Airworthiness Directives; Turbomeca S.A. ARRIUS 2F Turboshaft Engines, 16809-16811 [E9-8310]
Download as PDF
Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Proposed Rules
Removing LPCR Discs from Service
(f) For engines with a second and
third stage LPCR disc that has a serial
number (SN) listed in Table 5 of
Honeywell International Inc. Alert
Service Bulletins (ASBs) TFE731–72–
A3748, dated August 21, 2008, or
TFE731–72–A3749, dated August 21,
2008, remove the second and third stage
LPCR disc from service within 100
cycles-in-service (CIS) after the effective
date of this AD.
(g) For engines with a second and
third stage LPCR disc that has an SN
listed in Table 6 of Honeywell
International Inc. ASBs TFE731–72–
A3748, dated August 21, 2008, or
TFE731–72–A3749, dated August 21,
2008, do the earlier of the following:
(1) Remove the second and third stage
LPCR disc from service within 2,000 CIS
after the effective date of this AD, or
(2) Remove the second and third stage
LPCR disc from service the next time
the intermediate case is removed from
the LPC case.
Installation Prohibition
(h) After the effective date of this AD,
don’t install any second and third stage
LPCR disc removed as required in
paragraphs (f) or (g) of this AD.
Alternative Methods of Compliance
(i) The Manager, Los Angeles 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
(j) Contact Joseph Costa, Aerospace
Engineer, Los Angeles Aircraft
Certification Office, FAA, Transport
Airplane Directorate, 3960 Paramount
Blvd., Lakewood, CA 90712–4137; email: joseph.costa@faa.gov; telephone:
(562) 627–5246; fax: (562) 627–5210, for
more information about this AD.
(k) Honeywell International Inc. ASBs
TFE731–72–A3748, dated August 21,
2008, and TFE731–72–A3749, dated
August 21, 2008, pertain to the subject
of this AD. Contact Honeywell Engines
and Systems Technical Publications and
Distribution, M/S 2101–201, P.O. Box
52170, Phoenix, AZ 85072–2170,
telephone: Global Customer Care toll
free (800) 601–3099; International
callers (602) 365–3099, for a copy of this
service information.
VerDate Nov<24>2008
18:52 Apr 10, 2009
Jkt 217001
Issued in Burlington, Massachusetts, on
April 6, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E9–8309 Filed 4–10–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0330; Directorate
Identifier 2008–NE–43–AD]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
S.A. ARRIUS 2F Turboshaft Engines
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as: Rubs between the pipe and
the bulkhead may lead to premature
wearing and finally rupture of the P3 air
pipe. The loss of P3 air pressure would
then force the fuel control system to idle
which could have a detrimental effect in
critical phases of flight. We are
proposing this AD to prevent an
uncommanded power loss, which could
result in an emergency autorotation
landing or accident.
DATES: We must receive comments on
this proposed AD by May 13, 2009.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the instructions for sending your
comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 1200
New Jersey Avenue, SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: (202) 493–2251.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
16809
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is the
same as the Mail address provided in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: james.lawrence@faa.gov;
telephone (781) 238–7176; fax (781)
238–7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2009–0330; Directorate Identifier
2008–NE–43–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of the Web
site, anyone can find and read the
comments in any of our dockets,
including, if provided, the name of the
individual who sent the comment (or
signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78).
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2008–0134R1,
dated February 17, 2009, (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
E:\FR\FM\13APP1.SGM
13APP1
16810
Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Proposed Rules
On several ARRIUS 2F engines, the
clearance between the P3 air pipe P/N
0319719180 and the rear right bulkhead P/N
0319998240 has been found to be too small.
Investigations have shown that both P3 air
pipe and rear right bulkhead were compliant
to the design. The Turbomeca Engineering
Department concluded that the tolerance of
assembly established during the design could
result in some rubbing between parts.
Rubs between the pipe and the bulkhead
may lead to premature wearing and finally
rupture of the P3 air pipe. The loss of P3 air
pressure would then force the fuel control
system to idle which could have a
detrimental effect in critical phases of flight.
For the reason stated above, this
Airworthiness Directive (AD) requires the
inspection of the P3 air pipe (first section)
and RH rear half-wall and, in case it is found
damaged or non-compliant (idem), the
replacement or readjustment of parts.
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.
You may obtain further information by
examining the MCAI in the AD docket.
