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2015-17-18 TURBOMECA S.A.: Amendment 39-18251; Docket No. FAA-2015-0900; Directorate Identifier 2015-NE-12-AD.
(a) EFFECTIVE DATE

    This AD becomes effective October 2, 2015.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This  AD  applies  to  all Turbomeca S.A. Arrius 2F turboshaft engines
    with oil pump, part number (P/N) 0319155050, installed, except for:

(1) Engines, equipped with an oil pump, P/N 0319155050,  that  were  over-
    hauled in a Turbomeca repair center after January 1, 2013, and

(2) Engines with a serial number of 34776 or higher, provided that the oil
    pump was not replaced on that  engine  since  the first flight of that
    engine on a helicopter.

(d) REASON

    This AD was  prompted by cases  of deterioration of  the gas generator
    front bearing due to a link  loss between the pump driver and  the oil
    pump shaft. We are  issuing this AD to  prevent link loss between  the
    pump driver and the oil pump  shaft, which could lead to an  engine in
    -flight shutdown, forced landing, and damage to the helicopter.

(e) ACTIONS AND COMPLIANCE

    Comply with this AD within the compliance times specified,  unless al-
    ready done.

(1) Inspect  the  pump  driver  assembly  on the oil pump shaft,  the pump
    driver  splines,  and  the  oil pump splines,  using  paragraph 2.4.2,
    Operating Instructions,  of  Turbomeca S.A. Mandatory Service Bulletin
    (MSB) No. 319 79 4834, Version B, dated October 21, 2014, as follows:

(i) For engines with fewer than 250 engine hours (EH),  accumulated  since
    new,  since last overhaul,  or  since last installation of an affected
    oil pump,  whichever occurred later,  inspect before exceeding 300 EH,
    accumulated since new, since last overhaul, or since last installation
    of an affected oil pump, as applicable.

(ii) For engines with 250 EH or more,  but fewer than 300 EH,  accumulated
     since new,  since  last  overhaul,  or  since last installation of an
     affected oil pump, whichever occurred later, inspect within 50 EH.

(iii) For engines with 300 EH or more, but fewer than 800 EH,  accumulated
      since new,  since last  overhaul, or  since last  installation of an
      affected oil pump, whichever occurred later, inspect within 100 EH.

(iv) For engines with 800 EH or more,  accumulated since new,  since  last
     overhaul,  or since last installation of an affected oil pump, which-
     ever occurred later, inspect during the next scheduled 500 EH inspec-
     tion.

(2) If any oil pump drive assembly and/or oil pump shaft,  or the oil pump
    itself, fails the inspection required by this AD, then before  further
    flight,  replace  the  failed   part(s)  with  part(s)  eligible   for
    installation.

(3) The  instruction  to  report inspection results and the instruction to
    return  a  compliance  certificate  to  Turbomeca  S.A.  as  stated in
    paragraph 2.4.2, Operating Instructions, of Turbomeca S.A. MSB No. 319
    79 4834, Version B,  dated October 21, 2014, are not required by  this
    AD.

(f) CREDIT FOR PREVIOUS ACTION

    If  you  inspected the oil pump driver assembly on the oil pump shaft,
    the pump driver splines,  and the oil pump splines,  and  replaced any
    part(s) with part(s) eligible for installation  before  the  effective
    date of this AD in accordance with Turbomeca S.A. MSB No. 319 79 4834,
    Version A,  dated November 25, 2013,  you met the requirements of this
    AD.

(g) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

    The Manager, Engine Certification Office,  FAA,  may approve AMOCs for
    this AD.  Use  the  procedures  found in 14 CFR 39.19 to make your re-
    quest. You may email your request to: ANE-AD-AMOC@faa.gov.

(h) RELATED INFORMATION

(1) For more information about this AD, contact Philip Haberlen, Aerospace
    Engineer,  Engine  Certification  Office,  FAA,   Engine  &  Propeller
    Directorate,  12  New  England  Executive  Park, Burlington, MA 01803;
    phone: 781-238-7770; fax: 781-238-7199; email: philip.haberlen@faa.gov

(2) Refer to  MCAI  European  Aviation  Safety  Agency AD 2015-0049, dated
    March 17, 2015 (Corrected May 7, 2015), for more information.  You may
    examine the MCAI in the AD docket on the Internet at http://www.
    regulations.gov/#!documentDetail;D=FAA-2015-0900-0002.

