am]
BILLING CODE 3410–34–P
2 The compliance date in the final rule was
originally published as April 14, 2008; it was
corrected to April 14, 2009, in a correction
published on October 27, 2008 (73 FR 63621).
VerDate Nov<24>2008
18:17 Apr 10, 2009
Jkt 217001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0827; Directorate
Identifier 2008–NE–26–AD; Amendment 39–
15879; AD 2009–08–06]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company (GE) CF6–80A Series
Turbofan Engines
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for GE
CF6–80A series turbofan engines with
certain stage 1 high-pressure turbine
(HPT) rotor disks, installed. This AD
requires removal from service of those
stage 1 HPT rotor disks within 30 days
after the effective date of the AD. This
AD results from the FAA learning that
those disks are susceptible to cracks
developing at the aft chamfer of the
blade dovetail slots. We are issuing this
AD to prevent cracks developing at the
aft chamfer of the blade dovetail slots
that could propagate to a failure of the
disk and cause an uncontained engine
failure and damage to the airplane.
DATES: This AD becomes effective May
18, 2009.
ADDRESSES: 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:
Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: robert.green@faa.gov;
telephone: (781) 238–7754, fax: (781)
238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to GE CF6–80A series turbofan
engines with certain stage 1 HPT rotor
disks, installed. We published the
proposed AD in the Federal Register on
September 4, 2008 (73 FR 51604). That
action proposed to require removal from
service of those stage 1 HPT rotor disks
within 30 days after the effective date of
the AD.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is provided in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment received.
Claim That Cost of Compliance Is
Underestimated
One commenter, FedEx Express,
claims that we greatly underestimated
the actual cost of compliance with the
proposed AD. The proposed AD
estimated 1 work-hour of labor. The
commenter states that this estimate is
accurate only when the engine is
already removed and disassembled to
piece-part exposure of the disk. The
commenter states that the true cost to an
airline, both in disruption to the
operation and in the subsequent
unplanned engine shop visit, would
vastly exceed 1 work-hour.
We agree that the cost of compliance
should also cover the work-hours for an
unplanned engine shop visit. We do not
agree that it should factor in the cost of
disruption to the operation. We are
required to calculate only the direct cost
to an operator, of labor and parts. We
changed the cost of compliance
paragraph to include an estimate for an
unplanned engine shop visit.
Clarification of Unsafe Condition
Statement
Since we issued the proposed AD, we
clarified the unsafe condition statement
as to where potential cracks could occur
in the disk. We changed ‘‘cracks
developing in the bottoms of the
dovetail slots’’ to ‘‘cracks developing at
the aft chamfer of the blade dovetail
slots.’’
Conclusion
We have carefully reviewed the
available data, including the comment
received, and determined that air safety
and the public interest require adopting
the AD 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.
E:\FR\FM\13APR1.SGM
13APR1
Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Rules and Regulations
Costs of Compliance
We estimate that this AD will affect 3
out of 316 CF6–80A series turbofan
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 if the engine is
already removed and disassembled to
piece-part exposure of the disk, and will
take about 115 work-hours per engine
for an unplanned engine shop visit. The
average labor rate is $80 per work-hour.
Required parts would cost about
$300,000 per engine. Based on these
figures, we estimate the total cost of the
AD to U.S. operators to be $927,600.
List of Subjects in 14 CFR Part 39
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.
§ 39.13
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.
VerDate Nov<24>2008
18:17 Apr 10, 2009
Jkt 217001
Air transportation, Aircraft, Aviation
safety, 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:
■
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.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2009–08–06 General Electric Company:
Amendment 39–15879. Docket No.
FAA–2008–0827; Directorate Identifier
2008–NE–26–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective May 18, 2009.
(b) None.
Applicability
(c) This AD applies to General Electric
Company (GE) CF6–80A series turbofan
engines with any of the following stage
1 high-pressure turbine (HPT) rotor disk
part numbers (P/Ns), installed:
(1) 1380M69G01; 1380M69G02;
1380M69G04; 1380M69G05; or
1380M69G06; or
(2) 9234M67G12; 9234M67G13;
9234M67G14; 9234M67G15; or
9234M67G16; or
(3) 9362M58G04; or
(4) 9367M45G01; 9367M45G03;
9367M45G05; 9367M45G06;
9367M45G07; or 9367M45G08.
(d) These CF6–80A series turbofan
engines are installed on, but not limited
to, Airbus A310–200 series and Boeing
767–200 and –300 series airplanes.
Unsafe Condition
(e) This AD results from the FAA
learning that those disks are susceptible
to cracks developing at the aft chamfer
of the blade dovetail slots. We are
issuing this AD to prevent cracks
developing at the aft chamfer of the
blade dovetail slots that could propagate
to a failure of the disk and cause an
uncontained engine failure and damage
to the airplane.
Compliance
(f) You are responsible for having the
actions required by this AD performed
Frm 00003
Fmt 4700
within 30 days after the effective date of
this AD, unless the actions have already
been done.
(g) Remove from service HPT stage 1
rotor disks identified by P/N in
paragraph (c) of this AD.
Prohibition of HPT Stage 1 Rotor Disks
(h) After the effective date of this AD,
do not install any of the HPT stage 1
rotor disks, listed by P/N in paragraph
(c) of this AD into any engine.
Alternative Methods of Compliance
(i) 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
(j) Contact Robert Green, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803; e-mail:
robert.green@faa.gov; telephone: (781)
238–7754, fax: (781) 238–7199, for more
information about this AD.
Material Incorporated by Reference
(k) None.
