Airworthiness Directives; Turbomeca Arrius 2F Turboshaft Engines, 28791-28793 [05-9982]
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Federal Register / Vol. 70, No. 96 / Thursday, May 19, 2005 / Rules and Regulations
(b) The grant recipient may transfer
additional assets into the revolving loan
fund.
(c) All cash and other assets of the
revolving loan fund shall be deposited
in a separate bank account or accounts.
(d) No cash or other assets of any
other fund maintained by the grant
recipient shall be commingled with the
cash and other assets of the revolving
loan fund.
(e) All moneys deposited in such bank
account or accounts shall be money of
the revolving loan fund.
(f) Loans to loan recipients are
advanced from the revolving loan fund.
(g) The revolving loan fund will
consist of receivables created by making
loans, the grant recipient’s security
interest in collateral pledged by loan
recipients, collections on the
receivables, interest, fees, and any other
income or assets derived from the
operation of the revolving loan fund.
(h) The portion of the revolving loan
fund that consists of HWWS grant
funds, on a last-in-first-out basis, may be
used for only those purposes set forth in
this part.
(i) The grant recipient must submit an
annual budget of proposed
administrative costs for RUS approval.
The amount removed from the revolving
loan fund for administrative costs in any
year must be reasonable; must not
exceed the actual cost of operating the
revolving loan fund, including loan
servicing and providing technical
assistance; and must not exceed the
amount approved by RUS in the grant
recipient’s annual budget.
(j) A reasonable amount of revolved
funds must be used to create a reserve
for bad debts. Reserves should be
accumulated over a period of years. The
total amount should not exceed
maximum expected losses, considering
the quality of the grant recipient’s
portfolio of loans. Unless the grant
recipient provides loss and delinquency
records that, in the opinion of RUS,
justifies different amounts, a reserve for
bad debts of 6 percent of outstanding
loans must be accumulated over three
years and then maintained as set forth
in the grant agreement.
(k) Any cash in the revolving loan
fund from any source that is not needed
for debt service, approved
administrative costs, or reasonable
reserves must be available for additional
loans to loan recipients.
(l) All reserves and other cash in the
revolving loan fund not immediately
needed for loans to loan recipients or
other authorized uses must be deposited
in accounts in banks or other financial
institutions. Such accounts must be
fully covered by Federal deposit
VerDate jul<14>2003
15:30 May 18, 2005
Jkt 205001
insurance or fully collateralized with
U.S. Government obligations, and must
be interest bearing. Any interest earned
thereon remains a part of the revolving
loan fund.
Dated: May 12, 2005.
Curtis M. Anderson,
Acting Administrator, Rural Utilities Service.
[FR Doc. 05–10003 Filed 5–18–05; 8:45 am]
BILLING CODE 3410–15–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21155; Directorate
Identifier 2005–NE–14–AD; Amendment 39–
14099; AD 2005–09–51]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
Arrius 2F Turboshaft Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: This document publishes in
the Federal Register an amendment
adopting emergency airworthiness
directive (AD) 2005–09–51 that we sent
previously to all known U.S. owners
and operators of certain Turbomeca
Arrius 2F turboshaft engines. This AD
requires before further flight, replacing
the Module 2 on certain engines listed
by serial number (SN) in this AD. This
AD results from a report of the failure
of a high pressure turbine (HPT) blade
and damage to two other HPT blades in
a Turbomeca Arrius 2F turboshaft
engine. We are issuing this AD to
prevent failure of the engine and
subsequent loss of power.
DATES: This AD becomes effective June
3, 2005 to all persons except those
persons to whom it was made
immediately effective by emergency AD
2005–09–51, issued on April 28, 2005,
which contained the requirements of
this amendment.
We must receive any comments on
this AD by July 18, 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
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
28791
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.
FOR FURTHER INFORMATION CONTACT:
Christopher Spinney, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803–2599, telephone
(781) 238–7175; fax (781) 238–7199.
The
Direction General De L’Aviation Civile
(DGAC), which is the airworthiness
authority for France, recently notified us
that an unsafe condition might exist on
certain Turbomeca Arrius 2F turboshaft
engines. The DGAC advises that on
March 31, 2005, the failure of an HPT
blade and damage to two other HPT
blades in a Turbomeca Arrius 2F
turboshaft engine caused an in-flight
engine shutdown (IFSD). That IFSD
resulted in loss of the helicopter and
fatalities and injuries to the occupants.
A preliminary investigation of the
engine found that a ferrule started a
disturbance that reduced the cooling
effect of the secondary air system. The
secondary air system cools the HPT.
Turbomeca identified 38 engines that
might contain a configuration similar to
the engine involved in the accident.