(i) MATERIAL INCORPORATED BY REFERENCE

(1) The  Director  of  the  Federal Register approved the incorporation by
    reference (IBR)  of  the  service information listed in this paragraph
    under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use  this service information as applicable to do the actions
    required by this AD, unless the AD specifies otherwise.

(i) Turbomeca S.A. MSB No. 319 79 4834, Version B, dated October 21, 2014.

(ii) Reserved.

(3) For  service  information  identified  in  this  proposed  AD, contact
    Turbomeca, S.A.,  40220 Tarnos,  France;  phone:  33 (0)5 59 74 40 00;
    telex: 570 042; fax: 33 (0)5 59 74 45 15.

(4) You may  view  this service information at the FAA, Engine & Propeller
    Directorate, 12 New England Executive Park, Burlington, MA. For infor-
    mation on the availability of this material at the FAA,  call 781-238-
    7125.

(5) You  may  view  this  service information 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.

Issued  in  Burlington,  Massachusetts,  on  August  17,  2015.  Diane  S.
Romanosky,  Acting Directorate  Manager, Engine  & Propeller  Directorate,
Aircraft Certification Service.

FOR  FURTHER  INFORMATION  CONTACT:  Philip Haberlen,  Aerospace Engineer,
Engine Certification Office,  FAA,  Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803;  phone:  781-238-7770;  fax:
781-238-7199; email: philip.haberlen@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0900; Directorate Identifier 2015-NE-12-AD;
Amendment 39-18251; AD 2015-17-18]
RIN 2120-AA64

Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Turbomeca S.A. Arrius 2F turboshaft engines with a certain part number
oil pump installed. This AD requires inspection, and if necessary,
replacement before further flight of the oil pump driver assembly and/
or the oil pump shaft, or the oil pump itself. This AD was prompted by
cases of deterioration of the gas generator front bearing due to a link
loss between the pump driver and the oil pump shaft. We are issuing
this AD to prevent link loss between the pump driver and the oil pump
shaft, which could lead to an engine in-flight shutdown, forced
landing, and damage to the helicopter.

DATES: This AD becomes effective October 2, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 2,
2015.

ADDRESSES: For service information identified in this AD, contact
Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00;
telex: 570 042; fax: 33 (0)5 59 74 45 15. You may view this service
information at the FAA, Engine & Propeller Directorate, 12 New England
Executive Park, Burlington, MA. For information on the availability of
this material at the FAA, call 781-238-7125. It is also available on
the Internet at http://www.regulations.gov by searching for and
locating Docket No. FAA-2015-0900.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.
gov by searching for and locating Docket No. FAA-2015-
0900; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the mandatory continuing airworthiness information
(MCAI), the regulatory evaluation, any comments received, and other
information. The address for the Docket Office (phone: 800-647-5527) is
Document Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Philip Haberlen, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; phone: 781-238-7770;
fax: 781-238-7199; email: philip.haberlen@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to the specified products. The
NPRM was published in the Federal Register on May 21, 2015 (80 FR
29224). The NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:

A risk of an in-flight shutdown (IFSD) has been identified on an
ARRIUS 2F engine, due to deterioration of gas generator front
bearing. This could be the result of lack of lubrication,
due to a link loss between pump driver and oil pump shaft.
This condition, if not detected and corrected, could lead to
cases of IFSD, possibly resulting in forced landing with consequent
damage to the helicopter and injury to occupants.

Related Service Information Under 1 CFR Part 51

Turbomeca S.A. has issued Mandatory Service Bulletin (MSB) No. 319
79 4834, Version B, dated October 21, 2014. The MSB describes
procedures for inspecting the oil pump driver assembly on the oil pump
shaft, the pump driver splines, and the oil pump splines. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section of this AD.

Comments

We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (80 FR 29224, May 21,
2015).

Conclusion

We reviewed the available data and determined that air safety and
the public interest require adopting this AD as proposed.

Costs of Compliance

We estimate that this AD affects about 96 engines installed on
helicopters of U.S. registry. We also estimate that it would take about
two hours per engine to comply with this AD. The average labor rate is
$85 per hour. Required parts would cost about $17,312 per engine. Based
on these figures, we estimate the cost of this AD on U.S. operators to
be $1,678,272.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction, and
(4) 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.

List of Subjects in 14 CFR Part 39


Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

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.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):