Airworthiness Directives; General Electric Co. (GE) CF34-8E Series Turbofan Engines, 44628-44630 [E8-17422]
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yshivers on PROD1PC62 with RULES
44628
Federal Register / Vol. 73, No. 148 / Thursday, July 31, 2008 / Rules and Regulations
data, information, and judgment used in
its quantitative and qualitative
approaches.
42. The ICAAP should be enhanced
and refined over time, with learning and
experience (both quantitative and
qualitative) contributing to its
improvement. The ICAAP should evolve
with changes in the risk profile and
activities of the bank, as well as with
advances in risk measurement and
management practices. For example, a
bank should incorporate in its ICAAP
the introduction of new products and
business lines and activities to ensure
that the bank’s capital plan is
responsive to changes in the operational
and/or business environment.
43. The board of directors and senior
management have certain
responsibilities in developing,
implementing, and overseeing the
ICAAP. The board should approve the
ICAAP and its components. The board
or its appropriately delegated agent
should review the ICAAP and its
components on a regular basis, and
approve any revisions. That review
should encompass the effectiveness of
the ICAAP, the appropriateness of risk
tolerance levels and capital planning,
and the strength of control
infrastructures. Senior management
should continually ensure that the
ICAAP is functioning effectively and as
intended, under a formal review policy
that is explicit and well documented.
Additionally, a bank’s internal audit
function should play a key role in
reviewing the controls and governance
surrounding the ICAAP on an ongoing
basis.
44. Each bank should ensure that the
components of its ICAAP, including any
models and their inputs, are subject to
the bank’s validation policies and
procedures. Validation should be
independent of the development,
implementation, and operation of the
ICAAP components, or the validation
process should be subject to an
independent review of its adequacy and
effectiveness. Validation is generally
defined as an ongoing process that
includes, but is not limited to, the
collection and review of developmental
evidence, process verification,
benchmarking, outcomes analysis, and
monitoring activities used to confirm
that processes are operating as designed.
Validation policies and procedures
should reflect the bank’s business,
structure, and sophistication, as well as
the relative importance of each
component of the ICAAP. Accordingly,
a bank is encouraged to consult the
agencies’ existing guidance on
validation.
VerDate Aug<31>2005
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45. A bank’s ICAAP should be aligned
with and be a part of the bank’s wider
internal governance structure and
overall risk-management processes. The
ICAAP should not be viewed as simply
a compliance exercise. Rather, it is a
dynamic and evolving process that is
used by a bank to provide internal
assurance that capital is adequate given
the bank’s risk profile. Management is
responsible for ensuring that the ICAAP
is fully consistent with the overall risk
management framework of the bank.
Information derived through the ICAAP
process should influence decision
making at both the consolidated and
individual business-line levels, and be
used to inform other management
processes related to risk assessment,
business planning and forecasting,
pricing strategies, and performance
measurement.
46. As part of the ICAAP, the board
or its delegated agent, as well as
appropriate senior management, should
periodically review the resulting
assessment of overall capital adequacy.
This review, which should occur at least
annually, should include an analysis of
how measures of internal capital
adequacy compare with other capital
measures (such as regulatory,
accounting-based or marketdetermined). Upon completion of this
review, the board or its delegated agent
should determine that, consistent with
safety and soundness, the bank’s capital
takes into account all material risks and
is appropriate for its risk profile.
However, in the event a capital
deficiency is uncovered (that is, if
capital is not consistent with the bank’s
risk profile or risk tolerance)
management should consult and adhere
to formal procedures to correct the
capital deficiency.
Dated: July 14, 2008.
John C. Dugan,
Comptroller of the Currency.
By order of the Board of Governors of the
Federal Reserve System, July 15, 2008.
Jennifer J. Johnson,
Secretary of the Board.
Dated at Washington, DC, the 15th day of
July, 2008.
By order of the Federal Deposit Insurance
Corporation.
Robert E. Feldman,
Executive Secretary.
Dated: July 14, 2008.
By the Office of Thrift Supervision.
John M. Reich,
Director.
[FR Doc. E8–17555 Filed 7–30–08; 8:45 am]
BILLING CODE 4810–33–P, 6210–01–P, 6714–01–P,
6720–01–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0821; Directorate
Identifier 2008–NE–20–AD; Amendment 39–
15619; AD 2008–16–01]
RIN 2120–AA64
Airworthiness Directives; General
Electric Co. (GE) CF34–8E Series
Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for GE
CF34–8E series turbofan engines with
certain part number (P/N) full authority
digital engine controls (FADECs)
installed. This AD requires
reprogramming the FADEC software
from version 8Ev5.40 to an FAAapproved software version. This AD
results from six loss of thrust control
events from the same software fault
scenario. We are issuing this AD to
prevent loss of thrust control and
controllability of the airplane.
