[Federal Register Volume 81, Number 55 (Tuesday, March 22, 2016)]
[Rules and Regulations]
[Pages 15154-15156]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-06372]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-2701; Directorate Identifier 2016-NE-03-AD; 
Amendment 39-18440; AD 2016-06-09]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Turbomeca S.A. Makila 2A and 2A1 turboshaft engines. This AD requires 
tightening the nut attaching the swivel union to the engine power 
turbine module M04. This AD was prompted by two occurrences of 
commanded in-flight shutdown following low oil pressure warning. We are 
issuing this AD to prevent loosening of the nut and oil leakage from 
the low-pressure oil system, which could lead to in-flight shutdown of 
the engine and forced landing.

DATES: This AD becomes effective April 6, 2016.
    We must receive comments on this AD by May 6, 2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Mail: U.S. Department of Transportation, 1200 New Jersey 
Avenue SE., West Building Ground Floor, Room W12-140, Washington, DC 
20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: 202-493-2251.
    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 16. You may view this service information at the 
FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, 
MA 01803. 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-2016-
2701.

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-2016-
2701; 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 mandatory continuing airworthiness information 
(MCAI), regulatory evaluation, any comments received, and other 
information. The address for the Docket Office (phone: 800-647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Besian Luga, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7750; fax: 781-
238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2016-2701; Directorate 
Identifier 2016-NE-03-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to http://

[[Page 15155]]

www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2016-0016, dated January 15, 2016 (referred to hereinafter as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    Two occurrences of commanded in-flight shut down following low 
oil pressure warning were reported. In both cases the nut attaching 
the swivel union to the power turbine module 04 was found completely 
loose. After further investigation, it was determined that the 
application of Turbomeca Service Bulletin (SB) No. 298 79 2831 may 
have led to incorrect torque application or loosening of the nut.

    Turbomeca S.A. has issued Alert Mandatory Service Bulletin No. A298 
79 2835, Version A, dated January 14, 2016, to provide guidance to 
assist operators in resolving this unsafe condition. You may obtain 
further information by examining the MCAI in the AD docket on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2016-2701.

FAA's Determination and Requirements of This AD

    This product has been approved by the aviation authority of France 
and is approved for operation in the United States. Pursuant to our 
bilateral agreement with the European Community, EASA has notified us 
of the unsafe condition described in the MCAI and service information 
referenced above. We are issuing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design. This AD requires tightening the nut attaching the swivel union 
to the engine power turbine module M04.

Related Service Information

    Turbomeca S.A. has issued Alert Mandatory Service Bulletin No. A298 
79 2835, Version A, dated January 14, 2016. The service information 
describes procedures for tightening the nut attaching the swivel union 
to the engine power turbine module (M04). 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 document.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
operators are required to take action with 7 days or 30 engine hours 
after the effective date of this AD. Therefore, we find that notice and 
opportunity for prior public comment are impracticable and that good 
cause exists for making this amendment effective in less than 30 days.

Costs of Compliance

    We estimate that this AD affects 10 engines installed on airplanes 
of U.S. registry. We also estimate that it will take about 1 hour per 
engine to comply with this AD. The average labor rate is $85 per hour. 
No additional parts are required. Based on these figures, we estimate 
the total cost of the AD to U.S. operators to be $850.

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

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 (AD):

2016-06-09 Turbomeca S.A.: Amendment 39-18440; Docket No. FAA-2016-
2701; Directorate Identifier 2016-NE-03-AD.

(a) Effective Date

    This AD is effective April 6, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Turbomeca S.A. Makila 2A and 2A1 
turboshaft engines that have incorporated Turbomeca S.A. Service 
Bulletin No. 298 79 2831, Version B, dated November 13, 2015, or 
earlier.

(d) Reason

    This AD was prompted by two occurrences of in-flight shutdowns 
as a result of the nut, attaching the swivel union to the power 
turbine module M04, coming loose. We are issuing this AD to prevent 
loosening of the nut, and oil leakage from the low pressure oil 
system, which could lead to in-flight shutdown of the engine and 
forced landing.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Within 30 engine hours or 7 days after the effective date of 
this AD, whichever occurs first, apply 15 Newton-meters torque to 
the nut, part number 9560130990, attaching the swivel union to the 
engine power turbine module M04. Use a backup wrench to prevent the 
swivel union from rotating.

[[Page 15156]]

(f) 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 
request. You may email your request to: [email protected].

(g) Related Information

    (1) For more information about this AD, contact Besian Luga, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7750; fax: 781-238-7199; email: [email protected].
    (2) Refer to MCAI European Aviation Safety Agency AD 2016-0016, 
dated January 15, 2016, for more information. You may examine the 
MCAI in the AD docket on the Internet at http://www.regulations.gov 
by searching for and locating it in Docket No. FAA-2016-2701.
    (3) Turbomeca S.A. Alert Mandatory Service Bulletin No. A298 79 
2835, Version A, dated January 14, 2016, which is not incorporated 
by reference in this AD, can be obtained from Turbomeca S.A., using 
the contact information in paragraph (g)(4) of this AD.
    (4) 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 16.
    (5) You may view this service information at the FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803. 
For information on the availability of this material at the FAA, 
call 781-238-7125.

(h) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on March 14, 2016.
Ann C. Mollica,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-06372 Filed 3-21-16; 8:45 am]
BILLING CODE 4910-13-P