Airworthiness Directives; Turbomeca Arriel 1B, 1D, 1D1, and 1S1 Turboshaft Engines, 15866-15868 [E8-5819]
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15866
Federal Register / Vol. 73, No. 59 / Wednesday, March 26, 2008 / Rules and Regulations
in-flight checks of instrument accuracy,
including:
• Preflight check of the accuracy of both
the primary and backup altimeter against
known airfield elevation and against each
other.
• Verification of airspeed indications
consistent with prevailing conditions at
startup, during taxi, and prior to takeoff.
• ‘‘Airspeed alive’’ check and reasonable
indications during takeoff roll.
• Maintenance of current altimeter setting
in both primary and backup altimeters.
• Cross-check of primary and backup
altimeters at each change of altimeter setting
and prior to entering instrument
meteorological conditions (IMC).
• Cross-check of primary and backup
altimeters and validation against other
available data, such as glideslope intercept
altitude, prior to conducting any instrument
approach.
• Periodic cross-checks of primary and
backup airspeed indicators, preferably in
combination with altimeter cross-checks.
For flight operations under instrument
flight rules (IFR) or in conditions in which
visual reference to the horizon cannot be
reliably maintained (that is IMC, night
operations, flight operations over water, in
haze or smoke) and the pilot has reasons to
suspect that any source (PFD or back-up
instruments) of attitude, airspeed, or altitude
is not functioning properly, flight under IFR
or in these conditions must not be initiated
(when condition is determined on the
ground) and further flight under IFR or in
these conditions is prohibited until
equipment is serviced and functioning
properly.
Operation of aircraft not equipped with
operating backup (or standby) attitude,
altimeter, and airspeed indicators that are
located where they are readily visible to the
pilot is prohibited.
Pilots must frequently scan and crosscheck
flight instruments to make sure the
information depicted on the PFD correlates
and agrees with the information depicted on
the backup instruments.
Issued in Kansas City, Missouri, on March
13, 2008.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–5701 Filed 3–25–08; 8:45 am]
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BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21242; Directorate
Identifier 2005–NE–09–AD; Amendment 39–
15442; AD 2008–07–01]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
Arriel 1B, 1D, 1D1, and 1S1 Turboshaft
Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
certain Turbomeca Arriel 1B, 1D, 1D1,
and 1S1 turboshaft engines. That AD
currently requires initial and repetitive
position checks of the gas generator 2nd
stage turbine blades on all Turbomeca
Arriel 1B, 1D, 1D1, and 1S1 turboshaft
engines. That AD also currently requires
initial and repetitive replacements of
2nd stage turbines on 1B, 1D, and 1D1
engines only. This AD requires adding
a 3,000 hour life limit to Arriel 1B 2nd
stage turbine blades. This AD results
from reports of failures of second stage
turbine blades. We are issuing this AD
to prevent failures of the 2nd stage
turbine blades, which could result in
uncommanded in-flight engine
shutdown, and subsequent forced
autorotation landing or accident.
DATES: This AD becomes effective April
30, 2008. The Director of the Federal
Register approved the incorporation by
reference of certain publications listed
in the regulations as of April 30, 2008.
The Director of the Federal Register
previously approved the incorporation
by reference of Turbomeca Mandatory
Alert Service Bulletins A292 72 0809,
Update 1, dated October 4, 2005; and
A292 72 0810, dated March 24, 2004; as
of February 28, 2006 (71 FR 3754,
January 24, 2006).
ADDRESSES: You can get the service
information identified in this AD from
Turbomeca, 40220 Tarnos, France;
telephone (33) 05 59 74 40 00, fax (33)
05 59 74 45 15.
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
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
England Executive Park, Burlington, MA
01803; e-mail: james.lawrence@faa.gov;
telephone (781) 238–7176, fax (781)
238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 by
superseding AD 2006–02–08R1,
Amendment 39–14721 (71 FR 46390,
August 14, 2006), with a proposed AD.
