Airworthiness Directives; Turbomeca Arriel 1B, 1D, 1D1, and 1S1 Turboshaft Engines, 27411-27414 [2010-10720]
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srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations
(i) Remove the studs by following the
Accomplishment Instructions, paragraphs
3.B.(1) through 3.B.(4) of the ASB. Visually
inspect the tapped holes for any damage to
the threads. Serrations on the entire counter
bore (360 degrees) are acceptable. Serrations
in the housing must be intact, and mating
serrations on the lock ring must line up with
serrations on the housing. Visually inspect
the housing to determine that the housing
threads are free from damage and corrosion.
Visually inspect housing lockring
counterbore to determine if the housing is
airworthy.
(ii) If you find damage or corrosion to the
housing threads, the housing, or the lockring
counterbore, stop work and contact Kirk
Gustafson, Aviation Safety Engineer, Boston
Aircraft Certification Office, Engine and
Propeller Directorate, FAA, 12 New England
Executive Park, Burlington, MA 01803,
telephone (781) 238–7190, fax (781) 238–
7170.
(iii) If you do not find damage to the
housing threads, the housing, or the lockring
counterbore that requires repair, replace the
mounting studs by following the
Accomplishment Instructions, paragraphs
3.B.(7) through 3.B.(15) of the ASB.
(5) Install an airworthy, two-piece MGB
filter bowl assembly modification kit, P/N
92070–35005–011, as depicted in Figures 8
and 9 of the ASB and by following the
Accomplishment Instructions, paragraphs
3.C.(1) through 3.C.(20), of the ASB.
(b) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Manager, Boston Aircraft
Certification Office, Attn: Kirk Gustafson,
Aviation Safety Engineer, Boston Aircraft
Certification Office, Engine and Propeller
Directorate, FAA, 12 New England Executive
Park, Burlington, MA 01803, telephone (781)
238–7190, fax (781) 238–7170, for
information about previously approved
alternative methods of compliance.
(c) The Joint Aircraft System/Component
(JASC) Code is 6320: Main Rotor Gearbox.
(d) Inspecting and replacing the MGB filter
bowl assembly shall be done by following the
specified portions of Sikorsky Alert Service
Bulletin No. 92–63–022A, dated December
18, 2009. The Director of the Federal Register
approved this incorporation by reference in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from
Sikorsky Aircraft Corporation, Attn: Manager,
Commercial Technical Support, mailstop
s581a, 6900 Main Street, Stratford, CT,
telephone (203) 383–4866, e-mail address
tsslibrary@sikorsky.com, or at https://
www.sikorsky.com. Copies may be inspected
at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas, or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
(e) This amendment becomes effective on
June 21, 2010.
VerDate Mar<15>2010
16:29 May 14, 2010
Jkt 220001
Issued in Fort Worth, Texas, on April 27,
2010.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2010–11069 Filed 5–14–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21242; Directorate
Identifier 2005–NE–09–AD; Amendment 39–
16288; AD 2010–10–09]
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
requires initial and repetitive relative
position checks of the gas generator 2nd
stage turbine blades on Turbomeca
Arriel 1B (that incorporate Turbomeca
Modification (mod) TU 148), Arriel 1D,
1D1, and 1S1 turboshaft engines that do
not incorporate mod TU 347. That AD
also requires initial and repetitive
replacements of 2nd stage turbines on
Arriel 1B, 1D, and 1D1 engines. This AD
requires lowering the initial and
repetitive thresholds for replacement of
2nd stage turbines on Arriel 1B, 1D, and
1D1 engines. This AD results from
reports of new cases of failures of 2nd
stage turbine blades since we issued AD
2008–07–01. We are issuing this AD to
prevent the failure of 2nd stage turbine
blades, which could result in an
uncommanded in-flight engine
shutdown, and a subsequent forced
autorotation landing or accident.
DATES: This AD becomes effective June
21, 2010. The Director of the Federal
Register approved the incorporation by
reference of certain publications listed
in the regulations as of June 21, 2010.
