[Federal Register Volume 81, Number 21 (Tuesday, February 2, 2016)]
[Proposed Rules]
[Pages 5395-5397]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-01770]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-7490; Directorate Identifier 2015-NE-40-AD]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Turbomeca S.A. Astazou XIV B and H turboshaft engines. This 
proposed AD was prompted by a report of a crack on the 3rd stage 
turbine wheel. This proposed AD would require a one-time inspection of 
the front surface of the 3rd stage turbine for a groove. We are 
proposing this AD to prevent cracks in the 3rd stage turbine wheel, 
failure of the engine, in-flight shutdown, and loss of control of the 
helicopter.

DATES: We must receive comments on this proposed AD by April 4, 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: Docket Management Facility, 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 proposed AD, contact 
Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; fax: 
33 (0)5 59 74 45 15. You may view this service information at the FAA, 
Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. 
For information on the availability of this material at the FAA, call 
781-238-7125.

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-
7490; 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 proposed 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 in the ADDRESSES section. Comments will be available in 
the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Wego Wang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7134; fax: 781-
238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this NPRM. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2015-7490; 
Directorate Identifier 2015-NE-40-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. We will 
consider all comments received by the closing date and may amend this 
NPRM based on those comments.
    We will post all comments we receive, without change, to http://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 NPRM.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2015-0223, dated November 16, 2015 (referred to hereinafter as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    During the overhaul of an ASTAZOU XIV engine, a crack was 
detected on the front face

[[Page 5396]]

of the third stage turbine wheel between two balancing lugs. The 
cause of the crack is probably linked to a geometric singularity, 
likely caused by the transformation operation aimed at introducing 
expansion slots between the blades during embodiment of Turbomeca 
mod AB 173. Although there is only one known case of this type of 
crack, and although it was detected, the possibility exists that 
additional parts have the same geometric singularity.
    This condition, if not detected and corrected, may lead to 
failure of a turbine blade and its associated piece of rim, possibly 
resulting in an uncommanded in-flight shut-down and/or release of 
high energy debris.

    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-2015-7490.

Related Service Information Under 1 CFR Part 51

    Turbomeca S.A. has issued Service Bulletin (SB) No. 283 72 0811, 
Version A, dated August 25, 2015. The SB describes procedures for 
inspection of the 3rd stage turbine wheel. 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 NPRM.

FAA's Determination and Requirements of This Proposed 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 proposing this NPRM 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 NPRM would require inspecting the front surface of the 3rd 
stage turbine for a groove.

Costs of Compliance

    We estimate that this proposed AD affects 9 engines installed on 
helicopters of U.S. registry. We also estimate that it would take about 
5 hours per engine to comply with this proposed AD. The average labor 
rate is $85 per hour. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be $3,825.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    (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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

Turbomeca S.A.: Docket No. FAA-2015-7490; Directorate Identifier 
2015-NE-40-AD.

(a) Comments Due Date

    We must receive comments by April 4, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Astazou XIV B and XIV H turboshaft 
engines with 3rd stage turbine wheel, part number (P/N) 0 265 25 700 
0 or P/N 0 265 25 706 0, installed, if the engine incorporates 
Turbomeca modification AB-173 or AB-208.

(d) Reason

    This AD was prompted by a report of a crack on the 3rd stage 
turbine wheel. We are issuing this AD to prevent cracks in the 3rd 
stage turbine wheel, failure of the engine, in-flight shutdown, and 
loss of control of the helicopter.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) At the next piece part exposure of the 3rd stage turbine 
wheel or within 1,000 engine hours after the effective date of this 
AD whichever comes first, perform a one-time inspection for a groove 
on the front surface of the 3rd stage turbine wheel. Use 
Accomplishment Instructions, paragraph 4.4.2, of Turbomeca S.A. 
Service Bulletin (SB) No. 283 72 0811, Version A, dated August 25, 
2015 to perform the inspection.
    (2) If the 3rd stage turbine wheel passes inspection required by 
paragraph (e)(1) of this AD, no further action is required.
    (3) If the 3rd stage turbine wheel fails inspection required by 
paragraph (e)(1) of this AD, remove the part and replace with a part 
eligible for installation.

(f) Installation Prohibition

    After the effective date of this AD, do not install any 3rd 
stage turbine wheel, P/N 0 265 25 700 0 or P/N 0 265 25 706 0, 
unless it was inspected per the Accomplishment Instructions, 
paragraph 4.4.2, of Turbomeca S.A. SB No. 283 72 0811, Version A, 
dated August 25, 2015.

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

(h) Related Information

    (1) For more information about this AD, contact Wego Wang, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-

[[Page 5397]]

7134; fax: 781-238-7199; email: [email protected].
    (2) Refer to MCAI European Aviation Safety Agency AD 2015-0223, 
dated November 16, 2015, 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-2015-7490.
    (3) Turbomeca S.A. SB No. 283 72 0811, Version A, dated August 
25, 2015, can be obtained from Turbomeca S.A., using the contact 
information in paragraph (h)(4) of this proposed AD.
    (4) For service information identified in this proposed AD, 
contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 
40 00; fax: 33 (0)5 59 74 45 15.
    (5) You may view this service information at the FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.

    Issued in Burlington, Massachusetts, on January 27, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-01770 Filed 2-1-16; 8:45 am]
 BILLING CODE 4910-13-P