Airworthiness Directives; Turbomeca Arriel 1B, 1D, 1D1, and 1S1 Turboshaft Engines, 3754-3757 [06-522]
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Federal Register / Vol. 71, No. 15 / Tuesday, January 24, 2006 / Rules and Regulations
Since the mean geometric chord of the
A380 is larger than that of the Boeing
747, a special condition is necessary to
define an appropriate upper value for
the range of gust gradient distances to be
investigated. That value would be the
mean geometric chord of the A380
(which is 34.8 feet) multiplied by 12.5,
which equals 435 feet. Increasing the
range of gust gradient distances to be
investigated to 435 feet will ensure an
appropriate analysis of the critical rigid
body response of the A380.
Discussion of Comments
Notice of Proposed Special
Conditions No. 25–05–11–C, pertaining
to discrete gust requirements for the
Airbus A380 airplane, was published in
the Federal Register on August 9, 2005
(70 FR 46113). A single comment was
received which supports the intent and
the language of the special condition, as
proposed.
Applicability
As discussed above, these special
conditions are applicable to the Airbus
A380–800 airplane. Should Airbus
apply at a later date for a change to the
type certificate to include another
model incorporating the same novel or
unusual design features, these special
conditions would apply to that model as
well under the provisions of § 21.101.
Conclusion
This action affects only certain novel
or unusual design features of the Airbus
A380–800 airplane. It is not a rule of
general applicability.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
The authority citation for these
special conditions is as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Special Conditions
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the Federal Aviation Administration
(FAA), the following special conditions
are issued as part of the type
certification basis for the Airbus A380–
800 airplane.
In lieu of the requirements of
§ 25.341(a)(3), the following special
conditions apply:
A sufficient number of gust gradient
distances in the range of 30 feet to 435
feet (12.5 times the Geometric Chord of
the Model A380) must be investigated to
find the critical response for each load
quantity.
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I
VerDate Aug<31>2005
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Issued in Renton, Washington, on January
10, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–598 Filed 1–23–06; 8:45 am]
BILLING CODE 4910–13–M
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21242; Directorate
Identifier 2005–NE–09–AD; Amendment 39–
14460; AD 2006–02–08]
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; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Turbomeca Arriel 1B, 1D, 1D1, and 1S1
turboshaft engines. This AD 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, and
initial and repetitive replacements of
2nd stage turbines on 1B, 1D, and 1D1
engines only. This AD results from
reports of the release of gas generator
2nd stage turbine blades while in
service, with full containment of debris.
We are issuing this AD to prevent
inflight engine shutdown and
subsequent forced autorotation landing
or accident.
DATES: This AD becomes effective
February 28, 2006. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulations as
of February 28, 2006.
We must receive any comments on
this AD by March 27, 2006.
ADDRESSES: Use one of the following
addresses to comment on this AD:
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
PO 00000
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Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Turbomeca, 40220 Tarnos,
France; telephone +33 05 59 74 40 00,
fax +33 05 59 74 45 15, for the service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Christopher Spinney, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803–5299; telephone
(781) 238–7175, fax (781) 238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed airworthiness directive (AD).
The proposed AD applies to Turbomeca
Arriel 1B engines fitted with 2nd stage
turbine modification TU 148, and Arriel
1D, 1D1, and 1S1 engines. We published
the proposed AD in the Federal Register
on June 28, 2005 (70 FR 37063). 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, and replacement of 2nd stage
turbines on 1B and 1D1 engines only.
