Airworthiness Directives; Turbomeca S.A. Arrius 2F Turboshaft Engines, 37793-37795 [E8-14311]
Download as PDF
<![CDATA[
Federal Register / Vol. 73, No. 128 / Wednesday, July 2, 2008 / Rules and Regulations
Applicability
(c) This AD applies to Hartzell Propeller
Inc. left-hand rotating ( )HC–( )(2,3)Y(K,R)–
2 two- and three-bladed, aluminum hub,
‘‘compact’’ series propellers, with hubs
having a non-suffix serial number (SN), and
lubrication holes located on the shoulder of
the hub blade socket. These propellers are
installed on Lycoming Engines LIO–360
series and LO–360 series reciprocating
engines, installed on Piper Aircraft, Inc.
Seneca PA–34–200 and Seminole PA–44–
180, and Hawker Beechcraft Corporation
Model 76 Duchess, airplanes.
(d) The parentheses appearing in the
propeller model number indicates the
presence or absence of an additional letter(s)
that varies the basic propeller model. This
AD still applies regardless of whether these
letters are present or absent in the propeller
model designation.
Unsafe Condition
(e) This AD results from four reports of
propeller hub cracks, including two in-flight
blade separation events. We are issuing this
AD to prevent failure of the propeller hub,
which could result in blade separation and
loss of control of the airplane.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified unless the
actions have already been done.
Initial Eddy Current Inspection (ECI)
(g) Within 50 hours time-in-service (TIS) or
12 months after the effective date of this AD,
whichever occurs first, perform an initial ECI
of the area around the lubrication holes of the
hub blade sockets.
(h) Use paragraphs 3.A. through 3.A.(3)(d)
of Hartzell Propeller Inc. Alert Service
Bulletin (ASB) No. HC–ASB–61–297,
Revision 1, dated November 14, 2007, to do
the initial ECI.
(i) If any cracks are found, remove the
propeller hub from service before further
flight.
(j) If no cracks are found, mark the
propeller using paragraph 3.A.(5)(a) of the
Accomplishment Instructions of Hartzell
Propeller Inc., ASB No. HC–ASB–61–297,
Revision 1, dated November 14, 2007, to
indicate compliance with this ASB.
mstockstill on PROD1PC66 with RULES
Repetitive ECIs
(k) At repetitive intervals not to exceed 50
hours TIS or 12 months from the previous
ECI, whichever occurs first, perform ECIs of
the area around the lubrication holes of the
hub blade sockets.
(l) Use paragraphs 3.A. through 3.A.(3)(d)
of Hartzell Propeller Inc. ASB No. HC–ASB–
61–297, Revision 1, dated November 14,
2007, to do the repetitive ECIs.
(m) If any cracks are found, remove the
propeller hub from service before further
flight.
Optional Terminating Action
(n) As optional terminating action to the
repetitive ECIs required by this AD, replace
the non-suffix SN propeller hub with a
propeller hub identified by an ‘‘A’’ or ‘‘B’’
suffix letter in the propeller hub SN.
VerDate Aug<31>2005
17:12 Jul 01, 2008
Jkt 214001
37793
(o) Replacement propeller hub part
numbers can be found in paragraph 2.A.,
Material Information, of Hartzell Propeller
Inc. ASB No. HC–SB–61–297, Revision 1,
dated November 14, 2007.
DEPARTMENT OF TRANSPORTATION
Prohibition of Propeller Hub Reuse
[Docket No. FAA–2007–28053; Directorate
Identifier 2007–NE–18–AD; Amendment 39–
15590; AD 2008–13–27]
(p) After the effective date of this AD,
propeller hubs that have a non-suffix SN, or
an ‘‘E’’ suffix letter in the SN removed from
affected propellers in this AD, are not eligible
for installation on any engine in any aircraft.
Previous Credit
(q) ECIs of the propeller hubs done before
the effective date of this AD that use Hartzell
Propeller Inc. ASB No. HC–SB–61–297, dated
September 17, 2007, comply with the
requirements specified in this AD.
Alternative Methods of Compliance
(r) The Manager, Chicago Aircraft
Certification Office, has the authority to
approve alternative methods of compliance
for this AD if requested using the procedures
found in 14 CFR 39.19.
Related Information
(s) Contact Tim Smyth, Senior Aerospace
Engineer, Chicago Aircraft Certification
Office, FAA, Small Airplane Directorate,
2300 East Devon Avenue, Des Plaines, IL
60018–4696; e-mail: timothy.smyth@faa.gov;
telephone (847) 294–8110; fax (847) 294–
7132, for more information about this AD.