The proposed AD applies to certain
Turbomeca Arriel 1B, 1D, 1D1, and 1S1
turboshaft engines. We published the
proposed AD in the Federal Register on
March 9, 2007 (72 FR 10622). That
action proposed to require:
• Initial and repetitive position
checks of the 2nd stage turbine blades
on Turbomeca Arriel 1B, 1D, 1D1, and
1S1 turboshaft engines.
• Replacement of 2nd stage turbines
on 1B and 1D1 engines only.
• Initially replacing 2nd stage
turbines in Arriel 1B, 1D, and 1D1
turboshaft engines.
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.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the proposal or on the
determination of the cost to the public.
Addition of an Optional Terminating
Action
We have added to the AD, an option
to terminate the repetitive position
check requirements by installing a new
turbine, part number (P/N) 0 292 25 039
0.
Correction of a Typographical Error in
the Costs of Compliance
We corrected the number of turbine
replacements in the Costs of
Compliance from 587 to 571, and
changed the total cost from $3,905,240
to $3,769,760.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed.
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Federal Register / Vol. 73, No. 59 / Wednesday, March 26, 2008 / Rules and Regulations
Costs of Compliance
We estimate that this AD will affect
721 engines installed on helicopters of
U.S. registry. We also estimate that it
will take about 2 work-hours per engine
to inspect all 721 engines and 40 workhours per engine to replace about 571
2nd stage turbines on 1B and 1D1
engines, and that the average labor rate
is $80 per work-hour. Required parts
would cost about $3,200 per engine.
Based on these figures, we estimate the
total cost of the AD to U.S. operators to
be $3,769,760.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary at the address listed
under ADDRESSES.
15867
Effective Date
(a) This airworthiness directive (AD)
becomes effective April 30, 2008.
Affected ADs
(b) This AD supersedes AD 2006–02–08R1,
Amendment 39–14721 (71 FR 46390, August
14, 2006).
Applicability
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
(c) This AD applies to Turbomeca Arriel 1B
engines fitted with 2nd stage turbine
modification TU 148, and Arriel 1D, 1D1,
and 1S1 engines that do not incorporate TU
347. Arriel 1B engines are installed on, but
not limited to, Eurocopter France AS–350B
and AS–350A ‘‘Ecureuil’’ helicopters. Arriel
1D engines are installed on, but not limited
to, Eurocopter France AS–350B1 ‘‘Ecureuil’’
helicopters. Arriel 1D1 engines are installed
on, but not limited to, Eurocopter France AS–
350B2 ‘‘Ecureuil’’ helicopters. Arriel 1S1
engines are installed on, but not limited to,
Sikorsky Aircraft S–76A and S–76C
helicopters.
Adoption of the Amendment
Unsafe Condition
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
(d) This AD results from reports of failures
of second stage blades. We are issuing this
AD to prevent failures of the 2nd stage
turbine blades, which could result in
uncommanded in-flight engine shutdown,
and subsequent forced autorotation landing
or accident.
List of Subjects in 14 CFR Part 39
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]
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified unless the
actions have already been done.
I
Initial Relative Position Check of 2nd Stage
Turbine Blades
2008–07–01 Turbomeca: Amendment 39–
15442. Docket No. FAA–2005–21242;
Directorate Identifier 2005–NE–09–AD.
(f) Do an initial relative position check of
the 2nd stage turbine blades using the
Turbomeca mandatory alert service bulletins
(ASBs) specified in the following Table 1. Do
the check before reaching any of the intervals
specified in Table 1 or within 50 hours timein-service after the effective date of this AD,
whichever occurs later.
2. The FAA amends § 39.13 by
removing Amendment 39–14721 (71 FR
46390, August 14, 2006) and by adding
a new airworthiness directive,
Amendment 39–15442, to read as
follows:
TABLE 1.—INITIAL AND REPETITIVE RELATIVE POSITION CHECK INTERVALS OF 2ND STAGE TURBINE BLADE
Turbomeca engine
model
Arriel 1B (modified
per TU 148).
Arriel 1D1 and Arriel
1D.