Examining the AD Docket
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the Docket Management
Facility Docket Office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The Docket
Office (telephone (800) 647–5227) is
located on the plaza level of the
Department of Transportation Nassif
Building at the street address stated in
ADDRESSES. Comments will be available
in the AD docket shortly after the DMS
receives them.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Change the Compliance
Time
One commenter, Turbomeca, requests
we change the compliance time for
replacing 2nd stage turbines to,
immediately upon receipt of a
replacement 2nd stage turbine from
Turbomeca, and at least by August 31,
2006. The commenter states that
without this requirement, operators will
incur unacceptable and unnecessary
risk for engines operating past the
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Federal Register / Vol. 71, No. 15 / Tuesday, January 24, 2006 / Rules and Regulations
hourly life limit. The commenter further
states that an unacceptable number of
engines will require replacement 2nd
stage turbines at the compliance enddate, causing grounding of aircraft
because of a lack of replacement parts.
We partially agree. There is a need to
replace the 2nd stage turbines as they
reach the hourly life limit, and to strive
to not allow them to stay installed until
the compliance end-date. However,
replacing them immediately upon
receipt could unnecessarily create
compliance problems for operators. An
example would be if a helicopter is at
a remote site the day an operator
receives a replacement 2nd stage
turbine. We changed the compliance to
read ‘‘After accumulating 1,500 hours
TSN or TSO for Arriel 1D and 1D1
engines, and 2,200 hours TSN or TSO
for Arriel 1B engines, initially replace
the 2nd stage turbine with a new or
overhauled 2nd stage turbine as soon as
practicable, but no later than August 31,
2006.’’ This change prevents
compliance problems associated with
the commenter’s phrase ‘‘immediately
upon receipt’’ yet still requires prompt
replacement of 2nd stage turbines after
one becomes available.
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NPRM Not Clear About Ongoing
Requirement
The same commenter states that the
NPRM is not clear that replacing the
2nd stage turbines is an ongoing
requirement. We agree. We changed the
compliance in this AD to address initial
and repetitive replacements of 2nd stage
turbines.
Inspection and Replacement
Requirements Changed for Arriel 1D
Turboshaft Engines
The same commenter states that the
requirements for inspecting and
replacing Arriel 1D turboshaft engines
have changed since we issued the
NPRM. Those requirements are now the
same as for Arriel 1D1 turboshaft
engines. We agree. We changed the
compliance in this AD to shorten the
repetitive inspection interval and add
the requirement to replace the 2nd stage
turbine. However, since many of the
Arriel 1D turboshaft engines may be at
or near the compliance time for
replacing the 2nd stage turbine, we have
found that notice and opportunity for
further comment before issuing this AD,
are impracticable. We are issuing this
AD as a final rule; request for
comments, allowing operators to
comment after the AD publishes.
Conclusion
We have carefully reviewed the
available data, including the comments
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received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Interim Action
These actions are interim actions and
we may take further rulemaking actions
in the future.
Costs of Compliance
There are about 2,557 Turbomeca
Arriel 1B, 1D, 1D1 and 1S1 turboshaft
engines of the affected design in the
worldwide fleet. We estimate that this
AD will affect 721 engines installed on
helicopters of U.S. registry. We estimate
that it will take about 2 work hours per
engine to inspect all 721 engines and 40
hours per engine to replace about 571
2nd stage turbines on 1B and 1D1
engines, and that the average labor rate
is $65 per work hour. Required parts
will cost about $3,200 per engine. Based
on these figures, we estimate the total
cost of the AD to U.S. operators to be
$3,405,530.
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:
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(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:
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 airworthiness
directive:
I
2006–02–08 Turbomeca: Amendment 39–
14460; Docket No. FAA–2005–21242;
Directorate Identifier. 2005–NE–09–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective February 28, 2006.
Affected ADs
(b) None.
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. Arriel 1B engines are
installed on, but not limited to, Eurocopter
France AS–350B and AS–350A ‘‘Ecureuil’’
helicopters; 1D engines are installed on, but
not limited to, Eurocopter France AS–350B1
‘‘Ecureuil’’ helicopters; 1D1 engines are
installed on, but not limited to, Eurocopter
France AS–350B2 ‘‘Ecureuil’’ helicopters;
and 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 the
release of gas generator 2nd stage turbine
blades while in service, with full
containment of debris. We are issuing this
AD to prevent inflight engine shutdown and
subsequent forced autorotation landing or
accident.
