Airworthiness Directives; Turbomeca Arriel 1B, 1D, 1D1, 2B, and 2B1 Turboshaft Engines, 17075-17077 [E9-8329]
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17075
Rules and Regulations
Federal Register
Vol. 74, No. 70
Tuesday, April 14, 2009
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0302; Directorate
Identifier 2009–NE–09–AD; Amendment 39–
15881; AD 2009–08–08]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
Arriel 1B, 1D, 1D1, 2B, and 2B1
Turboshaft Engines
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
Examining the AD Docket
We are adopting a new
airworthiness directive (AD) for the
products listed above. This 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:
SUMMARY:
During production of Arriel 1 and Arriel 2
power turbine (PT) wheels, geometric nonconformances on blade fir tree roots have
been detected by Turbomeca. Potentially
non-conforming PT blades have been traced
as having been installed on Module M04 (PT)
listed in Alert Mandatory Service Bulletin
(MSB) A292 72 0827 for Arriel 1 engines and
A292 72 2833 for Arriel 2 engines. The
geometric non-conformities of the blades may
potentially lead to a reduction in the fatigue
resistance of PT blades to a lower level than
their authorized in service use limit. This
reduction of fatigue resistance can potentially
result in blade release, which could cause an
uncommanded in-flight shutdown.
Uncommanded in-flight shutdown
could result in an emergency
autorotation landing. We are issuing this
AD to prevent release of PT blades,
which could result in uncommanded inflight shutdown and emergency
autorotation landing.
VerDate Nov<24>2008
15:32 Apr 13, 2009
Jkt 217001
DATES: This AD becomes effective April
29, 2009.
We must receive comments on this
AD by May 14, 2009.
The Director of the Federal Register
approved the incorporation by reference
of Turbomeca Alert Mandatory Service
Bulletin (MSB) No. A292 72 0827,
Version A, dated March 20, 2009, and
Turbomeca Alert MSB No. A292 72
0827, Version A, dated March 20, 2009,
listed in the AD as of April 29, 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: 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.
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 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:
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 2009–0068–E,
dated March 25, 2009 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
PO 00000
Frm 00001
Fmt 4700
Sfmt 4700
condition for the specified products.
The MCAI states:
During production of Arriel 1 and Arriel 2
power turbine (PT) wheels, geometric nonconformances on blade fir tree roots have
been detected by Turbomeca. Potentially
non-conforming PT blades have been traced
as having been installed on Module M04 (PT)
listed in Alert MSB A292 72 0827 for Arriel
1 engines and A292 72 2833 for Arriel 2
engines. The geometric non-conformities of
the blades may potentially lead to a
reduction in the fatigue resistance of PT
blades to a lower level than their authorized
in service use limit. This reduction of fatigue
resistance can potentially result in blade
release, which could cause an uncommanded
in-flight shutdown.
Uncommanded in-flight shutdown
could result in an emergency
autorotation landing. You may obtain
further information by examining the
MCAI in the AD docket.
Relevant Service Information
Turbomeca has issued Alert MSB No.
A292 72 0827, Version A, dated March
20, 2009, for Arriel 1 series turboshaft
engines, and issued Alert MSB No.
A292 72 2833, Version A, dated March
20, 2009, for Arriel 2 series turboshaft
engines. The power turbine modules
M04 having the affected PT blades, are
listed by serial number (SN) in Figure 1
of these MSBs, as applicable. We have
incorporated by reference these MSBs to
identify the affected parts.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we required different actions in this AD
from those in the MCAI in order to
follow FAA policies. Any such
differences are described in a separate
paragraph of the AD. These
requirements take precedence over the
actions copied from the MCAI.
FAA’s Determination and Requirements
of This 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
issuing this AD because we evaluated
all information provided by EASA and
determined the unsafe condition exists
E:\FR\FM\14APR1.SGM
14APR1
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Federal Register / Vol. 74, No. 70 / Tuesday, April 14, 2009 / Rules and Regulations
and is likely to exist or develop on other
products of the same type design. This
AD requires removing the affected PT
blades from service.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because depending on the number
of cycles already accumulated on some
engines, the actions specified in this AD
might require immediate incorporation
before further flight. Therefore, we
determined that notice and opportunity
for public comment before issuing this
AD are impracticable and that good
cause exists for making this amendment
effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2009–0302;
Directorate Identifier 2009–NE–09–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because 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 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).