DATES: This AD becomes effective
August 15, 2008.
We must receive any comments on
this AD by September 29, 2008.
ADDRESSES: Use one of the following
addresses to comment on this AD:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the instructions for sending your
comments electronically.
• Mail: U.S. Docket Management
Facility, Department of Transportation,
1200 New Jersey Avenue, SE., West
Building Ground Floor, Room W12–140,
Washington, DC 20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: (202) 493–2251.
Contact General Electric Company via
Lockheed Martin Technology Services,
10525 Chester Road, Suite C, Cincinnati,
Ohio 45215; telephone (513) 672–8400;
fax (513) 672–8422, for the service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Kenneth Steeves, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
e-mail: kenneth.steeves@faa.gov;
telephone (781) 238–7765; fax (781)
238–7199.
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31JYR1
Federal Register / Vol. 73, No. 148 / Thursday, July 31, 2008 / Rules and Regulations
We have
received reports of six events on CF34–
8E turbofan engines that resulted in loss
of thrust control. On March 2, 2008, the
No. 1 engine on an ERJ 170 experienced
a fluctuation of the interstage turbine
temperature during decent that resulted
in changes in thrust. The crew shut
down the engine. On May 12, 2008, an
ERJ 170 was at cruise when the ENG 2
Control Fault posted to the Engine
Indicating and Crew Alerting System
(EICAS) display. The FADEC software
commanded the number two engine to
idle and there was no response to
throttle movement by the crew. The
crew shut down the engine. Four more
similar events occurred on May 29, June
10, June 14, and July 10, 2008, all
resulting in loss of thrust control with
an ENG 1 or 2 Control Fault message
posted to the EICAS. Our investigation
revealed that all events resulted from
the same software fault scenario. We
attribute the fault to FADEC software
version 8Ev5.40. This condition, if not
corrected, could result in loss of thrust
control and controllability of the
airplane.
SUPPLEMENTARY INFORMATION:
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other GE CF34–8E series turbofan
engines of the same type design. For
that reason, we are issuing this AD to
prevent loss of thrust control and
controllability of the airplane.
FAA’s Determination of the Effective
Date
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we have found that notice and
opportunity for public comment before
issuing this AD are impracticable, and
that good cause exists for making this
amendment effective in less than 30
days.
yshivers on PROD1PC62 with RULES
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to send us any
written relevant data, views, or
arguments regarding this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
FAA–2008–0821; Directorate Identifier
2008–NE–20–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the rule that might suggest a
need to modify it.
VerDate Aug<31>2005
15:05 Jul 30, 2008
Jkt 214001
44629
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of the Web site, anyone
can find and read the comments in any
of our dockets, including, if provided,
the name of the individual who sent the
comment (or signed the comment on
behalf of an association, business, labor
union, etc.). You may review the DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
2000 (65 FR 19477–78).
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 the
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.
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 the same as the Mail
address provided in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
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.
Authority: 49 U.S.C. 106(g), 40113, 44701.
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.
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Adoption of the Amendment
Under the authority delegated to me
by the Administrator, the Federal
Aviation Administration amends part 39
of the Federal Aviation Regulations (14
CFR part 39) as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
I
2008–16–01 General Electric Co.:
Amendment 39–15619. Docket No.
FAA–2008–0821; Directorate Identifier
2008–NE–20–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective August 15, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric Co.
(GE) CF34–8E series turbofan engines with
full authority digital electronic controls
(FADECs), part numbers (P/N) 4120T00P47,
4120T00P48, 111E9320G48, or
111E9320G49, installed. These engines are
installed on, but not limited to, Empresa
Brasileira de Aeronautica S.A. (EMBRAER)
ERJ 170 series airplanes.
Unsafe Condition
(d) This AD results from six loss of thrust
control events from the same software fault
scenario. We are issuing this AD to prevent
loss of thrust control and controllability of
the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
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Federal Register / Vol. 73, No. 148 / Thursday, July 31, 2008 / Rules and Regulations
660 flight hours time-in-service after the
effective date of this AD, unless the actions
have already been done.
Removal of CF34–8E FADEC Software
Version 8Ev5.40
Installation Prohibition
(g) After the effective date of this AD, don’t
install any FADEC, P/N 4120T00P47,
4120T00P48, 111E9320G48, or
111E9320G49, onto any CF34–8E engine.
Alternative Methods of Compliance
(h) 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
(i) General Electric Alert Service Bulletin
CF34–8E–AL S/B 73–A0019, dated June 17,
2008, contains information on removing
software version 8Ev5.40 and installing an
FAA-approved FADEC software version.