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Federal Register / Vol. 71, No. 15 / Tuesday, January 24, 2006 / Rules and Regulations
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
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
Turbomeca engine
model
Initial relative position check interval
Repetitive interval
Arriel 1B (modified per
TU 148).
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.
Arriel 1D1 and Arriel
1D.
Within 1,200 hours TSN or TSO or 3,500 hours CSN or CSO,
whichever occurs earlier.
Within 200 hours time-inservice-since-last-relative-position-check
(TSLRPC).
Within 150 hours
TSLRPC.
Arriel 1S1 ...................
Within 1,200 hours TSN or TSO or 3,500 hours CSN or CSO,
whichever occurs earlier.
Within 150 hours
TSLRPC.
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,
may be used to show compliance with the
initial requirements of paragraph (f) of this
AD.
Initial Replacement of 2nd Stage Turbines
on Arriel 1B, 1D, and 1D1 Engines
(i) After accumulating 1,500 hours TSN or
TSO for Arriel 1D and 1D1 engines, and
2,200 hours TSN or TSO for Arriel 1B
engines, initially replace the 2nd stage
turbine with a new or overhauled 2nd stage
turbine as soon as practicable, but no later
than August 31, 2006.
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 for
Arriel 1D and 1D1 engines, and within every
2,200 hours TSN or TSO 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 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 relative position check
requirements of paragraphs (f) and (j) of this
AD.
Alternative Methods of Compliance
(m) 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.
Mandatory alert service
bulletin
A292 72 0807, dated
March 24, 2004.
A292 72 0809, Update
No. 1, dated October
4, 2005.
A292 72 0810, dated
March 24, 2004.
Related Information
(n) DGAC airworthiness directive F–2004–
047 R1, dated October 26, 2005, also
addresses the subject of this AD.
Material Incorporated by Reference
(o) You must use the service information
specified in Table 2 of this AD to perform the
actions required by this AD. The Director of
the Federal Register approved the
incorporation by reference of the documents
listed in Table 2 of this AD in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
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
Docket Management Facility; U.S.
Department of Transportation, 400 Seventh
Street, SW., Nassif Building, Room PL–401,
Washington, DC 20590–0001, on the Internet
at https://dms.dot.gov, 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/federalregister/cfr/ibr-locations.html.
TABLE 2.—INCORPORATION BY REFERENCE
Page
Update No.
A292 72 0807 .................................................................................................
Total Pages: 17
A292 72 0809 .................................................................................................
Total Pages: 18
A292 72 0810 .................................................................................................
Total Pages: 14
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Turbomeca mandatory alert service bulletin No.
ALL ............
Original ...........
March 24, 2004.
ALL ............
1 .....................
October 4, 2005.
ALL ............
Original ...........
March 24, 2004.
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Federal Register / Vol. 71, No. 15 / Tuesday, January 24, 2006 / Rules and Regulations
Issued in Burlington, Massachusetts, on
January 12, 2006.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 06–522 Filed 1–23–06; 8:45 am]
SUPPLEMENTARY INFORMATION:
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–18565; Directorate
Identifier 2003–NM–168–AD; Amendment
39–14461; AD 2006–02–09]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–200, A330–300, A340–200, and
A340–300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Airbus Model Airbus Model A330–200,
A330–300, A340–200, and A340–300
series airplanes. This AD requires
inspecting for damage to certain
actuators of the low-pressure shut-off
valve (LPSOV), and related investigative
and corrective actions if necessary. This
AD results from a report of damage to
the LPSOV pedestal. We are issuing this
AD to ensure that, in the event of an
engine fire, the LPSOV actuator
functions properly to delay or block the
fuel flow to the engine and prevent an
uncontrollable fire.
DATES: This AD becomes effective
February 28, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of February 28, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., Nassif Building, room PL–401,
Washington, DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2797;
fax (425) 227–1149.
