Airworthiness Directives; Turbomeca S.A. Arriel 2B Turboshaft Engines, 36480-36482 [05-12415]
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36480
Federal Register / Vol. 70, No. 121 / Friday, June 24, 2005 / Rules and Regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD. See the ADDRESSES section for
a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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 (AD):
I
2005–13–14 McDonnell Douglas:
Amendment 39–14151. Docket No.
FAA–2004–19867; Directorate Identifier
2004–NM–58–AD.
Effective Date
(a) This AD becomes effective July 29,
2005.
Affected ADs
(b) None.
VerDate jul<14>2003
16:42 Jun 23, 2005
Jkt 205001
Applicability
(c) This AD applies to all McDonnell
Douglas Model MD–90–30 airplanes,
certificated in any category.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Unsafe Condition
(d) This AD was prompted by reports of
multiple incidents of blown tires on landing
while using maximum autobrake. We are
issuing this AD to prevent metallic fibers
from the first stage filter of the servo valves
inside the dual anti-skid control manifolds
(DACM) from becoming lodged in the first
stage nozzle of the servo valve, which could
lead to tire failure during high speed/high
energy braking and possible subsequent
runway departure.
Prior Inspection/Replacement of Inlet Filters
(h) Inspecting and replacing DACM inlet
filters and flushing/cleaning braking systems
before the effective date of this AD in
accordance with Boeing Service Bulletin
MD90–32–043, dated April 10, 2000, is
considered acceptable for compliance with
the corresponding actions specified in this
AD.
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.
Replacement of DACMs
(f) Within 18 months after the effective
date of this AD, replace existing DACMs with
new, improved or reworked and reidentified
DACMs, part number 6006079–2, by doing
all actions in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin MD90–32–056, dated
October 7, 2003.
Note 1: Boeing Service Bulletin MD90–32–
056 refers to Aircraft Braking Systems
Corporation (ABSC) Service Bulletin MD–90
6006079–32–02, dated August 7, 2003, as an
additional source of service information for
installing new, improved or reworked and
reidentified DACMs.
Concurrent Service Bulletin
(g) Prior to or concurrently with the
accomplishment of paragraph (f) of this AD,
perform paragraphs (g)(1) and (g)(2) of this
AD in accordance with the Accomplishment
Instructions of Boeing Service Bulletin
MD90–32–043, Revision 01, dated November
9, 2000.
(1) Perform a detailed inspection of the
metered pressure inlet filters and other
components of the DACM for damage.
Replace any damaged DACM components
with new or serviceable components, and
flush/clean the braking system, as applicable.
(2) Replace the metered pressure inlet
filters of the DACM assembly with new
filters.
Note 2: Boeing Service Bulletin MD90–32–
043, Revision 01, refers to ABSC Service
Bulletin MD90–32–12, dated January 12,
2000, as an additional source of service
information for inspecting the components of
the DACM assembly for uncleanliness,
structural damage or excessive wear that may
render the DACM inoperable, and for
replacing those components with new or
serviceable components, if necessary.
Note 3: For the purposes of this AD, a
detailed inspection is ‘‘an intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
Alternative Methods of Compliance
(AMOCs)
(i) The Manager, Los Angeles Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(j) You must use Boeing Service Bulletin
MD90–32–056, dated October 7, 2003; and
Boeing Service Bulletin MD90–32–043,
Revision 01, dated November 9, 2000; as
applicable; to perform the actions that are
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approves the incorporation by
reference of these documents in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. To
get copies of the service information, contact
Boeing Commercial Airplanes, Long Beach
Division, 3855 Lakewood Boulevard, Long
Beach, California 90846, Attention: Data and
Service Management, Dept. C1–L5A (D800–
0024). To view the AD docket, go to the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street SW., room PL–401, Nassif Building,
Washington, DC. To review copies of the
service information, go to the National
Archives and Records Administration
(NARA). For information on the availability
of this material at the NARA, call (202) 741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on June 13,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–12313 Filed 6–23–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21624; Directorate
Identifier 2005–NE–17–AD; Amendment 39–
14162; AD 2005–13–25]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
S.A. Arriel 2B Turboshaft Engines
Federal Aviation
Administration (FAA), DOT.