(j) Contact Kenneth Steeves, Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: kenneth.steeves@faa.gov;
telephone (781) 238–7765; fax (781) 238–
7199, for more information about this AD.
Material Incorporated by Reference
(k) None.
Issued in Burlington, Massachusetts, on
July 23, 2008.
Carlos Pestana,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E8–17422 Filed 7–30–08; 8:45 am]
yshivers on PROD1PC62 with RULES
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15:05 Jul 30, 2008
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Federal Aviation Administration
14 CFR Part 39
(f) For CF34–8E engines with a FADEC, P/
N 4120T00P47, 4120T00P48, 111E9320G48,
or 111E9320G49, installed, do either of the
following:
(1) Replace the FADEC, P/N 4120T00P47,
4120T00P48, 111E9320G48, or
111E9320G49, with a FADEC P/N not listed
in paragraph (c) of this AD. Or,
(2) For CF34–8E engines with a FADEC, P/
N 4120T00P47, 4120T00P48, 111E9320G48,
or 111E9320G49, installed, reprogram the
FADEC software to an FAA approved
version.
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
[Docket No. FAA–2006–24825; Directorate
Identifier 2006–NE–17–AD; Amendment 39–
15623; AD 2008–16–05]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Deutschland Ltd & Co KG (RRD) Dart
528, 529, 532, 535, 542, and 552 Series
Turboprop Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
RRD Dart 528, 529, 532, 535, 542, and
552 Series turboprop engines. That AD
currently requires a dimensional
inspection of the intermediate pressure
turbine (IPT) disk or an ultrasonic
inspection of the seal arm contact
between the high pressure turbine (HPT)
and the IPT disk seal arm and reworking
or replacing the IPT disk if worn beyond
acceptable limits. This AD continues to
require those actions. This AD results
from us including an incorrect engine
model and omitting an engine model
from the applicability of the existing
AD. We are issuing this AD to prevent
HPT disk failure, which can result in an
uncontained engine failure and damage
to the airplane.
DATES: This AD becomes effective
September 4, 2008. The Director of the
Federal Register previously approved
the incorporation by reference of certain
publications listed in the regulations on
February 26, 2007 (72 FR 2610, January
22, 2007).
ADDRESSES: You can get the service
information identified in this AD from
Rolls-Royce Deutschland Ltd & Co KG,
Eschenweg 11, D–15827 Dahlewitz,
Germany; telephone 49 (0) 33–7086–
1768; fax 49 (0) 33–7086–3356.
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:
Jason Yang, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
telephone (781) 238–7747; fax (781)
238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 by
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superseding AD 2007–02–07,
Amendment 39–14894 (72 FR 2610,
January 22, 2007), with a proposed AD.
The proposed AD applies to RRD Dart
528, 529, 532, 535, 542, and 552 Series
turboprop engines. We published the
proposed AD in the Federal Register on
November 9, 2007 (72 FR 63508). That
action proposed to require deleting the
Dart 555 series engines from the
applicability paragraph of the proposed
AD, and to list the Dart 552 series
turboprop engines in the applicability
paragraph of the proposed 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 comments received.
Request To Correct a Typographical
Error in the Costs of Compliance
Section
One commenter asks us to change
‘‘turbofan engines’’ in the Costs of
Compliance Section to ‘‘turboprop
engines.’’ The commenter states that the
Dart engine is a turboprop engine, not
a ‘‘turbofan engines.’’
We agree. We changed ‘‘turbofan
engines’’ in the Costs to Comply section
to ‘‘turboprop engines.’’
Request To Add Airplane Models to the
Applicability Paragraph
The same commenter states that
paragraph (c) Applicability, appears to
omit some models of airplanes that
might use the engines. The commenter
states that the Dart engine is installed by
supplemental type certificate on certain
General Dynamics Convair model
airplanes, and that those airplanes can
still be found in the FAA’s registry
database.
We partially agree. We must identify
in paragraph (c) Applicability, all
engine models that are affected by this
AD. We list the aircraft models that
might use those engines to help readers
to determine if they might have an
affected engine. However, for clarity, we
E:\FR\FM\31JYR1.SGM
31JYR1
Agencies
[Federal Register Volume 73, Number 148 (Thursday, July 31, 2008)]
[Rules and Regulations]
[Pages 44628-44630]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-17422]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0821; Directorate Identifier 2008-NE-20-AD;
Amendment 39-15619; AD 2008-16-01]
RIN 2120-AA64
Airworthiness Directives; General Electric Co. (GE) CF34-8E
Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE
CF34-8E series turbofan engines with certain part number (P/N) full
authority digital engine controls (FADECs) installed. This AD requires
reprogramming the FADEC software from version 8Ev5.40 to an FAA-
approved software version. This AD results from six loss of thrust
control events from the same software fault scenario. We are issuing
this AD to prevent loss of thrust control and controllability of the
airplane.