Regulatory Findings
Relevant Service Information
Turbomeca S.A. has issued
Mandatory Service Bulletin (MSB) No.
319 75 4810, dated May 14, 2008. The
actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of France, and is
approved for operation in the United
States. Pursuant to our bilateral
agreement with France, they have
notified us of the unsafe condition
described in the MCAI and service
information referenced above. We are
proposing this AD because we evaluated
all information provided by France and
determined the unsafe condition exists
and is likely to exist or develop on other
products of the same type design.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 94 engines installed on
helicopters of U.S. registry. We also
estimate that it would take about 1
work-hour per engine to comply with
this proposed AD. The average labor
rate is $80 per work-hour. Required
parts would cost about $705 per engine.
Based on these figures, we estimate the
cost of the proposed AD on U.S.
operators to be $73,790. Our cost
estimate is exclusive of possible
warranty coverage.
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
VerDate Nov<24>2008
18:52 Apr 10, 2009
Jkt 217001
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 this proposed 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 regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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 AD:
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Frm 00014
Fmt 4702
Sfmt 4702
Turbomeca S.A.: Docket No. FAA–2009–
0330; Directorate Identifier 2008–NE–
43–AD.
Comments Due Date
(a) We must receive comments by May 13,
2009.
Affected Airworthiness Directives (ADs)
(b) None.
Applicability
(c) This AD applies to Turbomeca S.A.
ARRIUS 2F turboshaft engines with P3 air
pipe, part number 0319719180, installed.
These engines are installed on, but not
limited to, Eurocopter EC120B helicopters.
Reason
(d) Rubs between the pipe and the
bulkhead may lead to premature wearing and
finally rupture of the P3 air pipe. The loss
of P3 air pressure would then force the fuel
control system to idle which could have a
detrimental effect in critical phases of flight.
We are issuing this AD to prevent an
uncommanded power loss, which could
result in an emergency autorotation landing
or accident.
Actions and Compliance
(e) Unless already done, do the following
actions within 100 operating hours after the
effective date of this AD. Use paragraphs
2.B.(1) through 2.C.(2) of Turbomeca
Mandatory Service Bulletin No. 319 75 4810,
dated May 14, 2008.
(1) Visually inspect P3 air pipe (first
section) and RH rear half-wall.
(2) Inspect play between P3 air pipe (first
section) and RH rear half-wall.
(3) Replace P3 air pipe (first section) if any
damage is found.
(4) Readjust the first section of the P3 air
pipe if the inspected clearance is found to be
not compliant.
(5) If the play after readjusting the first
section of the P3 air pipe is still less than 0.5
mm, repeat paragraphs (e)(1) through (e)(4) of
this AD within intervals of 100 hours timesince-last inspection.
(6) Replace RH rear half-wall if any damage
is found.
FAA AD Differences
(f) None.
Other FAA AD Provisions
(g) Alternative Methods of Compliance
(AMOCs): The Manager, Engine Certification
Office, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Related Information
(h) Refer to MCAI EASA Airworthiness
Directive 2008–0134R1, dated February 17,
2009, and Turbomeca S.A. Mandatory
Service Bulletin No. 319 75 4810, dated May
14, 2008, for related information. Contact
Turbomeca, 40220 Tarnos, France; telephone
33 (0)5 59 74 40 00; telex 570 042; fax 33 (0)5
59 74 45 15, for a copy of this service
information.
(i) Contact James Lawrence, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
E:\FR\FM\13APP1.SGM
13APP1
Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Proposed Rules
England Executive Park, Burlington, MA
01803; e-mail: james.lawrence@faa.gov;
telephone (781) 238–7176; fax (781) 238–
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on
April 6, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E9–8310 Filed 4–10–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
FOR FURTHER INFORMATION CONTACT:
Roger Pesuit, Aerospace Engineer, Los
Angeles Aircraft Certification Office,
FAA, Transport Airplane Directorate,
3960 Paramount Blvd., Lakewood, CA
90712; e-mail: roger.pesuit@faa.gov;
telephone (562) 627–5251, fax (562)
627–5210.
Contact Hamilton Sundstrand
Technical Publications, One Hamilton
Road, Mail Stop: 1A–3–Z63, Windsor
Locks, CT 06096–1010; telephone (860)
654–3575, for a copy of the service
information identified in this proposed
AD.
