Airworthiness Directives; Rolls-Royce Corporation (RRC) (formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) Models 250-C28, -C28B, and -C28C Turboshaft Engines, 57487-57491 [05-19693]
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Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations
Inspection Service (APHIS) will conduct its
own tests during quarantine.
Two commenters said that the new
cancellation policy unnecessarily
penalizes those who reserve stall space
early and are then required to make
legitimate alterations to their bookings.
The commenters asked that we consider
implementing a small administrative fee
for changes made more than 30 days
prior to the reservation date.
The purpose of the interim rule was
to discourage horse brokers from making
several reservations and simply
forfeiting the $40 cancellation fees if a
client is not found to fill those reserved
spaces. This situation had led some
brokers to complain that the potential
loss of a $40 cancellation fee is not an
effective deterrent to prevent brokers
from reserving stall space before a client
is found. Since the publication of our
December 2002 interim rule, the
problem of late cancellations has been
eliminated. We believe that instituting
the suggested small fee for canceled
reservations would result in a situation
similar to the one that existed prior to
publication of the interim rule.
All three commenters stated that a
policy should be enacted wherein stall
space in a horse quarantine facility may
be formally transferred from one party
to another within 15 days of arrival.
Shipments arriving at quarantine
facilities are comprised of horses from
several different brokers. As such, the
suggested formal transfer policy would
require a continual monitoring policy,
along with the accompanying
paperwork. Such an approach
potentially involves a great amount of
time, personnel, and expense for all
affected parties. As such, this method is
not cost effective, nor would it eliminate
the practice of speculative reservation.
Two commenters said that the grace
period within which shipments may
arrive without incurring cancellation
fees should be extended from 24 to 48
hours.
Under the regulations in effect prior
to the December 2002 interim rule, we
required 5 business days’ notice for
cancellations in order for importers to
avoid forfeiture of the total reservation
fee. As a result of the interim rule, we,
among other things, established a
graduated fee schedule for
cancellations. Importers or their agents
are now required to present for entry,
within 24 hours following the
designated time of arrival, the horse for
which the reservation was made. In our
opinion, increasing the time period
within which importers must present
their horses would lead to a
reintroduction of past speculative
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reservation practices. The regulations in
§ 93.304(a)(3)(iv) provide for the return
of reservation fees to importers in
certain cases when unforseen
circumstances arise that prevent an
importer from presenting a horse for
entry within the required time period.
One commenter said that the
forfeiture amounts as established in the
graduated fee schedule set for
cancellations are too high.
Prior to publication of the interim
rule, we carefully considered a fee
schedule that we thought to be
appropriate and effective in eliminating
the practice of speculative reservations.
The USDA quarantine facilities in
Florida and New York each lost
approximately $300,000 to $470,000
yearly in forgone user fees. While we
recognize that increasing cancellation
fees and the time period required for
cancellation affects both horse owners
and brokers, the forfeiture amounts
must necessarily be set at a level that
will serve as a meaningful deterrent to
speculative reservation-making and
allow APHIS to recover the fixed cost
associated with operating quarantine
facilities when stall space goes unused.
Two commenters stated that there is
a need to specifically create a set of
circumstances under which a full
refund of the reservation fee would be
granted, suggesting that a refund would
be appropriate in cases where an airline
cancels a flight or a horse is injured
during loading.
The regulations already describe the
circumstances under which a full
refund may be granted. As stated
previously, under the regulations at
§ 93.304(a)(3)(iv), a reservation fee will
not be forfeited if the Administrator
determines that certain essential
services were not available at the
necessary time as a result of unforseen
circumstances. These circumstances
include, but are not limited to, the
closing of an airport due to inclement
weather or the unavailability of the
reserved space due to the extension of
another quarantine. We believe it is
appropriate and necessary to limit
refunds to the circumstances relating to
services, other than those provided by
carriers, necessary for the importation of
the horses within the required period
that are unavailable because of
unforeseen circumstances as determined
by the Administrator.