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.
VerDate Nov<24>2008
15:32 Apr 13, 2009
Jkt 217001
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 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 this AD:
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 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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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:
■
2009–08–08 Turbomeca: Amendment 39–
15881; Docket No. FAA–2009–0302;
Directorate Identifier 2009–NE–09–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective April 29, 2009.
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
Affected ADs
(b) None.
Applicability
(c) This AD applies to:
(1) Turbomeca Arriel 1B, 1D, and 1D1
turboshaft engines with the power turbine
modules M04 installed, as listed by serial
number (SN) in Figure 1 of Turbomeca Alert
Mandatory Service Bulletin (MSB) No. A292
72 0827, Version A, dated March 20, 2009;
and
(2) Turbomeca Arriel 2B, and 2B1
turboshaft engines with the power turbine
modules M04 installed, as listed by SN in
Figure 1 of Turbomeca Alert MSB No. A292
72 2833, Version A, dated March 20, 2009.
(3) These engines are installed on, but not
limited to, Eurocopter AS 350 B, AS 350 BA,
AS 350 B1, AS 350 B2, AS 350 B3, and EC
130 B4 helicopters.
Reason
(d) European Aviation Safety Agency
(EASA) AD No. 2009–0068–E, dated March
25, 2009, states:
During production of Arriel 1 and Arriel 2
power turbine (PT) wheels, geometric nonconformances on blade fir tree roots have
been detected by Turbomeca. Potentially
non-conforming PT blades have been traced
as having been installed on Module M04 (PT)
listed in Alert MSB A292 72 0827 for Arriel
1 engines and A292 72 2833 for Arriel 2
engines. The geometric non-conformities of
the blades may potentially lead to a
reduction in the fatigue resistance of PT
blades to a lower level than their authorized
in service use limit. This reduction of fatigue
resistance can potentially result in blade
release, which could cause an uncommanded
in-flight shutdown.
Uncommanded in-flight shutdown could
result in an emergency autorotation landing.
We are issuing this AD to prevent release of
PT blades, which could result in
uncommanded in-flight shutdown and
emergency autorotation landing.
Actions and Compliance
(e) Unless already done, do the following
actions.
(1) For engines with an affected Module
M04 (PT module) which has accumulated
1,000 total PT cycles or more on the effective
date of this AD, remove the PT blades from
service before further flight.
(2) For engines with an affected Module
M04 (PT module) which has accumulated
fewer than 1,000 total PT cycles on the
effective date of this AD, remove the PT
blades from service before accumulating
1,000 total PT cycles.
(3) After the effective date of this AD, do
not install any PT blades removed as
specified in paragraph (e)(1) or (e)(2) of this
AD, into any engine.
FAA AD Differences
(f) Although the compliance section of
EASA AD No. 2009–0068–E, dated March 25,
2009, states to replace the Module M04, or
PT wheel assembly, or PT blades, this AD
states to remove the PT blades from service.
(g) Although EASA AD No. 2009–0068–E,
dated March 25, 2009, applies to the Arriel
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14APR1
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Federal Register / Vol. 74, No. 70 / Tuesday, April 14, 2009 / Rules and Regulations
2B1A engine, this AD does not apply to that
model because it has no U.S. type certificate.
Alternative Methods of Compliance
(AMOCs)
(h) 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.
(j) 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, for more information about this AD.
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Turbomeca, 40220 Tarnos,
France; telephone 33 05 59 74 40 00, fax 33
05 59 74 45 15.
(3) You may review copies at the FAA,
New England Region, 12 New England
Executive Park, Burlington, MA; 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/cfr/ibrlocations.html.