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Jkt 208001
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to all Airbus Model A330, A340–
200, and A340–300 series airplanes; and
A340–541 and -642 airplanes. That
NPRM was published in the Federal
Register on July 8, 2004 (69 FR 41211).
That NPRM proposed to require
inspecting for damage to certain
actuators of the low-pressure shut-off
valve (LPSOV), and related investigative
and corrective actions if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Requests To Limit Applicability
One commenter, on behalf of Airbus,
requests that we revise the proposed
applicability to match that of the French
airworthiness directive, which is
limited to airplanes equipped with
certain LPSOV part numbers (P/Ns). The
commenter adds that Model A330–301
airplanes (among others) receive Airbus
Modification 48225/48223 in
production, and Model A340–541 and
–642 airplanes receive Airbus
Modification 48552 in production.
These modifications involve installing
actuator P/N FRH010041.
We infer that the commenter would
like us to remove Model A330–301,
A340–541, and A340–642 airplanes
from the applicability of the proposed
AD. Since we issued the proposed AD,
French airworthiness directive F–2003–
360 R1, dated May 26, 2004, was issued
to limit the applicability to A340–200
and –300 series airplanes. We have
revised this final rule accordingly.
There has been no corresponding
revision to French airworthiness
directive F–2003–359 to exclude Model
A330–301 airplanes.
Another commenter, a Model A330
operator, also requests that we limit the
applicability. The commenter reports
the following: This operator’s entire
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3757
A330 fleet was delivered with P/N
FRH010041 actuators installed, its first
A330 was delivered July 2003, and no
P/N HTE190021 or P/N HTE190026
actuators have been purchased. Airbus
Service Bulletins A330–28–3083 and
A340–28–4098, both dated March 25,
2003, limit their effectivity to airplanes
delivered up to May 2003, but the
proposed AD would not so limit the
applicability. The commenter requests
that we revise the applicability of the
proposed AD to match that of the
service bulletins.
As stated in the preamble to the
proposed AD, ‘‘the French airworthiness
directives specify that Model A330 and
A340 series airplanes are affected if they
are equipped with LPSOV actuators
having certain part numbers.’’ The
Airbus service bulletins, which are
mandated by the French airworthiness
directives, specify that operators first
identify the part numbers of the
actuators. This AD therefore applies to
all Model A330 and A340 series
airplanes and requires part number
identification. Because the part is
interchangeable, this AD further ensures
that affected LPSOVs are not installed in
the future, as required by paragraph (g)
of this AD. However, we agree to revise
paragraph (f) of this final rule to also
allow an airplane records review to
determine the part number of the
actuator.
Request To Allow Additional Service
Information
The proposed AD would require
operators to inspect certain LPSOV
actuators, and would prohibit
installation of affected actuators on or
after the effective date of the AD. One
commenter, on behalf of an operator of
Model A330 airplanes, notes that Task
28–00–00–200–80 of the A330 Aircraft
Maintenance Manual (AMM), task 28–
00–00–200–801, revised July 1, 2004,
provides new installation procedures for
measuring the dowel in each LPSOV
location. According to the commenter,
the AMM should provide sufficient
instructions to meet the parts
installation requirement (paragraph (g)
of the proposed AD); however, as
written, paragraph (g) would prohibit
installing an affected actuator unless it
has been measured specifically in
accordance with Airbus Service Bulletin
A330–28–3083. The commenter
requests that we revise paragraph (g) to
also consider the AMM task acceptable
for measuring the dowel during
installation of the actuator. The
commenter asserts that this change will
also prevent the inadvertent installation
of an actuator that had not been
measured, since actuators that have
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]]>Agencies
[Federal Register Volume 71, Number 15 (Tuesday, January 24, 2006)]
[Rules and Regulations]
[Pages 3754-3757]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-522]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21242; Directorate Identifier 2005-NE-09-AD;
Amendment 39-14460; AD 2006-02-08]
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; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. This
AD 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, and initial and repetitive replacements of 2nd
stage turbines on 1B, 1D, and 1D1 engines only. This AD results from
reports of the release of gas generator 2nd stage turbine blades while
in service, with full containment of debris. We are issuing this AD to
prevent inflight engine shutdown and subsequent forced autorotation
landing or accident.