Likewise, the issuance of refunds, as
may be necessary in the situations
described above, is based somewhat on
the Administrator’s discretion. As such,
we believe that any attempt to list all
instances where a refund would be
granted would unnecessarily limit the
Administrator’s ability to make
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57487
determinations in a wide variety of
circumstances. It is necessary to leave
the exception as written in order to
preserve the flexibility of the
regulations.
Therefore, for the reasons given in the
interim rule and in this document, we
are adopting the interim rule as a final
rule without change.
This action also affirms the
information contained in the interim
rule concerning Executive Order 12866
and the Regulatory Flexibility Act,
Executive Order 12988, and the
Paperwork Reduction Act.
Further, this action has been
determined to be not significant for the
purposes of Executive Order 12866 and,
therefore, has not been reviewed by the
Office of Management and Budget.
List of Subjects in 9 CFR Part 93
Animal diseases, Imports, Livestock,
Poultry and poultry products,
Quarantine, Reporting and
recordkeeping requirements.
PART 93—IMPORTATION OF CERTAIN
ANIMALS, BIRDS, AND POULTRY,
AND CERTAIN ANIMAL, BIRD, AND
POULTRY PRODUCTS;
REQUIREMENTS FOR MEANS OF
CONVEYANCE AND SHIPPING
CONTAINERS
Accordingly, we are adopting as a
final rule, without change, the interim
rule that amended 9 CFR part 93 and
that was published at 67 FR 72827–
72830 on December 9, 2002.
I
Done in Washington, DC, this 27th day of
September 2005.
Elizabeth E. Gaston,
Acting Administrator, Animal and Plant
Health Inspection Service.
[FR Doc. 05–19689 Filed 9–30–05; 8:45 am]
BILLING CODE 3410–34–U
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22534; Directorate
Identifier 2005–NE–27–AD; Amendment 39–
14305; AD 2005–20–11]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Corporation (RRC) (formerly Allison
Engine Company, Allison Gas Turbine
Division, and Detroit Diesel Allison)
Models 250–C28, –C28B, and –C28C
Turboshaft Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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03OCR1
57488
Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations
Final rule; request for
comments.
ACTION:
The FAA is adopting a new
airworthiness directive (AD) for RollsRoyce Corporation (formerly Allison
Engine Company, Allison Gas Turbine
Division, and Detroit Diesel Allison)
(RRC) Models 250–C28, –C28B, and
–C28C turboshaft engines. This AD
requires a onetime visual inspection of
the seal joint in each passage between
airfoils at the hub and shroud of thirdstage turbine wheels, part number (P/N)
6899383. This AD results from reports
of three failed third-stage turbine wheels
and from the manufacturer’s analysis of
those failures. We are issuing this AD to
prevent loss of power and
uncommanded engine shutdown due to
failure of the third-stage turbine wheel.
DATES: This AD becomes effective
October 18, 2005.
We must receive any comments on
this AD by December 2, 2005.
ADDRESSES: Use one of the following
addresses to comment on this AD:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Rolls-Royce Corporation, PO
Box 420, Indianapolis, IN 46206–0420;
telephone (317) 230–6400; fax (317)
230–4243 for the service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT: John
Tallarovic, Aerospace Engineer, Chicago
Aircraft Certification Office, FAA, 2300
East Devon Avenue, Des Plaines, IL
60018–4696; telephone (847) 294–8180;
fax (847) 294–7834.
SUPPLEMENTARY INFORMATION: In April
2005, we became aware of reports of
three failed third-stage turbine wheels,
P/N 6899383. The third-stage turbine
wheels had partial loss of the blades and
shroud. RRC conducted an analysis and
found the failures were caused by
compromised third-stage blade fillet
radii, which led to increased stresses to
the third-stage blades and shroud. RRC
categorized this finding as a
SUMMARY:
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14:53 Sep 30, 2005
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manufacturer’s quality control problem.
This condition, if not corrected, could
result in loss of power and
uncommanded engine shutdown due to
failure of the third-stage turbine wheel.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other RRC Models 250–C28, –C28B,
and –C28C turboshaft engines of the
same type design. For that reason, we
are issuing this AD to prevent loss of
power and uncommanded engine
shutdown due to failure of the thirdstage turbine wheel. This AD requires a
onetime visual inspection of the seal
joint in each passage between airfoils at
the hub and shroud of third-stage
turbine wheels, P/N 6899383.