DATES: This AD becomes effective August 15, 2008.
We must receive any comments on this AD by September 29, 2008.
ADDRESSES: Use one of the following addresses to comment on this AD:
Federal eRulemaking Portal: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: U.S. Docket Management Facility, Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground
Floor, Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
Contact General Electric Company via Lockheed Martin Technology
Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215;
telephone (513) 672-8400; fax (513) 672-8422, for the service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Kenneth Steeves, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
kenneth.steeves@faa.gov; telephone (781) 238-7765; fax (781) 238-7199.
[[Page 44629]]
SUPPLEMENTARY INFORMATION: We have received reports of six events on
CF34-8E turbofan engines that resulted in loss of thrust control. On
March 2, 2008, the No. 1 engine on an ERJ 170 experienced a fluctuation
of the interstage turbine temperature during decent that resulted in
changes in thrust. The crew shut down the engine. On May 12, 2008, an
ERJ 170 was at cruise when the ENG 2 Control Fault posted to the Engine
Indicating and Crew Alerting System (EICAS) display. The FADEC software
commanded the number two engine to idle and there was no response to
throttle movement by the crew. The crew shut down the engine. Four more
similar events occurred on May 29, June 10, June 14, and July 10, 2008,
all resulting in loss of thrust control with an ENG 1 or 2 Control
Fault message posted to the EICAS. Our investigation revealed that all
events resulted from the same software fault scenario. We attribute the
fault to FADEC software version 8Ev5.40. This condition, if not
corrected, could result in loss of thrust control and controllability
of the airplane.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other GE CF34-8E series turbofan engines of the same type
design. For that reason, we are issuing this AD to prevent loss of
thrust control and controllability of the airplane.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are impracticable, and that good
cause exists for making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to send us any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. FAA-2008-0821;
Directorate Identifier 2008-NE-20-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this AD. Using the search function of the
Web site, anyone can find and read the comments in any of our dockets,
including, if provided, the name of the individual who sent the comment
(or signed the comment on behalf of an association, business, labor
union, etc.). You may review the DOT's complete Privacy Act Statement
in the Federal Register published on April 11, 2000 (65 FR 19477-78).
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 the same as
the Mail address provided in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
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 the 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
Under the authority delegated to me by the Administrator, the Federal
Aviation Administration amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2008-16-01 General Electric Co.: Amendment 39-15619. Docket No. FAA-
2008-0821; Directorate Identifier 2008-NE-20-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective August
15, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric Co. (GE) CF34-8E series
turbofan engines with full authority digital electronic controls
(FADECs), part numbers (P/N) 4120T00P47, 4120T00P48, 111E9320G48, or
111E9320G49, installed. These engines are installed on, but not
limited to, Empresa Brasileira de Aeronautica S.A. (EMBRAER) ERJ 170
series airplanes.
Unsafe Condition
(d) This AD results from six loss of thrust control events from
the same software fault scenario. We are issuing this AD to prevent
loss of thrust control and controllability of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within
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660 flight hours time-in-service after the effective date of this
AD, unless the actions have already been done.
Removal of CF34-8E FADEC Software Version 8Ev5.40
(f) For CF34-8E engines with a FADEC, P/N 4120T00P47,
4120T00P48, 111E9320G48, or 111E9320G49, installed, do either of the
following:
(1) Replace the FADEC, P/N 4120T00P47, 4120T00P48, 111E9320G48,
or 111E9320G49, with a FADEC P/N not listed in paragraph (c) of this
AD. Or,
(2) For CF34-8E engines with a FADEC, P/N 4120T00P47,
4120T00P48, 111E9320G48, or 111E9320G49, installed, reprogram the
FADEC software to an FAA approved version.
Installation Prohibition
(g) After the effective date of this AD, don't install any
FADEC, P/N 4120T00P47, 4120T00P48, 111E9320G48, or 111E9320G49, onto
any CF34-8E engine.
Alternative Methods of Compliance
(h) 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
(i) General Electric Alert Service Bulletin CF34-8E-AL S/B 73-
A0019, dated June 17, 2008, contains information on removing
software version 8Ev5.40 and installing an FAA-approved FADEC
software version.
(j) Contact Kenneth Steeves, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
kenneth.steeves@faa.gov; telephone (781) 238-7765; fax (781) 238-
7199, for more information about this AD.
Material Incorporated by Reference
(k) None.
Issued in Burlington, Massachusetts, on July 23, 2008.
Carlos Pestana,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-17422 Filed 7-30-08; 8:45 am]
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