DATES: This AD becomes effective February 28, 2006. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of February 28, 2006.
We must receive any comments on this AD by March 27, 2006.
ADDRESSES: Use one of the following addresses to comment on this AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Turbomeca, 40220 Tarnos, France; telephone +33 05 59 74 40
00, fax +33 05 59 74 45 15, for the service information identified in
this AD.
FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299;
telephone (781) 238-7175, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed airworthiness directive (AD). The proposed AD applies
to Turbomeca Arriel 1B engines fitted with 2nd stage turbine
modification TU 148, and Arriel 1D, 1D1, and 1S1 engines. We published
the proposed AD in the Federal Register on June 28, 2005 (70 FR 37063).
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, and replacement of 2nd stage turbines on 1B and
1D1 engines only.
Examining the AD Docket
You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
Facility Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is located on the plaza level of the Department of
Transportation Nassif Building at the street address stated in
ADDRESSES. Comments will be available in the AD docket shortly after
the DMS receives them.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Change the Compliance Time
One commenter, Turbomeca, requests we change the compliance time
for replacing 2nd stage turbines to, immediately upon receipt of a
replacement 2nd stage turbine from Turbomeca, and at least by August
31, 2006. The commenter states that without this requirement, operators
will incur unacceptable and unnecessary risk for engines operating past
the
[[Page 3755]]
hourly life limit. The commenter further states that an unacceptable
number of engines will require replacement 2nd stage turbines at the
compliance end-date, causing grounding of aircraft because of a lack of
replacement parts. We partially agree. There is a need to replace the
2nd stage turbines as they reach the hourly life limit, and to strive
to not allow them to stay installed until the compliance end-date.
However, replacing them immediately upon receipt could unnecessarily
create compliance problems for operators. An example would be if a
helicopter is at a remote site the day an operator receives a
replacement 2nd stage turbine. We changed the compliance to read
``After accumulating 1,500 hours TSN or TSO for Arriel 1D and 1D1
engines, and 2,200 hours TSN or TSO for Arriel 1B engines, initially
replace the 2nd stage turbine with a new or overhauled 2nd stage
turbine as soon as practicable, but no later than August 31, 2006.''
This change prevents compliance problems associated with the
commenter's phrase ``immediately upon receipt'' yet still requires
prompt replacement of 2nd stage turbines after one becomes available.
NPRM Not Clear About Ongoing Requirement
The same commenter states that the NPRM is not clear that replacing
the 2nd stage turbines is an ongoing requirement. We agree. We changed
the compliance in this AD to address initial and repetitive
replacements of 2nd stage turbines.
Inspection and Replacement Requirements Changed for Arriel 1D
Turboshaft Engines
The same commenter states that the requirements for inspecting and
replacing Arriel 1D turboshaft engines have changed since we issued the
NPRM. Those requirements are now the same as for Arriel 1D1 turboshaft
engines. We agree. We changed the compliance in this AD to shorten the
repetitive inspection interval and add the requirement to replace the
2nd stage turbine. However, since many of the Arriel 1D turboshaft
engines may be at or near the compliance time for replacing the 2nd
stage turbine, we have found that notice and opportunity for further
comment before issuing this AD, are impracticable. We are issuing this
AD as a final rule; request for comments, allowing operators to comment
after the AD publishes.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Interim Action
These actions are interim actions and we may take further
rulemaking actions in the future.