Material Incorporated by Reference
(t) You must use Hartzell Propeller Inc.
Alert Service Bulletin No. HC–ASB–61–297,
Revision 1, dated November 14, 2007, to
perform the ECIs 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 Hartzell Propeller
Inc. Technical Publications Department, One
Propeller Place, Piqua, OH 45356; telephone
(937) 778–4200; fax (937) 778–4391, for a
copy of this service information. 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.
Issued in Burlington, Massachusetts, on
June 19, 2008.
Diane Cook,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E8–14312 Filed 7–1–08; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; Turbomeca
S.A. Arrius 2F Turboshaft Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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:
This AD is issued following a case of noncommanded in-flight engine shut-down
which occurred on an ARRIUS 2F turboshaft
engine, following the seizing of the gas
generator. The result may be an emergency
autorotation landing or, at worst, an accident.
Investigations of this event have revealed
that the seizing of the gas generator was
caused by the fracture of the separator cage
of the gas generator front bearing, due to
high-cycle fatigue cracks initiated in the
lubrication slots of the separator cage.
We are issuing this AD to prevent
uncommanded shutdown of the engine,
which could lead to an accident.
DATES: This AD becomes effective
August 6, 2008. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD as of
August 6, 2008.
ADDRESSES: The Docket Operations
office is located at Docket Management
Facility, U.S. Department of
Transportation, 1200 New Jersey
Avenue, SE., West Building Ground
Floor, Room W12–140, Washington, DC
20590–0001.
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
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
Frm 00019
Fmt 4700
Sfmt 4700
E:\FR\FM\02JYR1.SGM
02JYR1
37794
Federal Register / Vol. 73, No. 128 / Wednesday, July 2, 2008 / Rules and Regulations
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on August 28, 2007 (72 FR
49236). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states that:
This AD is issued following a case of noncommanded in-flight engine shut-down
which occurred on an Arrius 2F turboshaft
engine, following the seizing of the gas
generator. The result may be an emergency
autorotation landing, or, at worst, an
accident.
Investigations of this event have revealed
that the seizing of the gas generator was
caused by the fracture of the separator cage
of the gas generator front bearing, due to
high-cycle fatigue cracks initiated in the
lubrication slots of the separator cage.
Modification Tf 12 introduces a new gas
generator front bearing without lubrication
slots on the separator cage.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Change to the Compliance End Date
We have changed the compliance
time from ‘‘at the next shop visit after
the effective date of the AD, but no later
than April 30, 2008’’ to ‘‘at the next
shop visit after the effective date of this
AD, but no later than 30 days after the
effective date of this AD’’ to allow the
operators more time to complete the
requirements of this AD.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We determined that these changes will
not increase the economic burden on
any operator or increase the scope of the
AD.
mstockstill on PROD1PC66 with RULES
Differences Between This AD and the
MCAI or Service Information
The Mandatory Continuing
Airworthiness Information (MCAI) and
service information require the
operators to comply with the
requirements at the next shop visit after
the effective date of the AD, but no later
than April 30, 2008. We require
compliance at the next shop visit after
the effective date of this AD, but no later
than 30 days after the effective date of
this AD.
Costs of Compliance
We estimate that this AD will affect
61 engines of U.S. registry. We also
estimate that it will take about 10 work-
VerDate Aug<31>2005
17:12 Jul 01, 2008
Jkt 214001
hours per engine to comply with this
AD. The average labor rate is $80 per
work-hour. Required parts will cost
about $111,440. Based on these figures,
we estimate the cost of this AD to the
U.S. operators to be $6,846,640. 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 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.
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
PO 00000
Frm 00020
Fmt 4700
Sfmt 4700
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is provided in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
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 AD:
I
2008–13–27 Turbomeca S.A.: Amendment
39–15590. Docket No. FAA–2007–28053;
Directorate Identifier 2007–NE–18–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective August 6, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Turbomeca S.A.
Arrius 2F turboshaft engines that have not
incorporated Turbomeca Modification Tf
12A. These engines are installed on, but not
limited to, Eurocopter EC120B helicopters.
Reason
(d) European Aviation Safety Agency
(EASA) AD No. 2007–0057, dated March 1,
2007, states:
This AD is issued following a case of noncommanded in-flight engine shut-down
which occurred on an Arrius 2F turboshaft
engine, following the seizing of the gas
generator. The result may be an emergency
autorotation landing, or, at worst, an
accident.
