[Federal Register: September 8, 2005 (Volume 70, Number 173)]
[Rules and Regulations]
[Page 53295-53296]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08se05-1]
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Rules and Regulations
Federal Register
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[[Page 53295]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18869; Directorate Identifier 2004-NE-23-AD;
Amendment 39-14256; AD 2005-18-16]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF34-3A1
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
General Electric Company (GE) CF34-3A1 turbofan engines installed on
Bombardier series Regional Jets with certain high pressure turbine
(HPT) rotating components installed. This AD requires removal from
service of certain HPT components prior to the parts exceeding their
designated life limits. This AD results from the discovery that the
manufacturer removed certain part numbers of HPT rotating components
from the Life Limits section of the CF34 Engine Manual, SEI-756. The
effect of this manual change was the removal of life limits from
certain components that are eligible for installation in GE CF34-3A1
engines. We are issuing this AD to impose life limits on these HPT
rotating components to prevent low cycle fatigue (LCF) cracking and
failure of those components, which could result in uncontained engine
failure and damage to the airplane.
DATES: This AD becomes effective October 13, 2005.
ADDRESSES: You may examine the AD docket on the Internet at http://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: Robert Grant, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7757; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed airworthiness directive. The proposed AD applies to GE
CF34-3A1 turbofan engines with certain HPT rotating components
installed. We published the proposed AD in the Federal Register on
August 16, 2004 (69 FR 50344). That action proposed a requirement for
removal from service of certain HPT components prior to their exceeding
designated life limits.
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 Docket Offices 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.
Identify Affected Engines
One commenter states that the AD should identify the specific
engines to which it applies or identify the applicable engines by the
maintenance manual used. We agree that applicability should be
clarified. We have reworded the AD to indicate that it applies only to
CF34-3A1 engines installed on Bombardier series Regional Jet Model CL-
600-2B19 (Regional Jet Series 100 and 440) airplanes with one or more
of certain HPT rotating components installed.
Challenger Aircraft Not Affected
Another commenter states that a note should be added to the AD
indicating that this AD does not apply to CF34-3A1 engines installed on
Challenger aircraft. We agree. We have clarified this AD to indicate
that it applies only to engines installed on Bombardier series Regional
Jet Model CL-600-2B19 (Regional Jet Series 100 and 440) airplanes with
one or more of certain HPT rotating components installed.
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 would affect eight CF34-3A1 turbofan
engines installed on airplanes of U.S. registry. We estimate that no
affected engine has a listed HPT rotating component near its original
type design life limit. Therefore, we estimate that this AD will not
result in any additional direct labor or part costs.
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
[[Page 53296]]
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:
2005-18-16 General Electric Company: Amendment 39-14256. Docket No.
FAA-2004-18869; Directorate Identifier 2004-NE-23-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October
13, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric CF34-3A1 turbofan
engines installed on Bombardier series Regional Jet Model CL-600-
2B19 (Regional Jet Series 100 and 440) airplanes with one or more of
the HPT rotating components installed, listed in the following Table
1:
Table 1.--HPT Rotating Components With Life Limits Restored
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Part No. Nomenclature
------------------------------------------------------------------------
6078T90P01............................. Seal, Balance Piston Air.
6017T00P05............................. Shaft, HPT Rotor.
4027T15P03............................. Plate, Stage 1 Front Cooling.
6078T93P01............................. Disk, Stage 1 Turbine.
6078T93P02............................. Disk, Stage 1 Turbine.
5041T70P03............................. Plate, Stage 1 Aft Cooling.
5023T97P03............................. Plate, Stage 2 Rear Cooling.
6078T94P01............................. Disk, Stage 2 Turbine.
6078T94P02............................. Disk, Stage 2 Turbine.
5042T29P02............................. Plate, Stage 2 Front Cooling.
5041T67P02............................. Coupling, Outer Torque.
5079T02P01............................. Coupling, Inner Torque.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from the discovery that the manufacturer
removed the HPT rotating component part numbers, listed in Table 1
of this AD, from the HPT Life Limits section of the CF34 Engine
Manual, SEI-756. We view this as a change to the life limit of the
part, removing the type design life limit and imposing an unlimited
life on the part. We are issuing this AD to re-impose life limits on
the HPT rotating components with part numbers listed in Table 1 of
this AD to prevent LCF cracking and failure of those components,
which could result in uncontained engine failure and damage to the
airplane.
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) Remove from service the HPT rotating components listed in
Table 1 of this AD before exceeding the life limit of 6,000 cycles-
since-new.
Alternative Methods of Compliance
(g) 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
(h) GE Temporary Revision No. 05-0073, and Temporary Revision
No. 05-0074, for CF34 Engine Manual, SEI-756, also pertain to the
subject of this AD.
Issued in Burlington, Massachusetts, on August 31, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-17761 Filed 9-7-05; 8:45 am]
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