Costs of Compliance
There are about 2,557 Turbomeca Arriel 1B, 1D, 1D1 and 1S1
turboshaft engines of the affected design in the worldwide fleet. We
estimate that this AD will affect 721 engines installed on helicopters
of U.S. registry. We estimate that it will take about 2 work hours per
engine to inspect all 721 engines and 40 hours per engine to replace
about 571 2nd stage turbines on 1B and 1D1 engines, and that the
average labor rate is $65 per work hour. Required parts will cost about
$3,200 per engine. Based on these figures, we estimate the total cost
of the AD to U.S. operators to be $3,405,530.
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 adding the following new airworthiness
directive:
2006-02-08 Turbomeca: Amendment 39-14460; Docket No. FAA-2005-21242;
Directorate Identifier. 2005-NE-09-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective February
28, 2006.
Affected ADs
(b) None.
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. Arriel 1B engines are installed on, but not limited to,
Eurocopter France AS-350B and AS-350A ``Ecureuil'' helicopters; 1D
engines are installed on, but not limited to, Eurocopter France AS-
350B1 ``Ecureuil'' helicopters; 1D1 engines are installed on, but
not limited to, Eurocopter France AS-350B2 ``Ecureuil'' helicopters;
and 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 the release of gas generator
2nd stage turbine blades while in service, with full containment of
debris. We are issuing this AD to prevent inflight engine shutdown
and subsequent forced autorotation landing or accident.
[[Page 3756]]
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 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
Turbomeca engine model check interval Repetitive interval service bulletin
----------------------------------------------------------------------------------------------------------------
Arriel 1B (modified per TU 148)... Within 1,200 hours time- Within 200 hours time- A292 72 0807, dated
since-new (TSN) or time- in-service-since-last- March 24, 2004.
since-overhaul (TSO) or relative-position-
3,500 cycles-since-new check (TSLRPC).
(CSN) or cycles-since-
overhaul (CSO), whichever
occurs earlier.
Arriel 1D1 and Arriel 1D.......... Within 1,200 hours TSN or Within 150 hours A292 72 0809, Update
TSO or 3,500 hours CSN or TSLRPC. No. 1, dated October
CSO, whichever occurs 4, 2005.
earlier.
Arriel 1S1........................ Within 1,200 hours TSN or Within 150 hours A292 72 0810, dated
TSO or 3,500 hours CSN or TSLRPC. March 24, 2004.
CSO, whichever occurs
earlier.
----------------------------------------------------------------------------------------------------------------
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,
may be used to show compliance with the initial requirements of
paragraph (f) of this AD.
Initial Replacement of 2nd Stage Turbines on Arriel 1B, 1D, and 1D1
Engines
(i) After accumulating 1,500 hours TSN or TSO for Arriel 1D and
1D1 engines, and 2,200 hours TSN or TSO for Arriel 1B engines,
initially replace the 2nd stage turbine with a new or overhauled 2nd
stage turbine as soon as practicable, but no later than August 31,
2006.
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 for
Arriel 1D and 1D1 engines, and within every 2,200 hours TSN or TSO
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 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 relative position check
requirements of paragraphs (f) and (j) of this AD.
Alternative Methods of Compliance
(m) 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
(n) DGAC airworthiness directive F-2004-047 R1, dated October
26, 2005, also addresses the subject of this AD.
Material Incorporated by Reference
(o) You must use the service information specified in Table 2 of
this AD to perform the actions required by this AD. The Director of
the Federal Register approved the incorporation by reference of the
documents listed in Table 2 of this AD in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. 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 Docket
Management Facility; U.S. Department of Transportation, 400 Seventh
Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-
0001, on the Internet at https://dms.dot.gov, 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................. ALL............. Original........... March 24, 2004.
Total Pages: 17
A292 72 0809................. ALL............. 1.................. October 4, 2005.
Total Pages: 18
A292 72 0810................. ALL............. Original........... March 24, 2004.
Total Pages: 14
----------------------------------------------------------------------------------------------------------------
[[Page 3757]]
Issued in Burlington, Massachusetts, on January 12, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 06-522 Filed 1-23-06; 8:45 am]
BILLING CODE 4910-13-P