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
PO 00000
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27411
Ground Floor, Room W12–140,
Washington, DC 20590–0001.
FOR FURTHER INFORMATION CONTACT:
Kevin Dickert, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: kevin.dickert@faa.gov;
phone: (781) 238–7117, fax: (781) 238–
7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 by
superseding AD 2008–07–01,
Amendment 39–15442 (73 FR 15866,
March 26, 2008), with a proposed AD.
The proposed AD applies to Turbomeca
Arriel 1B (that incorporate mod TU
148), 1D, 1D1, and 1S1 turboshaft
engines that do not incorporate mod TU
347. We published the proposed AD in
the Federal Register on March 10, 2010
(75 FR 11072). That action proposed to
require lowering the repetitive threshold
for relative position checks on Arriel 1B
engines. That action also proposed to
require lowering the initial and
repetitive thresholds for replacement of
2nd stage turbines on Arriel 1B, 1D, and
1D1 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 (phone
(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.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed.
Costs of Compliance
Based on the service information, we
estimate that this AD will affect about
587 Turbomeca Arriel 1B, 1D, 1D1, and
1S1 turboshaft engines installed on
products of U.S. registry. We also
estimate that it will take about 2 workhours per engine to perform one
inspection, and about 40 work-hours per
engine to replace the gas turbine discs
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Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations
and blades. The average labor rate is $85
per work-hour. Required parts will cost
about $54,000 per engine. Based on
these figures, we estimate the cost of the
AD on U.S. operators to be $33,793,590.
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
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
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
removing Amendment 39–15442 (73 FR
15866, March 26, 2008), and by adding
a new airworthiness directive,
Amendment 39–16288, to read as
follows:
■
2010–10–09 Turbomeca: Amendment 39–
16288. Docket No. FAA–2005–21242;
Directorate Identifier 2005–NE–09–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective June 21, 2010.
Affected ADs
(b) This AD supersedes AD 2008–07–01,
Amendment 39–15442.
Applicability
(c) This AD applies to Turbomeca Arriel 1B
(that incorporate Turbomeca Modification
(mod) TU 148), Arriel 1D, 1D1, and 1S1
engines that do not incorporate mod TU 347.
Arriel 1B engines are installed on, but not
limited to, Eurocopter AS–350B and AS–
350BA ‘‘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 Corporation S–76C
helicopters.
Unsafe Condition
(d) This AD results from reports of new
cases of failures of 2nd stage turbine blades
since we issued AD 2008–07–01. We are
issuing this AD to prevent the failure of 2nd
stage turbine blades, which could result in an
uncommanded in-flight engine shutdown,
and a 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 Service Bulletins
(MSBs) 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.
TABLE 1—INITIAL AND REPETITIVE RELATIVE POSITION CHECK INTERVALS OF 2ND STAGE TURBINE BLADE
Turbomeca engine model
Initial relative position check
interval
Repetitive interval
Mandatory Service Bulletin
Arriel 1B (that incorporate mod TU
148), 1D1, and 1D.
Within 1,200 hours time-sincenew (TSN) or time-since-overhaul (TSO) or 3,500 cyclessince-new (CSN) or cyclessince-overhaul (CSO), whichever occurs earlier.
Within 1,200 hours TSN or TSO
or 3,500 CSN or CSO, whichever occurs earlier.
Within 150 hours time-in-servicesince-last-relative-positioncheck (TSLRPC).
A292 72 0807, Version E, dated
October 29, 2009, paragraphs
2B(1)(a) and (b), or 2B(2)(a).
Within 150 hours TSLRPC ...........
A292 72 0810, Version C, dated
July 24, 2009, paragraphs
2B(1)(a) and (b), or 2B(2)(a),
(b), and (c).
srobinson on DSKHWCL6B1PROD with RULES
Arriel 1S1 .......................................
Repetitive Relative Position Check of 2nd
Stage Turbine Blades
Credit for Previous Relative Position Checks
(g) Recheck the relative position of 2nd
stage turbine blades at the TSLRPC intervals
specified in Table 1 of this AD, using the
Turbomeca MSBs indicated.