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–2005–22534; Directorate Identifier
2005–NE–27–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://
dms.dot.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 Docket
Management System (DMS) Web site,
anyone can find and read the comments
in any of our dockets, including 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) or you may visit
https://dms.dot.gov.
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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.
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 the regulation:
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.
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Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations
Detroit Diesel Allison): Amendment 39–
14305. Docket No. FAA–2005–22534;
Directorate Identifier 2005–NE–27–AD.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
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:
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 adding
the following new airworthiness
directive:
I
2005–20–11 Rolls-Royce Corporation
(formerly Allison Engine Company,
Allison Gas Turbine Division, and
VerDate Aug<31>2005
14:53 Sep 30, 2005
Jkt 208001
Effective Date
(a) This airworthiness directive (AD)
becomes effective October 18, 2005.
Affected ADs
Applicability
(c) This AD applies to Rolls-Royce
Corporation (RRC) (formerly Allison Engine
Company, Allison Gas Turbine Division, and
Detroit Diesel Allison) models 250–C28,
–C28B, and –C28C turboshaft engines. These
engines are installed on, but not limited to,
Bell Helicopter Textron 206L–1; Eurocopter
Deutschland BO 105 LS A–1; and Eurocopter
Canada BO 105 LS A–3 helicopters.
Unsafe Condition
(d) This AD results from reports of three
failed third-stage turbine wheels and from
the manufacturer’s analysis of those failures.
We are issuing this AD to prevent loss of
power and uncommanded engine shutdown
Frm 00007
due to failure of the third-stage turbine
wheel.
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.
Onetime Visual Inspection
(b) None.
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Fmt 4700
Sfmt 4700
(f) For third-stage turbine wheels, part
number (P/N) 6899383, with fewer than
3,000 hours time-since-new (TSN), inspect
the next time the third-stage turbine wheel is
directly available for removal, at the next
turbine overhaul, or by April 30, 2007,
whichever occurs sooner.
(g) For third-stage turbine wheels, P/N
6899383, with 3,000 hours or more TSN,
inspect within 300 hours or by April 30,
2007, whichever occurs sooner.
(h) Remove the third-stage turbine wheel
and perform a onetime visual inspection of
the seal joint in each passage between airfoils
at the hub and shroud. Seal joint evidence
must not be present within blade fillet radii.
See Figure 1 of this AD for reference.
BILLING CODE 4910–13–P
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Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations
VerDate Aug<31>2005
14:53 Sep 30, 2005
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BILLING CODE 4910–13–C
Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations
(i) Remove from service any turbine wheel
that has seal joint evidence present within
blade fillet radii.
Alternative Methods of Compliance
(j) The Manager, Chicago Aircraft
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
(k) RRC Alert Service Bulletin No. CEB–A–
72–2205, dated April 26, 2005, pertains to
the subject of this AD.
Issued in Burlington, Massachusetts, on
September 26, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–19693 Filed 9–30–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20881; Directorate
Identifier 2004–NM–253–AD; Amendment
39–14302; AD 2003–17–07 R1]
RIN 2120–AA64
Airworthiness Directives; Various
Transport Category Airplanes
Manufactured by McDonnell Douglas
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
14:53 Sep 30, 2005
Jkt 208001
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the street
address stated in the ADDRESSES section.
Discussion
SUMMARY: The FAA is revising an
existing airworthiness directive (AD)
that applies to various transport
category airplanes manufactured by
McDonnell Douglas. We issued that AD
to require a one-time test of the fire
extinguishers for the engine and
auxiliary power unit (APU), as
applicable, to determine the capability
of the Firex electrical circuits to fire
discharge cartridges, and
troubleshooting actions if necessary.
This new AD removes certain transport
category airplanes from the applicability
of the existing AD. This AD results from
reports indicating that fire extinguishers
for the engine and auxiliary power unit
had failed to discharge when
commanded. We are issuing this AD to
prevent failure of the fire extinguishers
to fire discharge cartridges, which could
result in the inability to put out a fire
in an engine or in the APU.
