
[Federal Register: May 17, 2010 (Volume 75, Number 94)]
[Rules and Regulations]
[Page 27411-27414]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17my10-6]

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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 http://
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
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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: http://
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

