Document ID: FAA-2016-6990-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Turbomeca S.A. Turboshaft Engines
Posted Date: 2016-11-01T04:00Z

[Federal Register Volume 81, Number 211 (Tuesday, November 1, 2016)]
[Rules and Regulations]
[Pages 75687-75689]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-26184]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6990; Directorate Identifier 2016-NE-14-AD; 
Amendment 39-186990; AD 2016-22-10]
RIN 2120-AA64

Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 75688]]

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Turbomeca S.A. Arriel 1, 1A, 1A1, 1A2, 1B, 1B2, 1C, 1C1, 1C2, 1D, 1D1, 
1E, 1E2, 1K1, 1S, and 1S1 turboshaft engines. This AD requires removing 
the centrifugal impeller and replacing with a part eligible for 
installation. This AD was prompted by an anomaly that occurred during 
the grinding operation required by modification TU376, which increases 
the clearance between the rear curvic coupling of the centrifugal 
impeller and the fuel injection manifold. We are issuing this AD to 
prevent failure of the centrifugal impeller, uncontained centrifugal 
impeller release, damage to the engine, and damage to the helicopter.

DATES: This AD becomes effective December 6, 2016.

ADDRESSES: See the FOR FURTHER INFORMATION CONTACT section.

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-
6990; 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, 1200 
District Avenue, 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 July 28, 2016 (81 FR 
49575). The NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Turbomeca reported an anomaly that was generated during the 
grinding operation associated to the application of modification 
TU376, which increases the clearance between the rear curvic 
coupling of the centrifugal impeller and the fuel injection 
manifold.
    This condition, if not corrected, could lead to crack initiation 
and propagation in the centrifugal impeller bore area, possibly 
resulting in centrifugal impeller failure, with consequent damage 
to, and reduced control of, the helicopter. To address this 
potential unsafe condition, the life of the affected centrifugal 
impellers was reduced and Turbomeca published Mandatory Service 
Bulletin (MSB) 292 72 0848 to inform operators about the life 
reduction and to provide instructions for the replacement of the 
affected centrifugal impellers.
    For the reasons described above, this AD requires replacement of 
each affected centrifugal impeller before it exceeds the applicable 
reduced life limit.

    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-2016-6990.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (81 FR 49575, July 28, 
2016) or on the determination of the cost to the public.

Conclusion

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

Related Service Information

    Turbomeca S.A. has issued Mandatory Service Bulletin (MSB) 292 72 
0848, Version B, dated April 13, 2016. The MSB describes procedures for 
reducing the life limit of the centrifugal impellers affected by an 
anomaly that occurred during the grinding operation required by 
modification TU376. 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 3 engines installed on helicopters 
of U.S. registry. We also estimate that it would take about 22 hours 
per engine to comply with this AD. The average labor rate is $85 per 
hour. Required parts cost about $96,518 per engine. Based on these 
figures, we estimate the cost of this AD on U.S. operators to be 
$295,164.

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.

[[Page 75689]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2016-22-10 Turbomeca S.A.: Amendment 39-186990; Docket No. FAA-2016-
6990; Directorate Identifier 2016-NE-14-AD.

(a) Effective Date

    This AD becomes effective December 6, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to certain Arriel 1, 1A, 1A1, 1A2, 1B, 1B2, 1C, 
1C1, 1C2, 1D, 1D1, 1E, 1E2, 1K1, 1S, and 1S1 turboshaft engines, 
with modification TU376 installed.

(d) Reason

    This AD was prompted by an anomaly that occurred during the 
grinding operation required by modification TU376, which increases 
the clearance between the rear curvic coupling of the centrifugal 
impeller and the fuel injection manifold. We are issuing this AD to 
prevent failure of the centrifugal impeller, uncontained centrifugal 
impeller release, damage to the engine, and damage to the 
helicopter.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Remove from service, any centrifugal impeller listed in 
Table 1 to paragraph (e) of this AD, before exceeding the applicable 
cycles since new (CSN) and replace with a centrifugal impeller not 
listed in Table 1 to paragraph (e) of this AD.

           Table 1 to Paragraph (e)--Centrifugal Impeller CSNs
------------------------------------------------------------------------
                    Part No.                       Serial No.     CSN
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0292254040......................................           44      5,129
0292254040......................................       1762FT     11,476
0292254050......................................      1676CAR      6,281
0292254050......................................      5333OTT      5,495
0292254050......................................      5017OTT      5,491
0292254050......................................      1136CAR      8,734
0292254050......................................      3655OTT      4,600
0292254050......................................      1757CAR      7,913
0292254050......................................      1738CAR     10,640
0292254050......................................      1149CAR     12,273
0292254050......................................      2677OTT     11,145
0292254050......................................      3109OTT     10,662
0292254050......................................      3496OTT      5,562
0292254050......................................      2074CAR      7,423
729225293A......................................       290CAR      6,326
729225293A......................................       1227FT      8,139
729225293A......................................        504FB      4,600
729225293A......................................      2517OTT      9,732
729225293A......................................      2165OTT      6,163
729225293A......................................       2194FT     11,461
729225293A......................................      1331OTT     12,513
729225293A......................................       1301FT      7,262
729225293A......................................       1567FT      6,305
729225293A......................................        783FB      8,307
729225293A......................................        98OTT      9,492
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    (2) Reserved.

(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: ANE-AD-AMOC@faa.gov.

(g) Related Information

    (1) For more information about this AD, contact Philip Haberlen, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, 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 2016-0090, 
dated May 10, 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-2016-6990.

(h) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on October 24, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-26184 Filed 10-31-16; 8:45 am]
 BILLING CODE 4910-13-P