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Initial relative position check interval
Repetitive interval
Mandatory Alert Service Bulletin
Within 1,200 hours time-since-new
(TSN) or time-since-overhaul (TSO)
or 3,500 cycles-since-new (CSN) or
cycles-since-overhaul (CSO), whichever occurs earlier.
Within 1,200 hours TSN or TSO or
3,500 CSN or CSO, whichever occurs earlier.
Within 1,200 hours TSN or TSO or
3,500 CSN or CSO, whichever occurs earlier.
Within 200 hours time-in-service-sincelast-relative-position-check
(TSLRPC).
A292 72 0807, Update 1, dated October 26, 2006.
Within 150 hours TSLRPC ...................
A292 72 0809, Update No. 1, dated
October 4, 2005.
Within 150 hours TSLRPC ...................
A292 72 0810, dated March 24, 2004.
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15868
Federal Register / Vol. 73, No. 59 / Wednesday, March 26, 2008 / Rules and Regulations
Repetitive Relative Position Check of 2nd
Stage Turbine Blades
(g) Recheck the relative position of 2nd
stage turbine blades at the TSLRPC intervals
specified in Table 1 of this AD, using the
mandatory ASBs indicated.
Credit for Previous Relative Position Checks
(h) Relative position checks of 2nd stage
turbine blades done using Turbomeca Service
Bulletin A292 72 0263, Update 1, 2, 3, or 4,
or A292 72 0807, dated March 24, 2004,
comply with the initial requirements of
paragraph (f) of this AD.
Initial Replacement of 2nd Stage Turbines
on Arriel 1B, 1D, and 1D1 Engines
(i) Initially replace the 2nd stage turbine
with a new or overhauled 2nd stage turbine
as follows:
(1) Before accumulating 1,500 hours TSN
or TSO on the module for Arriel 1D and 1D1
engines.
(2) Before accumulating 2,200 hours TSN
or TSO on the module or 3,000 total hours
TSN on the 2nd stage turbine blades,
whichever occurs first, for Arriel 1B engines.
Repetitive Replacements of 2nd Stage
Turbines on Arriel 1B, 1D, and 1D1 Engines
(j) Thereafter, replace the 2nd stage turbine
with a new or overhauled 2nd stage turbine
within every 1,500 hours TSN or TSO on the
module for Arriel 1D and 1D1 engines, and
within every 2,200 hours TSN or TSO on the
module or 3,000 total hours TSN on the 2nd
stage turbine blades, for Arriel 1B engines.
Criteria for Overhauled 2nd Stage Turbines
(k) Do the following to overhauled 2nd
stage turbines, referenced in paragraphs (i)
and (j) of this AD:
(1) You must install new blades in the 2nd
stage turbines of overhauled Arriel 1D and
1D1 engines.
(2) You may install either overhauled
blades with fewer than 3,000 total hours TSN
or new blades in the 2nd stage turbines of
overhauled Arriel 1B engines.
Relative Position Check Continuing
Compliance Requirements
(l) All 2nd stage turbines, including those
that are new or overhauled, must continue to
comply with the actions specified in
paragraphs (f), (g), and (j) of this AD.
Optional Terminating Action
(m) Installing a new turbine, P/N 0 292 25
039 0, reference TU 347, terminates the
requirements to perform the repetitive
actions specified in paragraphs (g) and (j) of
this AD.
Alternative Methods of Compliance
(n) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Related Information
(o) The EASA airworthiness directive
2007–0018R1, dated August 14, 2007, also
addresses the subject of this AD.
(p) 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
(q) You must use the service information
specified in Table 2 of this AD to perform the
actions required by this AD.
(1) The Director of the Federal Register
approved the incorporation by reference of
Turbomeca Mandatory Alert Service Bulletin
A292 72 0807, Update 1, dated October 26,
2006, in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.
(2) The Director of the Federal Register
previously approved the incorporation by
reference of Turbomeca Mandatory Alert
Service Bulletins A292 72 0809, Update 1,
dated October 4, 2005; and A292 72 0810,
dated March 24, 2004; as of February 28,
2006 (71 FR 3754, January 24, 2006).