SUPPLEMENTARY INFORMATION:
14 CFR Part 39
Comments Invited
[Docket No. FAA–2009–0247; Directorate
Identifier 2009–NE–07–AD]
We invite you to send us any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2009–0247; Directorate Identifier 2009–
NE–07–AD’’ in the subject line of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of the Web
site, anyone can find and read the
comments in any of our dockets,
including, if provided, the name of the
individual who sent the comment (or
signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78).
RIN 2120–AA64
Airworthiness Directives; Hamilton
Sundstrand Power Systems T–62T–
46C12 Auxiliary Power Units
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
Hamilton Sundstrand Power Systems
T–62T–46C12 auxiliary power units
(APUs). This proposed AD would
require upgrading the software in the
APU full-authority digital controller
(FADEC), from software version
02.01.000 to version 03.00.000. This
proposed AD results from two reports of
APU compartment explosions due to
over-fueling of the APU at low rpm
during the start sequence. We are
proposing this AD to prevent overfueling of the APU during the start
sequence, which could lead to fuel
explosions, injury, and damage to the
APU and the airplane.
DATES: We must receive any comments
on this proposed AD by June 12, 2009.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD.
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the instructions for sending your
comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 1200
New Jersey Avenue, SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: (202) 493–2251.
VerDate Nov<24>2008
18:52 Apr 10, 2009
Jkt 217001
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is the
same as the Mail address provided in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
16811
Discussion
We received two reports of APU
compartment explosions of Hamilton
Sundstrand Power Systems T–62T–
46C12 APUs, related to attempted start
of the APU. In both events, the APU
compartment was damaged, and the
compartment doors were blown off the
airplane. The APUs are ground
operational only, and the airplanes were
parked at the time of explosion.
Investigation has revealed that the APU
could receive an excessively rich fuel
mixture at low rpm during the start
sequence, due to the APU FADEC
version 02.01.000 software, that can
allow over-fueling of the APU during
starting. This condition, if not corrected,
could result in over-fueling of the APU
during the start sequence, which could
lead to fuel explosion, injury, and
damage to the APU and the airplane.
Relevant Service Information
We have reviewed and approved the
technical contents of Hamilton
Sundstrand Power Systems Service
Bulletin No. 4503067–49–12, Revision
1, dated December 23, 2008, that
describes procedures for upgrading the
APU FADEC software to version
03.00.000. This upgrade eliminates the
potential for over-fueling the APU
during the start sequence.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other products of this same
type design. We are proposing this AD,
which would require upgrading the
APU FADEC software to version
03.00.000. The proposed AD would
require you to use the service
information described previously to
perform these actions.
Costs of Compliance
We estimate that this proposed AD
would affect 59 Hamilton Sundstrand
Power Systems T–62T–46C12 APUs
installed on airplanes of U.S. registry.
We also estimate that it would take
about three work-hours per APU to
perform the proposed actions, and that
the average labor rate is $80 per workhour. There is no required part cost.
Based on these figures, we estimate the
total cost of the proposed AD to U.S.
operators to be $14,160.
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,
E:\FR\FM\13APP1.SGM
13APP1
Agencies
[Federal Register Volume 74, Number 69 (Monday, April 13, 2009)]
[Proposed Rules]
[Pages 16809-16811]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-8310]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0330; Directorate Identifier 2008-NE-43-AD]
RIN 2120-AA64
Airworthiness Directives; Turbomeca S.A. ARRIUS 2F Turboshaft
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) issued by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as: Rubs between the pipe and the bulkhead may lead to
premature wearing and finally rupture of the P3 air pipe. The loss of
P3 air pressure would then force the fuel control system to idle which
could have a detrimental effect in critical phases of flight. We are
proposing this AD to prevent an uncommanded power loss, which could
result in an emergency autorotation landing or accident.
DATES: We must receive comments on this proposed AD by May 13, 2009.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground
Floor, Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
the same as the Mail address provided in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0330;
Directorate Identifier 2008-NE-43-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this proposed AD. Using the search
function of the Web site, anyone can find and read the comments in any
of our dockets, including, if provided, the name of the individual who
sent the comment (or signed the comment on behalf of an association,
business, labor union, etc.). You may review the DOT's complete Privacy
Act Statement in the Federal Register published on April 11, 2000 (65
FR 19477-78).