VerDate Mar<15>2010
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Jkt 220001
(h) Credit is allowed for previous relative
position checks of 2nd stage turbine blades
done using the following Turbomeca MSBs:
(1) MSB No. A292 72 0263, Update Nos. 1
through 5.
PO 00000
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(2) MSB No. A292 72 0807, Original, and
Update No. 1 through Version D.
(3) MSB No. A292 72 0809, Update No. 1.
(4) MSB No. A292 72 0810, Original, and
Version A through Version B.
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Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations
Initial Replacement of 2nd Stage Turbines
on Arriel 1B Engines
(i) Initially replace the Arriel 1B 2nd stage
turbine disk and blades with an inspected
2nd stage turbine that does not incorporate
mod TU 347 and is fitted with new blades
or with a 2nd stage turbine that incorporates
mod TU 347, using Turbomeca MSB No.
A292 72 0807, Version E, dated October 29,
2009, paragraphs 2B(1)(c) or (d), or 2B(2)(b)
or (c), at the following times:
(1) Replace before further flight on engines
with a 2nd stage turbine disk having
accumulated more than 2,200 hours TIS
since-new or since-last-inspection,
whichever occurs later, or with 2nd stage
turbine blades that have accumulated more
than 3,000 hours TIS since-new.
(2) For engines with 2nd stage turbine
blades having accumulated on the effective
date of this AD, more than 1,800 hours TIS
since-new, but 3,000 or fewer hours TIS
since-new, replace before reaching any of the
following:
(i) 400 hours TIS from the effective date of
this AD, or
(ii) 3,000 hours TIS since-new on the 2nd
stage turbine blades, or
(iii) 2,200 hours TIS since-new or sincelast-inspection, whichever occurs later, on
the 2nd stage turbine disk.
(3) For engines with 2nd stage turbine
blades having accumulated on the effective
date of this AD, more than 900 hours TIS
since-new, but 1,800 or fewer hours TIS
since-new, replace before reaching any of the
following:
(i) 800 hours TIS from the effective date of
this AD, or
(ii) 2,200 hours TIS since-new or since-lastinspection, whichever occurs later, on the
2nd stage turbine disk.
(4) For engines with 2nd stage turbine
blades having accumulated on the effective
date of this AD, 900 or fewer hours TIS sincenew, replace before the 2nd stage turbine
blades have accumulated 1,200 hours TIS
since-new.
Repetitive Replacements of 2nd Stage
Turbines on Arriel 1B Engines
(j) Thereafter, for 2nd stage turbines that do
not incorporate mod TU 347, replace the 2nd
Optional Terminating Action
stage turbine disk and blades before the
blades have accumulated 1,200 hours TIS
since-new.
(n) Installing a new turbine, P/N 0 292 25
039 0, (incorporation of mod TU 347)
terminates the requirements to perform the
repetitive actions specified in paragraphs (g),
(j), and (l) of this AD.
Initial Replacement of 2nd Stage Turbines
on Arriel 1D and 1D1 Engines
(k) Initially replace the Arriel 1D and 1D1
2nd stage turbine disk and blades with an
inspected turbine that does not incorporate
mod TU 347 and is fitted with new blades
or with a turbine that incorporates mod TU
347, using Turbomeca MSB No. A292 72
0807, Version E, dated October 29, 2009,
paragraphs 2B(1)(c) or (d), or 2B(2)(b) or (c),
at the following times:
(1) Replace before further flight on engines
with a 2nd stage turbine disk having
accumulated more than 1,500 hours TIS
since-new or since-last-inspection,
whichever occurs later, or with 2nd stage
turbine blades having accumulated more
than 1,500 hours TIS since-new.
(2) For engines with 2nd stage turbine
blades having accumulated on the effective
date of this AD, more than 900 hours TIS
since-new, but 1,500 or fewer hours TIS
since-new, replace before the 2nd stage
turbine blades have accumulated 1,500 hours
TIS since-new, or before the 2nd stage
turbine disk has accumulated 1,500 hours
TIS since-new, whichever occurs first.