Material Incorporated by Reference
(k) You must use the service information
specified in Table 1 of this AD to do the
actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Related Information
(i) Refer to MCAI EASA Airworthiness
Directive 2009–0068–E, dated March 25,
2009, for related information.
TABLE 1—MATERIAL INCORPORATED BY REFERENCE
Turbomeca Alert Mandatory Service Bulletin No.
Page
Version
A292 72 0827 .....................................................................................................................
Total pages: 17
A292 72 2833 .....................................................................................................................
Total Pages: 17
All .................
A ...................
March 20, 2009.
All .................
A ...................
March 20, 2009.
Issued in Burlington, Massachusetts, on
April 6, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E9–8329 Filed 4–13–09; 8:45 am]
and ODP is specified in the amendatory
provisions.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of April 14,
2009.
BILLING CODE 4910–13–P
Availability of matter
incorporated by reference in the
amendment is as follows:
For Examination—
1. FAA Rules Docket, FAA
Headquarters Building, 800
Independence Avenue, SW.,
Washington, DC 20591;
2. The FAA Regional Office of the
region in which the affected airport is
located;
3. The National Flight Procedures
Office, 6500 South MacArthur Blvd.,
Oklahoma City, OK 73169 or,
4. 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.
Availability—All SIAPs are available
online free of charge. Visit nfdc.faa.gov
to register. Additionally, individual
SIAP and Takeoff Minimums and ODP
copies may be obtained from:
1. FAA Public Inquiry Center (APA–
200), FAA Headquarters Building, 800
Independence Avenue, SW.,
Washington, DC 20591; or
2. The FAA Regional Office of the
region in which the affected airport is
located.
ADDRESSES:
DEPARTMENT OF TRANSPORTATION
14 CFR Part 97
[Docket No. 30661; Amdt. No. 3317]
Standard Instrument Approach
Procedures, and Takeoff Minimums
and Obstacle Departure Procedures;
Miscellaneous Amendments
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: This rule establishes, amends,
suspends, or revokes Standard
Instrument Approach Procedures
(SIAPs) and associated Takeoff
Minimums and Obstacle Departure
Procedures for operations at certain
airports. These regulatory actions are
needed because of the adoption of new
or revised criteria, or because of changes
occurring in the National Airspace
System, such as the commissioning of
new navigational facilities, adding new
obstacles, or changing air traffic
requirements. These changes are
designed to provide safe and efficient
use of the navigable airspace and to
promote safe flight operations under
instrument flight rules at the affected
airports.
DATES: This rule is effective April 14,
2009. The compliance date for each
SIAP, associated Takeoff Minimums,
VerDate Nov<24>2008
15:32 Apr 13, 2009
Jkt 217001
FOR FURTHER INFORMATION CONTACT:
Harry J. Hodges, Flight Procedure
Standards Branch (AFS–420) Flight
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
Date
Technologies and Programs Division,
Flight Standards Service, Federal
Aviation Administration, Mike
Monroney Aeronautical Center, 6500
South MacArthur Blvd., Oklahoma City,
OK 73169 (Mail Address: P.O. Box
25082 Oklahoma City, OK 73125)
telephone: (405) 954–4164.
This rule
amends Title 14, Code of Federal
Regulations, Part 97 (14 CFR part 97) by
amending the referenced SIAPs. The
complete regulatory description of each
SIAP is listed on the appropriate FAA
Form 8260, as modified by the National
Flight Data Center (FDC)/Permanent
Notice to Airmen (P–NOTAM), and is
incorporated by reference in the
amendment under 5 U.S.C. 552(a), 1
CFR part 51, and § 97.20 of Title 14 of
the Code of Federal Regulations.
The large number of SIAPs, their
complex nature, and the need for a
special format make their verbatim
publication in the Federal Register
expensive and impractical. Further,
airmen do not use the regulatory text of
the SIAPs, but refer to their graphic
depiction on charts printed by
publishers of aeronautical materials.
Thus, the advantages of incorporation
by reference are realized and
publication of the complete description
of each SIAP contained in FAA form
documents is unnecessary. This
amendment provides the affected CFR
sections and specifies the types of SIAP
and the corresponding effective dates.