(3) Contact Turbomeca, 40220 Tarnos,
France; telephone (33) 05 59 74 40 00, fax
(33) 05 59 74 45 15 for a copy of this service
information. You may review copies at the
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.
TABLE 2.—INCORPORATION BY REFERENCE
Turbomeca Mandatory Alert Service Bulletin No.
Page
Update No.
Date
A292 72 0807, Total Pages: 18 ............................................
A292 72 0809, Total Pages: 18 ............................................
A292 72 0810, Total Pages: 14 ............................................
ALL ........................................
ALL ........................................
ALL ........................................
1 ............................................
1 ............................................
Original ..................................
October 26, 2006.
October 4, 2005.
March 24, 2004.
Issued in Burlington, Massachusetts, on
March 17, 2008.
Ann C. Mollica,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E8–5819 Filed 3–25–08; 8:45 am]
ACTION:
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0056 Directorate
Identifier 2007–CE–096–AD; Amendment
39–15446; AD 2008–07–05]
sroberts on PROD1PC70 with RULES
RIN 2120–AA64
Airworthiness Directives; APEX
Aircraft Model CA 10B Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
VerDate Aug<31>2005
16:40 Mar 25, 2008
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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:
A CAP 10B experienced an emergency
landing after its front fuel tank collapsed and
rendered inoperative the left rudder pedals
which were blocked in neutral position.
Investigation and the metallurgical
examination revealed that the fuel tank straps
had fractured as a result of fatigue. The tank
support straps had logged around 7000 hours
time-in-service (TIS).
DGAC France Airworthiness Directive (AD)
F–2004–071 was issued to introduce a 4000
hour life-limit for the tank support straps and
to require replacement of straps which had
exceeded this life-limit. Since then, a front
tank support has been found damaged during
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an inspection before reaching 4000 hours
TIS.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective April
30, 2008.
On April 30, 2008, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Sarjapur Nagarajan, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
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]]>Agencies
[Federal Register Volume 73, Number 59 (Wednesday, March 26, 2008)]
[Rules and Regulations]
[Pages 15866-15868]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-5819]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21242; Directorate Identifier 2005-NE-09-AD;
Amendment 39-15442; AD 2008-07-01]
RIN 2120-AA64
Airworthiness Directives; Turbomeca Arriel 1B, 1D, 1D1, and 1S1
Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for certain Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft
engines. That AD currently requires initial and repetitive position
checks of the gas generator 2nd stage turbine blades on all Turbomeca
Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. That AD also currently
requires initial and repetitive replacements of 2nd stage turbines on
1B, 1D, and 1D1 engines only. This AD requires adding a 3,000 hour life
limit to Arriel 1B 2nd stage turbine blades. This AD results from
reports of failures of second stage turbine blades. We are issuing this
AD to prevent failures of the 2nd stage turbine blades, which could
result in uncommanded in-flight engine shutdown, and subsequent forced
autorotation landing or accident.
DATES: This AD becomes effective April 30, 2008. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of April 30, 2008. The
Director of the Federal Register previously approved the incorporation
by reference of Turbomeca Mandatory Alert Service Bulletins A292 72
0809, Update 1, dated October 4, 2005; and A292 72 0810, dated March
24, 2004; as of February 28, 2006 (71 FR 3754, January 24, 2006).
ADDRESSES: You can get the service information identified in this AD
from Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 74 40 00,
fax (33) 05 59 74 45 15.
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: The FAA proposed to amend 14 CFR part 39 by
superseding AD 2006-02-08R1, Amendment 39-14721 (71 FR 46390, August
14, 2006), with a proposed AD. The proposed AD applies to certain
Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. We published
the proposed AD in the Federal Register on March 9, 2007 (72 FR 10622).
That action proposed to require:
Initial and repetitive position checks of the 2nd stage
turbine blades on Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft
engines.
Replacement of 2nd stage turbines on 1B and 1D1 engines
only.