(3) For engines with 2nd stage turbine
blades having accumulated on the effective
date of this AD, 900 or fewer hours TIS sincenew, replace before the 2nd stage turbine
blades have accumulated 1,200 hours TIS
since-new.
Alternative Methods of Compliance
(o) 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
(p) The EASA airworthiness directive
2009–0236, dated October 29, 2009, also
addresses the subject of this AD.
(q) Contact Kevin Dickert, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: kevin.dickert@faa.gov; phone:
(781) 238–7117, fax: (781) 238–7199, for
more information about this AD.
Material Incorporated by Reference
(r) You must use the service information
specified in the following Table 2 to perform
the actions required by this AD. The Director
of the Federal Register approved the
incorporation by reference of the documents
listed in the following Table 2 in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Turbomeca, 40220 Tarnos, France;
phone: (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.
Repetitive Replacements of 2nd Stage
Turbines on Arriel 1D and 1D1 Engines
(l) Thereafter, for 2nd stage turbines that do
not incorporate mod TU 347, replace the 2nd
stage turbine disk and blades before the
blades have accumulated 1,200 hours TIS
since-new.
Relative Position Check Continuing
Compliance Requirements
(m) All 2nd stage turbines, including those
that are new or overhauled, must continue to
comply with the actions specified in
paragraphs (f) and (g) of this AD, unless mod
TU 347 has been incorporated.
TABLE 2—INCORPORATION BY REFERENCE
Page
Version
A 292 72 0807 ........................................................................................................................
Total Pages: 20
A 292 72 0810 ........................................................................................................................
Total Pages: 15
srobinson on DSKHWCL6B1PROD with RULES
Turbomeca mandatory Service Bulletin No.
ALL ...............
E ...................
October 29, 2009.
ALL ...............
C ..................
July 24, 2009.
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Date
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Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations
Issued in Burlington, Massachusetts, on
April 28, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
[FR Doc. 2010–10720 Filed 5–14–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
FOR FURTHER INFORMATION CONTACT: Tim
Dulin, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2141; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
14 CFR Part 39
Discussion
[Docket No. FAA–2010–0129; Directorate
Identifier 2009–NM–245–AD; Amendment
39–16287; AD 2010–10–08]
RIN 2120–AA64
Airworthiness Directives; Airbus A318,
A319, A320, A321 Series Airplanes
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)
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:
Several occurrences of loss of the AC
[alternating current] BUS 1 have been
reported which led in some instances to the
loss of the AC ESS [essential] BUS and DC
[direct current] ESS BUS and connected
systems. The affected systems include
multiple flight deck Display Units (Primary
Flight Display, Navigation Display and Upper
Electronic Centralised Aircraft Monitoring
display).
*
*
*
*
*
srobinson on DSKHWCL6B1PROD with RULES
The loss of multiple display units, if not
corrected expediently during a high
workload period, potentially affects the
capability of the flight crew and could
contribute to a loss of situational awareness
and consequent control of the aeroplane,
which would constitute an unsafe condition.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective June
21, 2010.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of June 21, 2010.
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,
VerDate Mar<15>2010
16:29 May 14, 2010
Jkt 220001
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on February 23, 2010 (75 FR
8003). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
Several occurrences of loss of the AC
[alternating current] BUS 1 have been
reported which led in some instances to the
loss of the AC ESS [essential] BUS and DC
[direct current] ESS BUS and connected
systems. The affected systems include
multiple flight deck Display Units (Primary
Flight Display, Navigation Display and Upper
Electronic Centralised Aircraft Monitoring
display).
The reasons for these events have been
investigated but have not been fully
established for all cases.
Due to the range of system losses some
crews reported difficulty in establishing the
failure cause during the events and,
consequently, the appropriate actions to be
taken may not be completed in a timely
manner.
The loss of multiple display units, if not
corrected expediently during a high
workload period, potentially affects the
capability of the flight crew and could
contribute to a loss of situational awareness
and consequent control of the aeroplane,
which would constitute an unsafe condition.