This amendment also identifies the
airport and its location, the procedure
and the amendment number.
SUPPLEMENTARY INFORMATION:
E:\FR\FM\14APR1.SGM
14APR1
Agencies
[Federal Register Volume 74, Number 70 (Tuesday, April 14, 2009)]
[Rules and Regulations]
[Pages 17075-17077]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-8329]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 74, No. 70 / Tuesday, April 14, 2009 / Rules
and Regulations
[[Page 17075]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0302; Directorate Identifier 2009-NE-09-AD;
Amendment 39-15881; AD 2009-08-08]
RIN 2120-AA64
Airworthiness Directives; Turbomeca Arriel 1B, 1D, 1D1, 2B, and
2B1 Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This 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:
During production of Arriel 1 and Arriel 2 power turbine (PT)
wheels, geometric non-conformances on blade fir tree roots have been
detected by Turbomeca. Potentially non-conforming PT blades have
been traced as having been installed on Module M04 (PT) listed in
Alert Mandatory Service Bulletin (MSB) A292 72 0827 for Arriel 1
engines and A292 72 2833 for Arriel 2 engines. The geometric non-
conformities of the blades may potentially lead to a reduction in
the fatigue resistance of PT blades to a lower level than their
authorized in service use limit. This reduction of fatigue
resistance can potentially result in blade release, which could
cause an uncommanded in-flight shutdown.
Uncommanded in-flight shutdown could result in an emergency
autorotation landing. We are issuing this AD to prevent release of PT
blades, which could result in uncommanded in-flight shutdown and
emergency autorotation landing.
DATES: This AD becomes effective April 29, 2009.
We must receive comments on this AD by May 14, 2009.
The Director of the Federal Register approved the incorporation by
reference of Turbomeca Alert Mandatory Service Bulletin (MSB) No. A292
72 0827, Version A, dated March 20, 2009, and Turbomeca Alert MSB No.
A292 72 0827, Version A, dated March 20, 2009, listed in the AD as of
April 29, 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: 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 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:
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 2009-0068-E, dated March 25, 2009 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
During production of Arriel 1 and Arriel 2 power turbine (PT)
wheels, geometric non-conformances on blade fir tree roots have been
detected by Turbomeca. Potentially non-conforming PT blades have
been traced as having been installed on Module M04 (PT) listed in
Alert MSB A292 72 0827 for Arriel 1 engines and A292 72 2833 for
Arriel 2 engines. The geometric non-conformities of the blades may
potentially lead to a reduction in the fatigue resistance of PT
blades to a lower level than their authorized in service use limit.
This reduction of fatigue resistance can potentially result in blade
release, which could cause an uncommanded in-flight shutdown.
Uncommanded in-flight shutdown could result in an emergency
autorotation landing. You may obtain further information by examining
the MCAI in the AD docket.
Relevant Service Information
Turbomeca has issued Alert MSB No. A292 72 0827, Version A, dated
March 20, 2009, for Arriel 1 series turboshaft engines, and issued
Alert MSB No. A292 72 2833, Version A, dated March 20, 2009, for Arriel
2 series turboshaft engines. The power turbine modules M04 having the
affected PT blades, are listed by serial number (SN) in Figure 1 of
these MSBs, as applicable. We have incorporated by reference these MSBs
to identify the affected parts.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we required different actions
in this AD from those in the MCAI in order to follow FAA policies. Any
such differences are described in a separate paragraph of the AD. These
requirements take precedence over the actions copied from the MCAI.
FAA's Determination and Requirements of This 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 issuing this AD because we evaluated all information
provided by EASA and determined the unsafe condition exists
[[Page 17076]]
and is likely to exist or develop on other products of the same type
design. This AD requires removing the affected PT blades from service.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
depending on the number of cycles already accumulated on some engines,
the actions specified in this AD might require immediate incorporation
before further flight. Therefore, we determined that notice and
opportunity for public comment before issuing this AD are impracticable
and that good cause exists for making this amendment effective in fewer
than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2009-0302; Directorate
Identifier 2009-NE-09-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because 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 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).
