81 FR 26675 - Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 86 (May 4, 2016)

We are adopting a new airworthiness directive (AD) for certain Turbomeca S.A. Astazou XIV B and H turboshaft engines. This AD requires a one-time inspection of the front surface of the 3rd stage turbine for a groove. 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.

[Federal Register Volume 81, Number 86 (Wednesday, May 4, 2016)]
[Rules and Regulations]
[Pages 26675-26677]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-10279]


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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; 
Amendment 39-18500; AD 2016-09-02]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Turbomeca S.A. Astazou XIV B and H turboshaft engines. This AD requires 
a one-time inspection of the front surface of the 3rd stage turbine for 
a groove. 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.

DATES: This AD becomes effective June 8, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 8, 
2016.

ADDRESSES: For service information identified in this final rule, 
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. It is also available on the Internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2015-7490.

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 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: 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: 

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

[[Page 26676]]

NPRM was published in the Federal Register on February 2, 2016 (81 FR 
5395). The NPRM proposed 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 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (81 FR 5395, February 2, 
2016).

Conclusion

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

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.

Costs of Compliance

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

2016-09-02 Turbomeca S.A.: Amendment 39-18500; Docket No. FAA-2015-
7490; Directorate Identifier 2015-NE-40-AD.

(a) Effective Date

    This AD becomes effective June 8, 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: 781-238-7134; 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

[[Page 26677]]

docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-7490-0001.

(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. Service Bulletin No. 283 72 0811, Version A, 
dated August 25, 2015.
    (ii) Reserved.
    (3) For Turbomeca S.A. service information identified in this 
AD, contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 
74 40 00; fax: 33 (0)5 59 74 45 15.
    (4) You may view this service information at FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information 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 April 21, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-10279 Filed 5-3-16; 8:45 am]
 BILLING CODE 4910-13-P