DATES: The effective date of this AD is
September 24, 2003.
On September 24, 2003 (68 FR 50058,
August 20, 2003), the Director of the
VerDate Aug<31>2005
Federal Register approved the
incorporation by reference of certain
service bulletins listed in the AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach,
California 90846, Attention: Data and
Service Management, Dept. C1–L5A
(D800–0024) for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Samuel Lee, Aerospace Engineer,
Propulsion Branch, ANM–140L, FAA,
Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard,
Lakewood, California 90712–4137;
telephone (562) 627–5262; fax (562)
627–5210.
SUPPLEMENTARY INFORMATION:
The FAA proposed to amend part 39
of the Federal Aviation Regulations (14
CFR part 39) with an airworthiness
directive (AD) to revise AD 2003–17–07,
amendment 39–13281 (68 FR 50058,
August 20, 2003). The existing AD
applies to various transport category
airplanes manufactured by McDonnell
Douglas. The proposed AD was
published in the Federal Register on
April 11, 2005 (70 FR 18324) to require
a one-time test of the fire extinguishers
for the engine and auxiliary power unit
(APU), as applicable, to determine the
capability of the Firex electrical circuits
to fire discharge cartridges, and
troubleshooting actions if necessary.
That action also proposed to remove
Model MD–10–10F and MD–10–30F
airplanes from the applicability of the
existing AD.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
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57491
No Objections to the NPRM
One commenter states that it has no
objection to the NPRM.
Request To Give Credit for Previous
Alternative Methods of Compliance
(AMOCs)
This same commenter notes that it has
received an AMOC with AD 2003–17–
07. We infer that the commenter is
requesting that credit be given for
compliance with the AD in accordance
with the AMOC.
We acknowledge that the AMOC the
commenter received provides
compliance with AD 2003–17–07.
However, it is unnecessary to amend
this revised AD to reflect credit for
previous accomplishment of the onetime test of the fire extinguishers for the
engine and auxiliary power unit (APU),
as applicable. This revised AD merely
reduces the applicability of the AD, and
all of the previous requirements,
conditions, and provisions remain in
effect.
Request To Revise Note 1
One commenter requests that we
revise a typographical error in Note 1 of
the proposed AD, which referred to
paragraph (c) as the AMOC paragraph.
We agree with the commenter, and have
revised Note 1 to refer to paragraph (h)
of the AD for AMOCs.
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 change described
previously. We have determined that
this change will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
There are about 3,311 airplanes of the
affected design in the worldwide fleet.
This AD will affect about 1,520
airplanes of U.S. registry.
The actions that are required by AD
2003–17–07 and retained in this AD
take between 4 work hours and 7 work
hours per airplane, at an average labor
rate of $65 per work hour. Based on
these figures, the estimated cost of the
currently required actions is estimated
to be between $395,200, and $691,600,
on U.S. operators, or between $260 and
$455 per airplane.
This AD does not add any new
actions to the existing actions required
by AD 2003–17–07. Since this AD will
remove certain airplanes from the
applicability of the AD, the total
estimated cost of compliance of the AD
for U.S. operators is actually reduced
E:\FR\FM\03OCR1.SGM
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]]>Agencies
[Federal Register Volume 70, Number 190 (Monday, October 3, 2005)]
[Rules and Regulations]
[Pages 57487-57491]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-19693]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22534; Directorate Identifier 2005-NE-27-AD;
Amendment 39-14305; AD 2005-20-11]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Corporation (RRC) (formerly
Allison Engine Company, Allison Gas Turbine Division, and Detroit
Diesel Allison) Models 250-C28, -C28B, and -C28C Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
[[Page 57488]]
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas
Turbine Division, and Detroit Diesel Allison) (RRC) Models 250-C28, -
C28B, and -C28C turboshaft engines. This AD requires a onetime visual
inspection of the seal joint in each passage between airfoils at the
hub and shroud of third-stage turbine wheels, part number (P/N)
6899383. This AD results from reports of three failed third-stage
turbine wheels and from the manufacturer's analysis of those failures.