Investigations of this event have revealed
that the seizing of the gas generator was
caused by the fracture of the separator cage
of the gas generator front bearing, due to
high-cycle fatigue cracks initiated in the
lubrication slots of the separator cage.
Modification Tf12 introduces a new gas
generator front bearing without lubrication
slots on the separator cage.
We are issuing this AD to prevent
uncommanded shutdown of the engine,
which could lead to an accident.
Actions and Compliance
(e) Unless already done, do the following
actions.
E:\FR\FM\02JYR1.SGM
02JYR1
Federal Register / Vol. 73, No. 128 / Wednesday, July 2, 2008 / Rules and Regulations
(1) At the next engine shop visit after the
effective date of this AD, but no later than 30
days after the effective date of this AD,
replace the engine module 02 with a module
that incorporates Turbomeca Modification Tf
12A. Turbomeca Modification Tf 12A installs
into the engine module 02 a new gas
generator front bearing without lubrication
slots on the separator cage.
(2) Use the Instructions to be Incorporated
section of Turbomeca Mandatory Service
Bulletin No. 319 72 4012, Update No. 1,
dated September 19, 2006, to do the actions
in paragraph (e)(1) of this AD.
DEPARTMENT OF TRANSPORTATION
FAA AD Differences
AGENCY:
(f) The Mandatory Continuing
Airworthiness Information (MCAI) and
service information require the operators to
comply with the requirements at the next
shop visit after the effective date of the AD,
but no later than April 30, 2008. We require
compliance at the next shop visit after the
effective date of this AD, but no later than 30
days after the effective date of this AD.
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 EASA AD 2007–0057, dated
March 1, 2007, for related information.
(i) 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
mstockstill on PROD1PC66 with RULES
(j) You must use Turbomeca Mandatory
Service Bulletin No. 319 72 4012, Update No.
1, dated September 19, 2006, 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/ibrlocations.html.
Issued in Burlington, Massachusetts, on
June 18, 2008.
Diane Cook,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E8–14311 Filed 7–1–08; 8:45 am]
BILLING CODE 4910–13–P
VerDate Aug<31>2005
17:12 Jul 01, 2008
Jkt 214001
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0297; Directorate
Identifier 2007–NM–330–AD; Amendment
39–15586; AD 2008–13–23]
RIN 2120–AA64
Airworthiness Directives; Dornier
Model 328–100 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated 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 maintenance water has been found
in the elevator [assembly].
The unsafe condition is water or ice
accumulating in the elevator assembly,
which could result in corrosion and
consequent reduced structural integrity
of the flight control surface, or an
unbalanced flight control surface. These
conditions could result in reduced
controllability of the airplane. We are
issuing this AD to require actions to
correct the unsafe condition on these
products.
This AD becomes effective
August 6, 2008. The Director of the
Federal Register approved the
incorporation by reference of a certain
publication listed in this AD as of
August 6, 2008.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–2125;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
DATES:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
37795
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on March 13, 2008 (73 FR
13503). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
During maintenance water has been found
in the elevator [assembly].
The unsafe condition is water or ice
accumulating in the elevator assembly,
which could result in corrosion and
consequent reduced structural integrity
of the flight control surface, or an
unbalanced flight control surface. These
conditions could result in reduced
controllability of the airplane. You may
obtain further information by examining
the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
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 might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
about 12 products of U.S. registry. We
also estimate that it will take about 2
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $80 per work-hour.
Required parts will cost about $100 per
product. Where the service information
lists required parts costs that are
covered under warranty, we have
assumed that there will be no charge for
these parts. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. Based on these
E:\FR\FM\02JYR1.SGM
02JYR1
]]>Agencies
[Federal Register Volume 73, Number 128 (Wednesday, July 2, 2008)]
[Rules and Regulations]
[Pages 37793-37795]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-14311]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28053; Directorate Identifier 2007-NE-18-AD;
Amendment 39-15590; AD 2008-13-27]
RIN 2120-AA64
Airworthiness Directives; Turbomeca S.A. Arrius 2F Turboshaft
Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
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:
This AD is issued following a case of non-commanded in-flight
engine shut-down which occurred on an ARRIUS 2F turboshaft engine,
following the seizing of the gas generator. The result may be an
emergency autorotation landing or, at worst, an accident.