This AD therefore mandates the
modification of the electrical network
configuration management logic consisting in
adding an automatic switching of the AC and
DC ESS BUS power supply such that upon
the loss of the AC BUS 1, the AC BUS 2 will
automatically take over the power supply. On
pre-MOD aeroplanes, this power supply
switching can only be accomplished
manually from the cockpit and is covered by
an Electronic Centralized Aircraft Monitoring
(ECAM) procedure.
The modification of the electrical power
distribution system includes, depending
on the configuration, adding a new
circuit breaker and new relay to the AC/
DC ESS BUS circuit, and adding a diode
between a certain relay and terminal
block. You may obtain further
information by examining the MCAI in
the AD docket.
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Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
Support and Request to Reduce
Compliance Time
The Airline Pilots Association,
International (ALPA) supports this AD,
and asks that the 48-month compliance
time proposed in the NPRM be reduced
to 24 months. ALPA states that, given
the potentially serious consequences of
the flightcrew experiencing a very high
workload during a critical phase of
flight, the compliance time should be
reduced based on the number of events
and the safety risk associated with BUS
failures.
We do not agree that the compliance
time should be reduced. In developing
the compliance time for this AD action,
we considered not only the safety
implications of the identified unsafe
condition, but the average utilization
rate of the affected fleet, the practical
aspects of modifying the fleet during the
compliance time, and the availability of
required parts. In addition, we have
coordinated with the European Aviation
Safety Agency (EASA), which is the
Technical Agent for the Member States
of the European Community. We have
determined that the 48-month
compliance time to do the modification
addresses the identified unsafe
condition and ensures an adequate level
of safety for the affected fleet. We have
made no change to the AD in this
regard.
Conclusion
We reviewed the available data,
including the comment received, 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.
E:\FR\FM\17MYR1.SGM
17MYR1
]]>Agencies
[Federal Register Volume 75, Number 94 (Monday, May 17, 2010)]
[Rules and Regulations]
[Pages 27411-27414]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-10720]
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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 39-16288; AD 2010-10-09]
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.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for certain Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft
engines. That AD requires initial and repetitive relative position
checks of the gas generator 2nd stage turbine blades on Turbomeca
Arriel 1B (that incorporate Turbomeca Modification (mod) TU 148),
Arriel 1D, 1D1, and 1S1 turboshaft engines that do not incorporate mod
TU 347. That AD also requires initial and repetitive replacements of
2nd stage turbines on Arriel 1B, 1D, and 1D1 engines. This AD requires
lowering the initial and repetitive thresholds for replacement of 2nd
stage turbines on Arriel 1B, 1D, and 1D1 engines. This AD results from
reports of new cases of failures of 2nd stage turbine blades since we
issued AD 2008-07-01. We are issuing this AD to prevent the failure of
2nd stage turbine blades, which could result in an uncommanded in-
flight engine shutdown, and a subsequent forced autorotation landing or
accident.
DATES: This AD becomes effective June 21, 2010. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of June 21, 2010.
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: Kevin Dickert, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
kevin.dickert@faa.gov; phone: (781) 238-7117, fax: (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by
superseding AD 2008-07-01, Amendment 39-15442 (73 FR 15866, March 26,
2008), with a proposed AD. The proposed AD applies to Turbomeca Arriel
1B (that incorporate mod TU 148), 1D, 1D1, and 1S1 turboshaft engines
that do not incorporate mod TU 347. We published the proposed AD in the
Federal Register on March 10, 2010 (75 FR 11072). That action proposed
to require lowering the repetitive threshold for relative position
checks on Arriel 1B engines. That action also proposed to require
lowering the initial and repetitive thresholds for replacement of 2nd
stage turbines on Arriel 1B, 1D, and 1D1 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 (phone (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.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.
Costs of Compliance
Based on the service information, we estimate that this AD will
affect about 587 Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft
engines installed on products of U.S. registry. We also estimate that
it will take about 2 work-hours per engine to perform one inspection,
and about 40 work-hours per engine to replace the gas turbine discs
[[Page 27412]]
and blades. The average labor rate is $85 per work-hour. Required parts
will cost about $54,000 per engine. Based on these figures, we estimate
the cost of the AD on U.S. operators to be $33,793,590.