AGENCY:
E:\FR\FM\24JNR1.SGM
24JNR1
Federal Register / Vol. 70, No. 121 / Friday, June 24, 2005 / Rules and Regulations
Final rule; request for
comments.
ACTION:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for
Turbomeca S.A. Arriel 2B turboshaft
engines with Modification TU62A
incorporated. This AD results from
several reports of the hydromechanical
unit (HMU) acceleration controller axle
sticking. This AD requires initial and
repetitive inspections, cleaning,
lubrication, and checks for proper
operation of the HMU acceleration
controller axle. We are issuing this AD
to prevent loss of control of engine fuel
flow in manual control mode or mixed
control mode, leading to engine
overspeed and in-flight engine
shutdown, or uncommanded in-flight
engine shutdown.
DATES: Effective July 11, 2005. The
Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulations as of July 11, 2005.
We must receive any comments on
this AD by August 23, 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 Turbomeca S.A., 40220 Tarnos,
France; telephone 33 05 59 74 40 00, fax
33 05 59 74 45 15, for the service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Christopher Spinney, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803–5299; telephone
(781) 238–7175; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION: The
Direction Generale de L’Aviation Civile
(DGAC), which is the airworthiness
authority for France, notified us that an
unsafe condition might exist on
Turbomeca S.A. Arriel 2B turboshaft
engines with Modification TU62A
incorporated. The DGAC advises that
VerDate jul<14>2003
16:42 Jun 23, 2005
Jkt 205001
several reports of the HMU acceleration
controller axle sticking have been
received that resulted in engine
overspeed and in-flight engine
shutdown, or uncommanded in-flight
engine shutdown. These events can
occur when the fuel system is either in
manual control mode or mixed control
mode. They are most likely to occur
during an HMU failure simulation or
during autorotation training. HMU
acceleration controller axle sticking can
result in an excessive decrease in engine
speed when the manual control is used
to reduce fuel flow. It can also result in
an excessive increase in engine speed
when moving the control back to the
flight notch. We are issuing this AD to
prevent loss of control of engine fuel
flow in the manual control mode or
mixed control mode, leading to engine
overspeed and in-flight engine
shutdown, or uncommanded in-flight
engine shutdown.
Relevant Service Information
We have reviewed and approved the
technical contents of Turbomeca Alert
Mandatory Service Bulletin (ASB) No.
A292 73 2814, Update No. 1, dated
January 11, 2005. That ASB describes
procedures for inspecting, lubricating,
and checking for proper operation of the
HMU acceleration controller axle. The
DGAC classified this service bulletin as
mandatory and issued AD F–2004–139,
dated August 18, 2004, in order to
ensure the airworthiness of these Arriel
2B turboshaft engines in France.
Bilateral Airworthiness Agreement
This Turbomeca Arriel 2B turboshaft
engine model is manufactured in
France. It 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 has 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.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other Turbomeca Arriel 2B
turboshaft engines of the same type
design. We are issuing this AD to
prevent loss of control of engine fuel
flow in the manual control mode or
mixed control mode, leading to engine
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
36481
overspeed and in-flight engine
shutdown, or uncommanded in-flight
engine shutdown. This AD requires
initial and repetitive inspections,
cleaning, lubrication, and checks for
proper operation of the HMU
acceleration controller axle. You must
use the service information described
previously to perform the actions
required by this AD.
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. We
also found 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–2005–21624; Directorate Identifier
2005–NE–17–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. The Web site
includes 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
E:\FR\FM\24JNR1.SGM
24JNR1
36482
Federal Register / Vol. 70, No. 121 / Friday, June 24, 2005 / Rules and Regulations
in the AD docket shortly after the DMS
receives them.
PART 39—AIRWORTHINESS
DIRECTIVES
Authority for This Rulemaking
I
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 by sending a request to us
at the address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
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:
I
VerDate jul<14>2003
16:42 Jun 23, 2005
Jkt 205001
1. The authority citation for part 39
continues to read as follows:
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
2005–13–25 Turbomeca S.A.: Amendment
39–14162. Docket No. FAA–2005–21624;
Directorate Identifier 2005–NE–17–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective July 11, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Turbomeca S.A.