We are issuing this AD to prevent loss of power and uncommanded engine
shutdown due to failure of the third-stage turbine wheel.
DATES: This AD becomes effective October 18, 2005.
We must receive any comments on this AD by December 2, 2005.
ADDRESSES: Use one of the following addresses to comment on this AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Rolls-Royce Corporation, PO Box 420, Indianapolis, IN
46206-0420; telephone (317) 230-6400; fax (317) 230-4243 for the
service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: John Tallarovic, Aerospace Engineer,
Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des
Plaines, IL 60018-4696; telephone (847) 294-8180; fax (847) 294-7834.
SUPPLEMENTARY INFORMATION: In April 2005, we became aware of reports of
three failed third-stage turbine wheels, P/N 6899383. The third-stage
turbine wheels had partial loss of the blades and shroud. RRC conducted
an analysis and found the failures were caused by compromised third-
stage blade fillet radii, which led to increased stresses to the third-
stage blades and shroud. RRC categorized this finding as a
manufacturer's quality control problem. This condition, if not
corrected, could result in loss of power and uncommanded engine
shutdown due to failure of the third-stage turbine wheel.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other RRC Models 250-C28, -C28B, and -C28C turboshaft
engines of the same type design. For that reason, we are issuing this
AD to prevent loss of power and uncommanded engine shutdown due to
failure of the third-stage turbine wheel. This AD requires a onetime
visual inspection of the seal joint in each passage between airfoils at
the hub and shroud of third-stage turbine wheels, P/N 6899383.
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-2005-22534;
Directorate Identifier 2005-NE-27-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://
dms.dot.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 Docket
Management System (DMS) Web site, anyone can find and read the comments
in any of our dockets, including 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) or you may visit https://dms.dot.gov.
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.
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 the regulation:
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.
[[Page 57489]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
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:
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:
2005-20-11 Rolls-Royce Corporation (formerly Allison Engine Company,
Allison Gas Turbine Division, and Detroit Diesel Allison): Amendment
39-14305. Docket No. FAA-2005-22534; Directorate Identifier 2005-NE-
27-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October
18, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce Corporation (RRC) (formerly
Allison Engine Company, Allison Gas Turbine Division, and Detroit
Diesel Allison) models 250-C28, -C28B, and -C28C turboshaft engines.
These engines are installed on, but not limited to, Bell Helicopter
Textron 206L-1; Eurocopter Deutschland BO 105 LS A-1; and Eurocopter
Canada BO 105 LS A-3 helicopters.
Unsafe Condition
(d) This AD results from reports of three failed third-stage
turbine wheels and from the manufacturer's analysis of those
failures. We are issuing this AD to prevent loss of power and
uncommanded engine shutdown due to failure of the third-stage
turbine wheel.
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.
Onetime Visual Inspection
(f) For third-stage turbine wheels, part number (P/N) 6899383,
with fewer than 3,000 hours time-since-new (TSN), inspect the next
time the third-stage turbine wheel is directly available for
removal, at the next turbine overhaul, or by April 30, 2007,
whichever occurs sooner.
(g) For third-stage turbine wheels, P/N 6899383, with 3,000
hours or more TSN, inspect within 300 hours or by April 30, 2007,
whichever occurs sooner.
(h) Remove the third-stage turbine wheel and perform a onetime
visual inspection of the seal joint in each passage between airfoils
at the hub and shroud. Seal joint evidence must not be present
within blade fillet radii. See Figure 1 of this AD for reference.
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[[Page 57490]]
[GRAPHIC] [TIFF OMITTED] TR03OC05.055
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[[Page 57491]]
(i) Remove from service any turbine wheel that has seal joint
evidence present within blade fillet radii.
Alternative Methods of Compliance
(j) The Manager, Chicago Aircraft 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
(k) RRC Alert Service Bulletin No. CEB-A-72-2205, dated April
26, 2005, pertains to the subject of this AD.
Issued in Burlington, Massachusetts, on September 26, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-19693 Filed 9-30-05; 8:45 am]
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