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 39-15442 (73 FR
15866, March 26, 2008), and by adding a new airworthiness directive,
Amendment 39-16288, to read as follows:
2010-10-09 Turbomeca: Amendment 39-16288. Docket No. FAA-2005-21242;
Directorate Identifier 2005-NE-09-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective June 21,
2010.
Affected ADs
(b) This AD supersedes AD 2008-07-01, Amendment 39-15442.
Applicability
(c) This AD applies to Turbomeca Arriel 1B (that incorporate
Turbomeca Modification (mod) TU 148), Arriel 1D, 1D1, and 1S1
engines that do not incorporate mod TU 347. Arriel 1B engines are
installed on, but not limited to, Eurocopter AS-350B and AS-350BA
``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 Corporation S-
76C helicopters.
Unsafe Condition
(d) This AD results from reports of new cases of failures of 2nd
stage turbine blades since we issued AD 2008-07-01. We are issuing
this AD to prevent the failure of 2nd stage turbine blades, which
could result in an uncommanded in-flight engine shutdown, and a
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 Service Bulletins
(MSBs) 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 Mandatory Service
Turbomeca engine model position check interval Repetitive interval Bulletin
----------------------------------------------------------------------------------------------------------------
Arriel 1B (that incorporate mod TU Within 1,200 hours time- Within 150 hours time- A292 72 0807, Version
148), 1D1, and 1D. since-new (TSN) or in-service-since-last- E, dated October 29,
time-since-overhaul relative-position- 2009, paragraphs
(TSO) or 3,500 cycles- check (TSLRPC). 2B(1)(a) and (b), or
since-new (CSN) or 2B(2)(a).
cycles-since-overhaul
(CSO), whichever
occurs earlier.
Arriel 1S1........................... Within 1,200 hours TSN Within 150 hours TSLRPC A292 72 0810, Version
or TSO or 3,500 CSN or C, dated July 24,
CSO, whichever occurs 2009, paragraphs
earlier. 2B(1)(a) and (b), or
2B(2)(a), (b), and
(c).
----------------------------------------------------------------------------------------------------------------
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
Turbomeca MSBs indicated.
Credit for Previous Relative Position Checks
(h) Credit is allowed for previous relative position checks of
2nd stage turbine blades done using the following Turbomeca MSBs:
(1) MSB No. A292 72 0263, Update Nos. 1 through 5.
(2) MSB No. A292 72 0807, Original, and Update No. 1 through
Version D.
(3) MSB No. A292 72 0809, Update No. 1.
(4) MSB No. A292 72 0810, Original, and Version A through
Version B.
[[Page 27413]]
Initial Replacement of 2nd Stage Turbines on Arriel 1B Engines
(i) Initially replace the Arriel 1B 2nd stage turbine disk and
blades with an inspected 2nd stage turbine that does not incorporate
mod TU 347 and is fitted with new blades or with a 2nd stage turbine
that incorporates mod TU 347, using Turbomeca MSB No. A292 72 0807,
Version E, dated October 29, 2009, paragraphs 2B(1)(c) or (d), or
2B(2)(b) or (c), at the following times:
(1) Replace before further flight on engines with a 2nd stage
turbine disk having accumulated more than 2,200 hours TIS since-new
or since-last-inspection, whichever occurs later, or with 2nd stage
turbine blades that have accumulated more than 3,000 hours TIS
since-new.
(2) For engines with 2nd stage turbine blades having accumulated
on the effective date of this AD, more than 1,800 hours TIS since-
new, but 3,000 or fewer hours TIS since-new, replace before reaching
any of the following:
(i) 400 hours TIS from the effective date of this AD, or
(ii) 3,000 hours TIS since-new on the 2nd stage turbine blades,
or
(iii) 2,200 hours TIS since-new or since-last-inspection,
whichever occurs later, on the 2nd stage turbine disk.