Affected ADs
PO 00000
16755
Sfmt 4700
Issued in Burlington, Massachusetts, on
April 6, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E9–8263 Filed 4–10–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1207; Directorate
Identifier 2007–NE–47–AD; Amendment 39–
15880; AD 2009–08–07]
RIN 2120–AA64
Airworthiness Directives; Honeywell
International Inc. ALF502L–2 and
ALF502L–2C Turbofan Engines
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for
Honeywell International Inc. ALF502L–
2 and ALF502L–2C turbofan engines
with certain high-pressure compressor
(HPC) first stage discs installed. This AD
requires performing a dimensional
inspection to determine if excessive disc
balance material was removed and a
magnetic particle inspection if the disc
E:\FR\FM\13APR1.SGM
13APR1
Agencies
[Federal Register Volume 74, Number 69 (Monday, April 13, 2009)]
[Rules and Regulations]
[Pages 16754-16755]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-8263]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0827; Directorate Identifier 2008-NE-26-AD;
Amendment 39-15879; AD 2009-08-06]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF6-80A
Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE
CF6-80A series turbofan engines with certain stage 1 high-pressure
turbine (HPT) rotor disks, installed. This AD requires removal from
service of those stage 1 HPT rotor disks within 30 days after the
effective date of the AD. This AD results from the FAA learning that
those disks are susceptible to cracks developing at the aft chamfer of
the blade dovetail slots. We are issuing this AD to prevent cracks
developing at the aft chamfer of the blade dovetail slots that could
propagate to a failure of the disk and cause an uncontained engine
failure and damage to the airplane.
DATES: This AD becomes effective May 18, 2009.
ADDRESSES: 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: Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
robert.green@faa.gov; telephone: (781) 238-7754, fax: (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to GE CF6-80A series
turbofan engines with certain stage 1 HPT rotor disks, installed. We
published the proposed AD in the Federal Register on September 4, 2008
(73 FR 51604). That action proposed to require removal from service of
those stage 1 HPT rotor disks within 30 days after the effective date
of the AD.
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 comment received.
Claim That Cost of Compliance Is Underestimated
One commenter, FedEx Express, claims that we greatly underestimated
the actual cost of compliance with the proposed AD. The proposed AD
estimated 1 work-hour of labor. The commenter states that this estimate
is accurate only when the engine is already removed and disassembled to
piece-part exposure of the disk. The commenter states that the true
cost to an airline, both in disruption to the operation and in the
subsequent unplanned engine shop visit, would vastly exceed 1 work-
hour.
We agree that the cost of compliance should also cover the work-
hours for an unplanned engine shop visit. We do not agree that it
should factor in the cost of disruption to the operation. We are
required to calculate only the direct cost to an operator, of labor and
parts. We changed the cost of compliance paragraph to include an
estimate for an unplanned engine shop visit.
Clarification of Unsafe Condition Statement
Since we issued the proposed AD, we clarified the unsafe condition
statement as to where potential cracks could occur in the disk. We
changed ``cracks developing in the bottoms of the dovetail slots'' to
``cracks developing at the aft chamfer of the blade dovetail slots.''
Conclusion
We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD 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.
[[Page 16755]]
Costs of Compliance
We estimate that this AD will affect 3 out of 316 CF6-80A series
turbofan 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 if the engine is already removed and disassembled to piece-part
exposure of the disk, and will take about 115 work-hours per engine for
an unplanned engine shop visit. The average labor rate is $80 per work-
hour. Required parts would cost about $300,000 per engine. Based on
these figures, we estimate the total cost of the AD to U.S. operators
to be $927,600.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2009-08-06 General Electric Company: Amendment 39-15879. Docket No.
FAA-2008-0827; Directorate Identifier 2008-NE-26-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 18,
2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric Company (GE) CF6-80A series
turbofan engines with any of the following stage 1 high-pressure
turbine (HPT) rotor disk part numbers (P/Ns), installed:
(1) 1380M69G01; 1380M69G02; 1380M69G04; 1380M69G05; or 1380M69G06;
or
(2) 9234M67G12; 9234M67G13; 9234M67G14; 9234M67G15; or 9234M67G16;
or
(3) 9362M58G04; or
(4) 9367M45G01; 9367M45G03; 9367M45G05; 9367M45G06; 9367M45G07; or
9367M45G08.
(d) These CF6-80A series turbofan engines are installed on, but not
limited to, Airbus A310-200 series and Boeing 767-200 and -300 series
airplanes.
Unsafe Condition
(e) This AD results from the FAA learning that those disks are
susceptible to cracks developing at the aft chamfer of the blade
dovetail slots. We are issuing this AD to prevent cracks developing at
the aft chamfer of the blade dovetail slots that could propagate to a
failure of the disk and cause an uncontained engine failure and damage
to the airplane.
Compliance
(f) You are responsible for having the actions required by this AD
performed within 30 days after the effective date of this AD, unless
the actions have already been done.
(g) Remove from service HPT stage 1 rotor disks identified by P/N
in paragraph (c) of this AD.
Prohibition of HPT Stage 1 Rotor Disks
(h) After the effective date of this AD, do not install any of the
HPT stage 1 rotor disks, listed by P/N in paragraph (c) of this AD into
any engine.
Alternative Methods of Compliance
(i) 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
(j) Contact Robert Green, Aerospace Engineer, Engine Certification
Office, FAA, Engine and Propeller Directorate, 12 New England Executive
Park, Burlington, MA 01803; e-mail: robert.green@faa.gov; telephone:
(781) 238-7754, fax: (781) 238-7199, for more information about this
AD.
Material Incorporated by Reference
(k) None.
Issued in Burlington, Massachusetts, on April 6, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E9-8263 Filed 4-10-09; 8:45 am]
BILLING CODE 4910-13-P