Investigations of this event have revealed that the seizing of
the gas generator was caused by the fracture of the separator cage
of the gas generator front bearing, due to high-cycle fatigue cracks
initiated in the lubrication slots of the separator cage.
We are issuing this AD to prevent uncommanded shutdown of the engine,
which could lead to an accident.
DATES: This AD becomes effective August 6, 2008. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in this AD as of August 6, 2008.
ADDRESSES: The Docket Operations office is located at Docket Management
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue,
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.
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
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
[[Page 37794]]
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on August 28, 2007 (72
FR 49236). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states that:
This AD is issued following a case of non-commanded in-flight
engine shut-down which occurred on an Arrius 2F turboshaft engine,
following the seizing of the gas generator. The result may be an
emergency autorotation landing, or, at worst, an accident.
Investigations of this event have revealed that the seizing of
the gas generator was caused by the fracture of the separator cage
of the gas generator front bearing, due to high-cycle fatigue cracks
initiated in the lubrication slots of the separator cage.
Modification Tf 12 introduces a new gas generator front bearing
without lubrication slots on the separator cage.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Change to the Compliance End Date
We have changed the compliance time from ``at the next shop visit
after the effective date of the AD, but no later than April 30, 2008''
to ``at the next shop visit after the effective date of this AD, but no
later than 30 days after the effective date of this AD'' to allow the
operators more time to complete the requirements of this AD.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
The Mandatory Continuing Airworthiness Information (MCAI) and
service information require the operators to comply with the
requirements at the next shop visit after the effective date of the AD,
but no later than April 30, 2008. We require compliance at the next
shop visit after the effective date of this AD, but no later than 30
days after the effective date of this AD.
Costs of Compliance
We estimate that this AD will affect 61 engines of U.S. registry.
We also estimate that it will take about 10 work-hours per engine to
comply with this AD. The average labor rate is $80 per work-hour.
Required parts will cost about $111,440. Based on these figures, we
estimate the cost of this AD to the U.S. operators to be $6,846,640.
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 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.
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 provided in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
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:
2008-13-27 Turbomeca S.A.: Amendment 39-15590. Docket No. FAA-2007-
28053; Directorate Identifier 2007-NE-18-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective August
6, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Turbomeca S.A. Arrius 2F turboshaft
engines that have not incorporated Turbomeca Modification Tf 12A.
These engines are installed on, but not limited to, Eurocopter
EC120B helicopters.
Reason
(d) European Aviation Safety Agency (EASA) AD No. 2007-0057,
dated March 1, 2007, states:
This AD is issued following a case of non-commanded in-flight
engine shut-down which occurred on an Arrius 2F turboshaft engine,
following the seizing of the gas generator. The result may be an
emergency autorotation landing, or, at worst, an accident.
Investigations of this event have revealed that the seizing of
the gas generator was caused by the fracture of the separator cage
of the gas generator front bearing, due to high-cycle fatigue cracks
initiated in the lubrication slots of the separator cage.
Modification Tf12 introduces a new gas generator front bearing
without lubrication slots on the separator cage.
We are issuing this AD to prevent uncommanded shutdown of the
engine, which could lead to an accident.
Actions and Compliance
(e) Unless already done, do the following actions.
[[Page 37795]]
(1) At the next engine shop visit after the effective date of
this AD, but no later than 30 days after the effective date of this
AD, replace the engine module 02 with a module that incorporates
Turbomeca Modification Tf 12A. Turbomeca Modification Tf 12A
installs into the engine module 02 a new gas generator front bearing
without lubrication slots on the separator cage.
(2) Use the Instructions to be Incorporated section of Turbomeca
Mandatory Service Bulletin No. 319 72 4012, Update No. 1, dated
September 19, 2006, to do the actions in paragraph (e)(1) of this
AD.
FAA AD Differences
(f) The Mandatory Continuing Airworthiness Information (MCAI)
and service information require the operators to comply with the
requirements at the next shop visit after the effective date of the
AD, but no later than April 30, 2008. We require compliance at the
next shop visit after the effective date of this AD, but no later
than 30 days after the effective date of this AD.
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 EASA AD 2007-0057, dated March 1, 2007, for related
information.
(i) 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
(j) You must use Turbomeca Mandatory Service Bulletin No. 319 72
4012, Update No. 1, dated September 19, 2006, 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.
Issued in Burlington, Massachusetts, on June 18, 2008.
Diane Cook,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-14311 Filed 7-1-08; 8:45 am]
BILLING CODE 4910-13-P