(3) For engines with 2nd stage turbine blades having accumulated
on the effective date of this AD, more than 900 hours TIS since-new,
but 1,800 or fewer hours TIS since-new, replace before reaching any
of the following:
(i) 800 hours TIS from the effective date of this AD, or
(ii) 2,200 hours TIS since-new or since-last-inspection,
whichever occurs later, on the 2nd stage turbine disk.
(4) For engines with 2nd stage turbine blades having accumulated
on the effective date of this AD, 900 or fewer hours TIS since-new,
replace before the 2nd stage turbine blades have accumulated 1,200
hours TIS since-new.
Repetitive Replacements of 2nd Stage Turbines on Arriel 1B Engines
(j) Thereafter, for 2nd stage turbines that do not incorporate
mod TU 347, replace the 2nd stage turbine disk and blades before the
blades have accumulated 1,200 hours TIS since-new.
Initial Replacement of 2nd Stage Turbines on Arriel 1D and 1D1 Engines
(k) Initially replace the Arriel 1D and 1D1 2nd stage turbine
disk and blades with an inspected turbine that does not incorporate
mod TU 347 and is fitted with new blades or with a turbine that
incorporates mod TU 347, using Turbomeca MSB No. A292 72 0807,
Version E, dated October 29, 2009, paragraphs 2B(1)(c) or (d), or
2B(2)(b) or (c), at the following times:
(1) Replace before further flight on engines with a 2nd stage
turbine disk having accumulated more than 1,500 hours TIS since-new
or since-last-inspection, whichever occurs later, or with 2nd stage
turbine blades having accumulated more than 1,500 hours TIS since-
new.
(2) For engines with 2nd stage turbine blades having accumulated
on the effective date of this AD, more than 900 hours TIS since-new,
but 1,500 or fewer hours TIS since-new, replace before the 2nd stage
turbine blades have accumulated 1,500 hours TIS since-new, or before
the 2nd stage turbine disk has accumulated 1,500 hours TIS since-
new, whichever occurs first.
(3) For engines with 2nd stage turbine blades having accumulated
on the effective date of this AD, 900 or fewer hours TIS since-new,
replace before the 2nd stage turbine blades have accumulated 1,200
hours TIS since-new.
Repetitive Replacements of 2nd Stage Turbines on Arriel 1D and 1D1
Engines
(l) Thereafter, for 2nd stage turbines that do not incorporate
mod TU 347, replace the 2nd stage turbine disk and blades before the
blades have accumulated 1,200 hours TIS since-new.
Relative Position Check Continuing Compliance Requirements
(m) All 2nd stage turbines, including those that are new or
overhauled, must continue to comply with the actions specified in
paragraphs (f) and (g) of this AD, unless mod TU 347 has been
incorporated.
Optional Terminating Action
(n) Installing a new turbine, P/N 0 292 25 039 0, (incorporation
of mod TU 347) terminates the requirements to perform the repetitive
actions specified in paragraphs (g), (j), and (l) of this AD.
Alternative Methods of Compliance
(o) 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
(p) The EASA airworthiness directive 2009-0236, dated October
29, 2009, also addresses the subject of this AD.
(q) Contact Kevin Dickert, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
kevin.dickert@faa.gov; phone: (781) 238-7117, fax: (781) 238-7199,
for more information about this AD.
Material Incorporated by Reference
(r) You must use the service information specified in the
following Table 2 to perform the actions required by this AD. The
Director of the Federal Register approved the incorporation by
reference of the documents listed in the following Table 2 in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact
Turbomeca, 40220 Tarnos, France; phone: (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 Service
Bulletin No. Page Version Date
----------------------------------------------------------------------------------------------------------------
A 292 72 0807..................... ALL................... E.................... October 29, 2009.
Total Pages: 20
A 292 72 0810..................... ALL................... C.................... July 24, 2009.
Total Pages: 15
----------------------------------------------------------------------------------------------------------------
[[Page 27414]]
Issued in Burlington, Massachusetts, on April 28, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-10720 Filed 5-14-10; 8:45 am]
BILLING CODE 4910-13-P