Initially replacing 2nd stage turbines in Arriel 1B, 1D,
and 1D1 turboshaft engines.
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.
Comments
We provided the public the opportunity to participate in the
development of this AD. We received no comments on the proposal or on
the determination of the cost to the public.
Addition of an Optional Terminating Action
We have added to the AD, an option to terminate the repetitive
position check requirements by installing a new turbine, part number
(P/N) 0 292 25 039 0.
Correction of a Typographical Error in the Costs of Compliance
We corrected the number of turbine replacements in the Costs of
Compliance from 587 to 571, and changed the total cost from $3,905,240
to $3,769,760.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.
[[Page 15867]]
Costs of Compliance
We estimate that this AD will affect 721 engines installed on
helicopters of U.S. registry. We also estimate that it will take about
2 work-hours per engine to inspect all 721 engines and 40 work-hours
per engine to replace about 571 2nd stage turbines on 1B and 1D1
engines, and that the average labor rate is $80 per work-hour. Required
parts would cost about $3,200 per engine. Based on these figures, we
estimate the total cost of the AD to U.S. operators to be $3,769,760.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration 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 removing Amendment 39-14721 (71 FR
46390, August 14, 2006) and by adding a new airworthiness directive,
Amendment 39-15442, to read as follows:
2008-07-01 Turbomeca: Amendment 39-15442. Docket No. FAA-2005-21242;
Directorate Identifier 2005-NE-09-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April
30, 2008.
Affected ADs
(b) This AD supersedes AD 2006-02-08R1, Amendment 39-14721 (71
FR 46390, August 14, 2006).
Applicability
(c) This AD applies to Turbomeca Arriel 1B engines fitted with
2nd stage turbine modification TU 148, and Arriel 1D, 1D1, and 1S1
engines that do not incorporate TU 347. Arriel 1B engines are
installed on, but not limited to, Eurocopter France AS-350B and AS-
350A ``Ecureuil'' helicopters. Arriel 1D engines are installed on,
but not limited to, Eurocopter France AS-350B1 ``Ecureuil''
helicopters. Arriel 1D1 engines are installed on, but not limited
to, Eurocopter France AS-350B2 ``Ecureuil'' helicopters. Arriel 1S1
engines are installed on, but not limited to, Sikorsky Aircraft S-
76A and S-76C helicopters.
Unsafe Condition
(d) This AD results from reports of failures of second stage
blades. We are issuing this AD to prevent failures of the 2nd stage
turbine blades, which could result in uncommanded in-flight engine
shutdown, and subsequent forced autorotation landing or accident.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Initial Relative Position Check of 2nd Stage Turbine Blades
(f) Do an initial relative position check of the 2nd stage
turbine blades using the Turbomeca mandatory alert service bulletins
(ASBs) specified in the following Table 1. Do the check before
reaching any of the intervals specified in Table 1 or within 50
hours time-in-service after the effective date of this AD, whichever
occurs later.
Table 1.--Initial and Repetitive Relative Position Check Intervals of 2nd Stage Turbine Blade
----------------------------------------------------------------------------------------------------------------
Initial relative position Mandatory Alert Service
Turbomeca engine model check interval Repetitive interval Bulletin
----------------------------------------------------------------------------------------------------------------
Arriel 1B (modified per TU 148).. Within 1,200 hours time- Within 200 hours time-in- A292 72 0807, Update 1,
since-new (TSN) or time- service-since-last- dated October 26, 2006.
since-overhaul (TSO) or relative-position-check
3,500 cycles-since-new (TSLRPC).
(CSN) or cycles-since-
overhaul (CSO),
whichever occurs earlier.
Arriel 1D1 and Arriel 1D......... Within 1,200 hours TSN or Within 150 hours TSLRPC. A292 72 0809, Update No.
TSO or 3,500 CSN or CSO, 1, dated October 4,
whichever occurs earlier. 2005.
Arriel 1S1....................... Within 1,200 hours TSN or Within 150 hours TSLRPC. A292 72 0810, dated
TSO or 3,500 CSN or CSO, March 24, 2004.
whichever occurs earlier.