This condition, if not corrected, could
result in failure of the engine and
subsequent loss of power. On April 28,
2005, we issued emergency AD 2005–
09–51 that applies to certain Turbomeca
Arrius 2F turboshaft engines. That AD
requires before further flight, replacing
the Module 2 on certain engines listed
by SN in that AD.
SUPPLEMENTARY INFORMATION:
Bilateral Airworthiness Agreement
This Turbomeca Arrius 2F turboshaft
engine model is manufactured in France
and is type certificated for operation in
the United States under the provisions
of section 21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement. Under this bilateral
airworthiness agreement, the DGAC
kept the FAA informed of the situation
described above. We have examined the
findings of the DGAC, reviewed all
available information, and determined
that AD action is necessary for products
of this type design that are certificated
for operation in the United States.
E:\FR\FM\19MYR1.SGM
19MYR1
28792
Federal Register / Vol. 70, No. 96 / Thursday, May 19, 2005 / Rules and Regulations
FAA’s Determination and Requirements
of This AD
2000 (65 FR 19477–78) or you may visit
https://dms.dot.gov.
this summary at the address listed
under ADDRESSES.
Since the unsafe condition described
is likely to exist or develop on other
engines of the same type design, we
issued emergency AD 2005–09–51 to
prevent failure of the engine and
subsequent loss of power. This AD
requires before further flight, replacing
the Module 2, on certain engines listed
by SN in this AD.
Examining the AD Docket
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
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 existed to make the AD
effective immediately on April 28, 2005,
to all known U.S. owners and operators
of Turbomeca Arrius 2F turbofan
engines. These conditions still exist,
and we are publishing the AD in the
Federal Register as an amendment to
Section 39.13 of part 39 of the Code
Federal Regulations (14 CFR part 39) to
make it effective to all persons.
Interim Action
These actions are interim actions and
we may take further rulemaking actions
in the future.
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–2005–21155; Directorate Identifier
2005–NE–14–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 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,
VerDate jul<14>2003
15:30 May 18, 2005
Jkt 205001
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the DMS 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
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
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
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
2005–09–51 Turbomeca: Amendment 39–
14099. Docket No. FAA–2005–21155;
Directorate Identifier 2005–NE–14–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective June 3, 2005, to all persons
except those persons to whom it was made
immediately effective by emergency AD
2005–09–51, issued April 28, 2005, which
contained the requirements of this
amendment.
Affected ADs
(b) None.
Applicability
(c) This AD applies to certain Turbomeca
Arrius 2F turboshaft engines listed by serial
number (SN) in Table 1 of this AD. These
engines are installed on, but not limited to,
Eurocopter EC 120B Helicopters.
TABLE 1.—ENGINE AND MODULE
SERIAL NUMBERS
Engine SN
34416
34417
34418
34419
34420
34421
34422
34423
34424
34425
34426
34427
34428
34429
34430
34431
34432
34433
34434
34435
E:\FR\FM\19MYR1.SGM
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......................................
......................................
......................................
......................................
......................................
......................................
......................................
19MYR1
Module 2 SN
01045
01063
01052
01053
01067
01068
01051
01078
01079
01080
01083
01089
01090
01097
01098
01099
01102
01103
01109
01110
Federal Register / Vol. 70, No. 96 / Thursday, May 19, 2005 / Rules and Regulations
TABLE 1.—ENGINE AND MODULE
SERIAL NUMBERS—Continued
Engine SN
Module 2 SN
34436 ......................................
34437 ......................................
34438 ......................................
34439 ......................................
34440 ......................................
34441 ......................................
34442 ......................................
34443 ......................................
34444 ......................................
34445 ......................................
34446 ......................................
34447 ......................................
34448 ......................................
34449 ......................................
34450 ......................................
Not Installed ............................
34033 ......................................
34177 ......................................
01121
01122
01123
01136
01139
01140
01138
01141
01142
01146
01147
01148
01164
01165
01177
01149
00125
00446
Unsafe Condition
(d) This AD results from failure of a high
pressure turbine (HPT) blade and damage to
two other HPT blades in a Turbomeca Arrius
2F turboshaft engine on March 31, 2005. We
are issuing this AD to prevent failure of the
engine and subsequent loss of power.
Compliance
(e) You are responsible for having the
actions required by this AD performed before
further flight, unless the actions have already
been done.
Replacing the Module 2
(f) Before further flight, on Turbomeca
Arrius 2F engines that have a SN listed in
Table 1 of this AD, remove the Module 2 and
replace the Module with a Module 2 that was
overhauled or that has a SN not listed in
Table 1 of this AD.
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) Direction General De L’Aviation Civile
Emergency airworthiness directive No. UF–
2005–073, dated April 27, 2005, also
addresses the subject of this AD.
Issued in Burlington, Massachusetts, on
May 13, 2005.