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 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 this AD:
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 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.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2009-08-08 Turbomeca: Amendment 39-15881; Docket No. FAA-2009-0302;
Directorate Identifier 2009-NE-09-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April
29, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to:
(1) Turbomeca Arriel 1B, 1D, and 1D1 turboshaft engines with the
power turbine modules M04 installed, as listed by serial number (SN)
in Figure 1 of Turbomeca Alert Mandatory Service Bulletin (MSB) No.
A292 72 0827, Version A, dated March 20, 2009; and
(2) Turbomeca Arriel 2B, and 2B1 turboshaft engines with the
power turbine modules M04 installed, as listed by SN in Figure 1 of
Turbomeca Alert MSB No. A292 72 2833, Version A, dated March 20,
2009.
(3) These engines are installed on, but not limited to,
Eurocopter AS 350 B, AS 350 BA, AS 350 B1, AS 350 B2, AS 350 B3, and
EC 130 B4 helicopters.
Reason
(d) European Aviation Safety Agency (EASA) AD No. 2009-0068-E,
dated March 25, 2009, states:
During production of Arriel 1 and Arriel 2 power turbine (PT)
wheels, geometric non-conformances on blade fir tree roots have been
detected by Turbomeca. Potentially non-conforming PT blades have
been traced as having been installed on Module M04 (PT) listed in
Alert MSB A292 72 0827 for Arriel 1 engines and A292 72 2833 for
Arriel 2 engines. The geometric non-conformities of the blades may
potentially lead to a reduction in the fatigue resistance of PT
blades to a lower level than their authorized in service use limit.
This reduction of fatigue resistance can potentially result in blade
release, which could cause an uncommanded in-flight shutdown.
Uncommanded in-flight shutdown could result in an emergency
autorotation landing. We are issuing this AD to prevent release of
PT blades, which could result in uncommanded in-flight shutdown and
emergency autorotation landing.
Actions and Compliance
(e) Unless already done, do the following actions.
(1) For engines with an affected Module M04 (PT module) which
has accumulated 1,000 total PT cycles or more on the effective date
of this AD, remove the PT blades from service before further flight.
(2) For engines with an affected Module M04 (PT module) which
has accumulated fewer than 1,000 total PT cycles on the effective
date of this AD, remove the PT blades from service before
accumulating 1,000 total PT cycles.
(3) After the effective date of this AD, do not install any PT
blades removed as specified in paragraph (e)(1) or (e)(2) of this
AD, into any engine.
FAA AD Differences
(f) Although the compliance section of EASA AD No. 2009-0068-E,
dated March 25, 2009, states to replace the Module M04, or PT wheel
assembly, or PT blades, this AD states to remove the PT blades from
service.
(g) Although EASA AD No. 2009-0068-E, dated March 25, 2009,
applies to the Arriel
[[Page 17077]]
2B1A engine, this AD does not apply to that model because it has no
U.S. type certificate.
Alternative Methods of Compliance (AMOCs)
(h) 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
(i) Refer to MCAI EASA Airworthiness Directive 2009-0068-E,
dated March 25, 2009, for related information.
(j) 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, for more information about this AD.
Material Incorporated by Reference
(k) You must use the service information specified in Table 1 of
this AD to do the actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33
05 59 74 45 15.
(3) You may review copies at the FAA, New England Region, 12 New
England Executive Park, Burlington, MA; 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/cfr/ibr-locations.html.
Table 1--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Turbomeca Alert Mandatory Service
Bulletin No. Page Version Date
----------------------------------------------------------------------------------------------------------------
A292 72 0827..................... All.................. A.................... March 20, 2009.
Total pages: 17
A292 72 2833..................... All.................. A.................... March 20, 2009.
Total Pages: 17
----------------------------------------------------------------------------------------------------------------
Issued in Burlington, Massachusetts, on April 6, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E9-8329 Filed 4-13-09; 8:45 am]
BILLING CODE 4910-13-P