----------------------------------------------------------------------------------------------------------------
[[Page 15868]]
Repetitive Relative Position Check of 2nd Stage Turbine Blades
(g) Recheck the relative position of 2nd stage turbine blades at
the TSLRPC intervals specified in Table 1 of this AD, using the
mandatory ASBs indicated.
Credit for Previous Relative Position Checks
(h) Relative position checks of 2nd stage turbine blades done
using Turbomeca Service Bulletin A292 72 0263, Update 1, 2, 3, or 4,
or A292 72 0807, dated March 24, 2004, comply with the initial
requirements of paragraph (f) of this AD.
Initial Replacement of 2nd Stage Turbines on Arriel 1B, 1D, and 1D1
Engines
(i) Initially replace the 2nd stage turbine with a new or
overhauled 2nd stage turbine as follows:
(1) Before accumulating 1,500 hours TSN or TSO on the module for
Arriel 1D and 1D1 engines.
(2) Before accumulating 2,200 hours TSN or TSO on the module or
3,000 total hours TSN on the 2nd stage turbine blades, whichever
occurs first, for Arriel 1B engines.
Repetitive Replacements of 2nd Stage Turbines on Arriel 1B, 1D, and 1D1
Engines
(j) Thereafter, replace the 2nd stage turbine with a new or
overhauled 2nd stage turbine within every 1,500 hours TSN or TSO on
the module for Arriel 1D and 1D1 engines, and within every 2,200
hours TSN or TSO on the module or 3,000 total hours TSN on the 2nd
stage turbine blades, for Arriel 1B engines.
Criteria for Overhauled 2nd Stage Turbines
(k) Do the following to overhauled 2nd stage turbines,
referenced in paragraphs (i) and (j) of this AD:
(1) You must install new blades in the 2nd stage turbines of
overhauled Arriel 1D and 1D1 engines.
(2) You may install either overhauled blades with fewer than
3,000 total hours TSN or new blades in the 2nd stage turbines of
overhauled Arriel 1B engines.
Relative Position Check Continuing Compliance Requirements
(l) All 2nd stage turbines, including those that are new or
overhauled, must continue to comply with the actions specified in
paragraphs (f), (g), and (j) of this AD.
Optional Terminating Action
(m) Installing a new turbine, P/N 0 292 25 039 0, reference TU
347, terminates the requirements to perform the repetitive actions
specified in paragraphs (g) and (j) of this AD.
Alternative Methods of Compliance
(n) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Related Information
(o) The EASA airworthiness directive 2007-0018R1, dated August
14, 2007, also addresses the subject of this AD.
(p) 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
(q) You must use the service information specified in Table 2 of
this AD to perform the actions required by this AD.
(1) The Director of the Federal Register approved the
incorporation by reference of Turbomeca Mandatory Alert Service
Bulletin A292 72 0807, Update 1, dated October 26, 2006, in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register previously approved the
incorporation by reference of Turbomeca Mandatory Alert Service
Bulletins A292 72 0809, Update 1, dated October 4, 2005; and A292 72
0810, dated March 24, 2004; as of February 28, 2006 (71 FR 3754,
January 24, 2006).
(3) Contact Turbomeca, 40220 Tarnos, France; telephone (33) 05
59 74 40 00, fax (33) 05 59 74 45 15 for a copy of this service
information. You may review copies at the 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 2.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Turbomeca Mandatory Alert Service
Bulletin No. Page Update No. Date
----------------------------------------------------------------------------------------------------------------
A292 72 0807, Total Pages: 18...... ALL.................. 1.................... October 26, 2006.
A292 72 0809, Total Pages: 18...... ALL.................. 1.................... October 4, 2005.
A292 72 0810, Total Pages: 14...... ALL.................. Original............. March 24, 2004.
----------------------------------------------------------------------------------------------------------------
Issued in Burlington, Massachusetts, on March 17, 2008.
Ann C. Mollica,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-5819 Filed 3-25-08; 8:45 am]
BILLING CODE 4910-13-P