Arriel 2B turboshaft engines with
Modification TU62A incorporated. These
engines are installed on, but not limited to,
Eurocopter AS350B3 helicopters.
this service bulletin in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. Contact
Turbomeca S.A., 40220 Tarnos, France;
telephone 33 05 59 74 40 00, fax 33 05 59
74 45 15, for a copy of this service
information. You may review copies at the
Docket Management Facility; U.S.
Department of Transportation, 400 Seventh
Street, SW., Nassif Building, Room PL–401,
Washington, DC 20590–0001, on the internet
at https://dms.dot.gov; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Burlington, Massachusetts, on
June 16, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 05–12415 Filed 6–23–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Unsafe Condition
(d) This AD results from several reports of
the hydromechanical unit (HMU)
acceleration controller axle sticking. We are
issuing this AD to prevent loss of control of
engine fuel flow in the manual control mode
or mixed control mode, leading to engine
overspeed and in-flight engine shutdown, or
uncommanded in-flight engine shutdown.
Federal Aviation Administration
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) Within 20 operating hours after the
effective date of this AD, inspect, clean,
lubricate, and check for proper operation of
the HMU acceleration controller axle. Use
paragraph 2 of Instructions to be
Incorporated of Turbomeca Alert Mandatory
Service Bulletin No. A292 73 2814, Update
No. 1, dated January 11, 2005, to do these
actions.
(g) Thereafter, repeat the actions specified
in paragraph (f) of this AD within every 210
operating hours.
Airworthiness Directives; Eurocopter
France Model EC 155B, EC155B1, SA–
365N, SA–365N1, AS–365N2, and AS
365 N3 Helicopters
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) DGAC airworthiness directive F–2004–
139, dated August 18, 2004, also addresses
the subject of this AD.
Material Incorporated by Reference
(j) You must use Turbomeca Alert
Mandatory Service Bulletin (ASB) No. A292
73 2814, Update No. 1, dated January 11,
2005, to perform the actions required by this
AD. The Director of the Federal Register
approved the incorporation by reference of
PO 00000
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Fmt 4700
Sfmt 4700
14 CFR Part 39
[Docket No. FAA–2005–20512; Directorate
Identifier 2004–SW–35–AD; Amendment 39–
14160; AD 2005–13–23]
RIN 2120–AA64
Federal Aviation
Administration, DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This amendment supersedes
an existing airworthiness directive (AD)
for Eurocopter France (Eurocopter)
Model EC 155B, SA–365N and N1, AS–
365N2, and AS 365 N3 helicopters. That
AD currently requires inspecting the
hydraulic brake hose (hose) for crazing,
pinching, distortion, or leaks at the
torque link hinge and replacing the
hose, if necessary. That AD also requires
inspecting the hose and the emergency
flotation gear pipe to ensure adequate
clearance, and adjusting the landing
gear leg, if necessary. This amendment
requires the same actions as the existing
AD and adds another model helicopter
to the applicability. This amendment is
prompted by notification by the
manufacturer and the European
Authority that another affected model
helicopter, the Model EC155B1, may
have the same unsafe condition and
should be added to the existing AD. The
actions specified by this AD are
intended to prevent failure of a hose,
E:\FR\FM\24JNR1.SGM
24JNR1
]]>Agencies
[Federal Register Volume 70, Number 121 (Friday, June 24, 2005)]
[Rules and Regulations]
[Pages 36480-36482]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-12415]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21624; Directorate Identifier 2005-NE-17-AD;
Amendment 39-14162; AD 2005-13-25]
RIN 2120-AA64
Airworthiness Directives; Turbomeca S.A. Arriel 2B Turboshaft
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
[[Page 36481]]
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Turbomeca S.A. Arriel 2B turboshaft engines with Modification TU62A
incorporated. This AD results from several reports of the
hydromechanical unit (HMU) acceleration controller axle sticking. This
AD requires initial and repetitive inspections, cleaning, lubrication,
and checks for proper operation of the HMU acceleration controller
axle. We are issuing this AD to prevent loss of control of engine fuel
flow in manual control mode or mixed control mode, leading to engine
overspeed and in-flight engine shutdown, or uncommanded in-flight
engine shutdown.
DATES: Effective July 11, 2005. The Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulations as of July 11, 2005.
We must receive any comments on this AD by August 23, 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 Turbomeca S.A., 40220 Tarnos, France; telephone 33 05 59 74 40
00, fax 33 05 59 74 45 15, for the service information identified in
this AD.
FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299;
telephone (781) 238-7175; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The Direction Generale de L'Aviation Civile
(DGAC), which is the airworthiness authority for France, notified us
that an unsafe condition might exist on Turbomeca S.A. Arriel 2B
turboshaft engines with Modification TU62A incorporated. The DGAC
advises that several reports of the HMU acceleration controller axle
sticking have been received that resulted in engine overspeed and in-
flight engine shutdown, or uncommanded in-flight engine shutdown. These
events can occur when the fuel system is either in manual control mode
or mixed control mode. They are most likely to occur during an HMU
failure simulation or during autorotation training. HMU acceleration
controller axle sticking can result in an excessive decrease in engine
speed when the manual control is used to reduce fuel flow. It can also
result in an excessive increase in engine speed when moving the control
back to the flight notch. We are issuing this AD to prevent loss of
control of engine fuel flow in the manual control mode or mixed control
mode, leading to engine overspeed and in-flight engine shutdown, or
uncommanded in-flight engine shutdown.
Relevant Service Information
We have reviewed and approved the technical contents of Turbomeca
Alert Mandatory Service Bulletin (ASB) No. A292 73 2814, Update No. 1,
dated January 11, 2005. That ASB describes procedures for inspecting,
lubricating, and checking for proper operation of the HMU acceleration
controller axle. The DGAC classified this service bulletin as mandatory
and issued AD F-2004-139, dated August 18, 2004, in order to ensure the
airworthiness of these Arriel 2B turboshaft engines in France.
Bilateral Airworthiness Agreement
This Turbomeca Arriel 2B turboshaft engine model is manufactured in
France. It 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 has
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.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other Turbomeca Arriel 2B turboshaft engines of the same
type design. We are issuing this AD to prevent loss of control of
engine fuel flow in the manual control mode or mixed control mode,
leading to engine overspeed and in-flight engine shutdown, or
uncommanded in-flight engine shutdown. This AD requires initial and
repetitive inspections, cleaning, lubrication, and checks for proper
operation of the HMU acceleration controller axle. You must use the
service information described previously to perform the actions
required by this AD.
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. We also found
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-2005-21624;
Directorate Identifier 2005-NE-17-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. The
Web site includes 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
[[Page 36482]]
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 by
sending a request to us at the address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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:
2005-13-25 Turbomeca S.A.: Amendment 39-14162. Docket No. FAA-2005-
21624; Directorate Identifier 2005-NE-17-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective July 11,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Turbomeca S.A. Arriel 2B turboshaft
engines with Modification TU62A incorporated. These engines are
installed on, but not limited to, Eurocopter AS350B3 helicopters.
Unsafe Condition
(d) This AD results from several reports of the hydromechanical
unit (HMU) acceleration controller axle sticking. We are issuing
this AD to prevent loss of control of engine fuel flow in the manual
control mode or mixed control mode, leading to engine overspeed and
in-flight engine shutdown, or uncommanded in-flight engine shutdown.
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) Within 20 operating hours after the effective date of this
AD, inspect, clean, lubricate, and check for proper operation of the
HMU acceleration controller axle. Use paragraph 2 of Instructions to
be Incorporated of Turbomeca Alert Mandatory Service Bulletin No.
A292 73 2814, Update No. 1, dated January 11, 2005, to do these
actions.
(g) Thereafter, repeat the actions specified in paragraph (f) of
this AD within every 210 operating hours.
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) DGAC airworthiness directive F-2004-139, dated August 18,
2004, also addresses the subject of this AD.
Material Incorporated by Reference
(j) You must use Turbomeca Alert Mandatory Service Bulletin
(ASB) No. A292 73 2814, Update No. 1, dated January 11, 2005, to
perform the actions required by this AD. The Director of the Federal
Register approved the incorporation by reference of this service
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Turbomeca S.A., 40220 Tarnos, France; telephone 33 05 59 74
40 00, fax 33 05 59 74 45 15, for a copy of this service
information. You may review copies at the Docket Management
Facility; U.S. Department of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL-401, Washington, DC 20590-0001, on the
internet at https://dms.dot.gov; or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, call 202-741-6030, or go to: https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Burlington, Massachusetts, on June 16, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 05-12415 Filed 6-23-05; 8:45 am]
BILLING CODE 4910-13-P