Robert J. Ganley,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–9982 Filed 5–18–05; 8:45 am]
BILLING CODE 4910–13–P
VerDate jul<14>2003
15:30 May 18, 2005
Jkt 205001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19998; Directorate
Identifier 2004–NM–224–AD; Amendment
39–14097; AD 2005–10–20]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 777–200 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 777–200 series airplanes.
This AD requires replacing the pressure
switches on the override/jettison fuel
pumps with new pressure switches, and
replacing the ship side electrical
connectors for the pressure switches on
override/jettison fuel pumps with new
connectors. This AD is prompted by
reports that the ‘‘FUEL LOW CENTER’’
message does not activate when the fuel
level in the center tank is low. We are
issuing this AD to prevent the fuel
pumps in the center fuel tank from
running dry and becoming a potential
ignition source, which could result in a
fuel tank explosion.
DATES: This AD becomes effective June
23, 2005.
The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of June 23, 2005.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
Docket: AD docket contains the
proposed AD, comments, and any final
disposition. You can 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 U.S. Department of Transportation,
400 Seventh Street SW., room PL–401,
Washington, DC. This docket number is
FAA–2004–19998; the directorate
identifier for this docket is 2004–NM–
224–AD.
FOR FURTHER INFORMATION CONTACT:
Margaret Langsted, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
PO 00000
Frm 00019
Fmt 4700
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28793
Washington 98055–4056; telephone
(425) 917–6500; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
an AD for certain Boeing Model 777–
200 series airplanes. That action,
published in the Federal Register on
January 5, 2005 (70 FR 735), proposed
to require replacing the pressure
switches on the override/jettison fuel
pumps with new pressure switches, and
replacing the ship side electrical
connectors for the pressure switches on
override/jettison fuel pumps with new
connectors.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been submitted on the proposed AD.
One commenter concurs with the
contents of the proposed AD.
Request To Clarify Applicability
One commenter states that there is a
concern for possible misinterpretation
of the applicability specified in the
Summary and Applicability sections of
the proposed AD. The commenter adds
that the referenced service bulletin
specifically identifies the affected
airplanes, and it is only applicable to
Boeing Model 777–200 series airplanes
equipped with no center wing tank, and
is not applicable to Boeing Model 777–
200ER series airplanes. The commenter
recommends clarification that Model
777–200ER series airplanes are not
affected be added to the proposed AD.
We acknowledge the commenter’s
concern and offer clarification. The
proposed AD is applicable to Boeing
Model 777–200 series airplanes,
certificated in any category; as
identified in Boeing Special Attention
Service Bulletin 777–28–0036, dated
September 2, 2004. There are two center
wing tank configurations certificated on
the Model 777–200 series airplane; the
referenced service bulletin identifies the
airplanes that have the smaller tank
configuration. The other Model 777–200
series airplanes, informally referred to
by Boeing as Model 777–200ER
airplanes, have a larger center wing tank
and a different pump inlet
configuration. Therefore, Model 777–
200ER airplanes are not subject to the
identified unsafe condition. We have
not changed the final rule in this regard.
Request To Change the Costs of
Compliance Section/Compliance Time
One commenter asks that the work
hours shown in the estimated costs table
in the proposed AD be reconsidered.
The commenter estimates 5.5 work
E:\FR\FM\19MYR1.SGM
19MYR1
]]>Agencies
[Federal Register Volume 70, Number 96 (Thursday, May 19, 2005)]
[Rules and Regulations]
[Pages 28791-28793]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-9982]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21155; Directorate Identifier 2005-NE-14-AD;
Amendment 39-14099; AD 2005-09-51]
RIN 2120-AA64
Airworthiness Directives; Turbomeca Arrius 2F Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This document publishes in the Federal Register an amendment
adopting emergency airworthiness directive (AD) 2005-09-51 that we sent
previously to all known U.S. owners and operators of certain Turbomeca
Arrius 2F turboshaft engines. This AD requires before further flight,
replacing the Module 2 on certain engines listed by serial number (SN)
in this AD. This AD results from a report of the failure of a high
pressure turbine (HPT) blade and damage to two other HPT blades in a
Turbomeca Arrius 2F turboshaft engine. We are issuing this AD to
prevent failure of the engine and subsequent loss of power.
DATES: This AD becomes effective June 3, 2005 to all persons except
those persons to whom it was made immediately effective by emergency AD
2005-09-51, issued on April 28, 2005, which contained the requirements
of this amendment.
We must receive any comments on this AD by July 18, 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.
FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-2599,
telephone (781) 238-7175; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The Direction General De L'Aviation Civile
(DGAC), which is the airworthiness authority for France, recently
notified us that an unsafe condition might exist on certain Turbomeca
Arrius 2F turboshaft engines. The DGAC advises that on March 31, 2005,
the failure of an HPT blade and damage to two other HPT blades in a
Turbomeca Arrius 2F turboshaft engine caused an in-flight engine
shutdown (IFSD). That IFSD resulted in loss of the helicopter and
fatalities and injuries to the occupants. A preliminary investigation
of the engine found that a ferrule started a disturbance that reduced
the cooling effect of the secondary air system. The secondary air
system cools the HPT. Turbomeca identified 38 engines that might
contain a configuration similar to the engine involved in the accident.
This condition, if not corrected, could result in failure of the engine
and subsequent loss of power. On April 28, 2005, we issued emergency AD
2005-09-51 that applies to certain Turbomeca Arrius 2F turboshaft
engines. That AD requires before further flight, replacing the Module 2
on certain engines listed by SN in that AD.
Bilateral Airworthiness Agreement
This Turbomeca Arrius 2F turboshaft engine model is manufactured in
France and is type certificated for operation in the United States
under the provisions of section 21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the applicable bilateral airworthiness
agreement. Under this bilateral airworthiness agreement, the DGAC kept
the FAA informed of the situation described above. We have examined the
findings of the DGAC, reviewed all available information, and
determined that AD action is necessary for products of this type design
that are certificated for operation in the United States.
[[Page 28792]]
FAA's Determination and Requirements of This AD
Since the unsafe condition described is likely to exist or develop
on other engines of the same type design, we issued emergency AD 2005-
09-51 to prevent failure of the engine and subsequent loss of power.
This AD requires before further flight, replacing the Module 2, on
certain engines listed by SN in this AD.
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 existed to make the AD effective immediately on April 28, 2005,
to all known U.S. owners and operators of Turbomeca Arrius 2F turbofan
engines. These conditions still exist, and we are publishing the AD in
the Federal Register as an amendment to Section 39.13 of part 39 of the
Code Federal Regulations (14 CFR part 39) to make it effective to all
persons.
Interim Action
These actions are interim actions and we may take further
rulemaking actions in the future.
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-2005-21155;
Directorate Identifier 2005-NE-14-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 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 DMS 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.
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:
2005-09-51 Turbomeca: Amendment 39-14099. Docket No. FAA-2005-21155;
Directorate Identifier 2005-NE-14-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective June 3,
2005, to all persons except those persons to whom it was made
immediately effective by emergency AD 2005-09-51, issued April 28,
2005, which contained the requirements of this amendment.
Affected ADs
(b) None.
Applicability
(c) This AD applies to certain Turbomeca Arrius 2F turboshaft
engines listed by serial number (SN) in Table 1 of this AD. These
engines are installed on, but not limited to, Eurocopter EC 120B
Helicopters.
Table 1.--Engine and Module Serial Numbers
------------------------------------------------------------------------
Engine SN Module 2 SN
------------------------------------------------------------------------
34416..................................................... 01045
34417..................................................... 01063
34418..................................................... 01052
34419..................................................... 01053
34420..................................................... 01067
34421..................................................... 01068
34422..................................................... 01051
34423..................................................... 01078
34424..................................................... 01079
34425..................................................... 01080
34426..................................................... 01083
34427..................................................... 01089
34428..................................................... 01090
34429..................................................... 01097
34430..................................................... 01098
34431..................................................... 01099
34432..................................................... 01102
34433..................................................... 01103
34434..................................................... 01109
34435..................................................... 01110
[[Page 28793]]
34436..................................................... 01121
34437..................................................... 01122
34438..................................................... 01123
34439..................................................... 01136
34440..................................................... 01139
34441..................................................... 01140
34442..................................................... 01138
34443..................................................... 01141
34444..................................................... 01142
34445..................................................... 01146
34446..................................................... 01147
34447..................................................... 01148
34448..................................................... 01164
34449..................................................... 01165
34450..................................................... 01177
Not Installed............................................. 01149
34033..................................................... 00125
34177..................................................... 00446
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from failure of a high pressure turbine
(HPT) blade and damage to two other HPT blades in a Turbomeca Arrius
2F turboshaft engine on March 31, 2005. We are issuing this AD to
prevent failure of the engine and subsequent loss of power.
Compliance
(e) You are responsible for having the actions required by this
AD performed before further flight, unless the actions have already
been done.
Replacing the Module 2
(f) Before further flight, on Turbomeca Arrius 2F engines that
have a SN listed in Table 1 of this AD, remove the Module 2 and
replace the Module with a Module 2 that was overhauled or that has a
SN not listed in Table 1 of this AD.
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) Direction General De L'Aviation Civile Emergency
airworthiness directive No. UF-2005-073, dated April 27, 2005, also
addresses the subject of this AD.
Issued in Burlington, Massachusetts, on May 13, 2005.
Robert J. Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-9982 Filed 5-18-05; 8:45 am]
BILLING CODE 4910-13-P