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2008-0134R1, dated February 17, 2009, (referred
to after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
[[Page 16810]]
On several ARRIUS 2F engines, the clearance between the P3 air
pipe P/N 0319719180 and the rear right bulkhead P/N 0319998240 has
been found to be too small.
Investigations have shown that both P3 air pipe and rear right
bulkhead were compliant to the design. The Turbomeca Engineering
Department concluded that the tolerance of assembly established
during the design could result in some rubbing between parts.
Rubs between the pipe and the bulkhead may lead to premature
wearing and finally rupture of the P3 air pipe. The loss of P3 air
pressure would then force the fuel control system to idle which
could have a detrimental effect in critical phases of flight.
For the reason stated above, this Airworthiness Directive (AD)
requires the inspection of the P3 air pipe (first section) and RH
rear half-wall and, in case it is found damaged or non-compliant
(idem), the replacement or readjustment of parts.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Turbomeca S.A. has issued Mandatory Service Bulletin (MSB) No. 319
75 4810, dated May 14, 2008. The actions described in this service
information are intended to correct the unsafe condition identified in
the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of France,
and is approved for operation in the United States. Pursuant to our
bilateral agreement with France, they have notified us of the unsafe
condition described in the MCAI and service information referenced
above. We are proposing this AD because we evaluated all information
provided by France and determined the unsafe condition exists and is
likely to exist or develop on other products of the same type design.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 94 engines installed on helicopters of U.S.
registry. We also estimate that it would take about 1 work-hour per
engine to comply with this proposed AD. The average labor rate is $80
per work-hour. Required parts would cost about $705 per engine. Based
on these figures, we estimate the cost of the proposed AD on U.S.
operators to be $73,790. Our cost estimate is exclusive of possible
warranty coverage.
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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
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 regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Turbomeca S.A.: Docket No. FAA-2009-0330; Directorate Identifier
2008-NE-43-AD.
Comments Due Date
(a) We must receive comments by May 13, 2009.
Affected Airworthiness Directives (ADs)
(b) None.
Applicability
(c) This AD applies to Turbomeca S.A. ARRIUS 2F turboshaft
engines with P3 air pipe, part number 0319719180, installed. These
engines are installed on, but not limited to, Eurocopter EC120B
helicopters.
Reason
(d) Rubs between the pipe and the bulkhead may lead to premature
wearing and finally rupture of the P3 air pipe. The loss of P3 air
pressure would then force the fuel control system to idle which
could have a detrimental effect in critical phases of flight. We are
issuing this AD to prevent an uncommanded power loss, which could
result in an emergency autorotation landing or accident.
Actions and Compliance
(e) Unless already done, do the following actions within 100
operating hours after the effective date of this AD. Use paragraphs
2.B.(1) through 2.C.(2) of Turbomeca Mandatory Service Bulletin No.
319 75 4810, dated May 14, 2008.
(1) Visually inspect P3 air pipe (first section) and RH rear
half-wall.
(2) Inspect play between P3 air pipe (first section) and RH rear
half-wall.
(3) Replace P3 air pipe (first section) if any damage is found.
(4) Readjust the first section of the P3 air pipe if the
inspected clearance is found to be not compliant.
(5) If the play after readjusting the first section of the P3
air pipe is still less than 0.5 mm, repeat paragraphs (e)(1) through
(e)(4) of this AD within intervals of 100 hours time-since-last
inspection.
(6) Replace RH rear half-wall if any damage is found.
FAA AD Differences
(f) None.
Other FAA AD Provisions
(g) Alternative Methods of Compliance (AMOCs): The Manager,
Engine Certification Office, FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures found in 14 CFR
39.19.
Related Information
(h) Refer to MCAI EASA Airworthiness Directive 2008-0134R1,
dated February 17, 2009, and Turbomeca S.A. Mandatory Service
Bulletin No. 319 75 4810, dated May 14, 2008, for related
information. Contact Turbomeca, 40220 Tarnos, France; telephone 33
(0)5 59 74 40 00; telex 570 042; fax 33 (0)5 59 74 45 15, for a copy
of this service information.
(i) Contact James Lawrence, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
[[Page 16811]]
England Executive Park, Burlington, MA 01803; e-mail:
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on April 6, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E9-8310 Filed 4-10-09; 8:45 am]
BILLING CODE 4910-13-P