[Federal Register Volume 83, Number 88 (Monday, May 7, 2018)]
[Rules and Regulations]
[Pages 19928-19930]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-09466]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0838; Product Identifier 2017-NE-33-AD; Amendment 
39-19275; AD 2018-10-01]
RIN 2120-AA64


Airworthiness Directives; Safran Helicopter Engines, 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 all 
Safran Helicopter Engines, S.A., Arriel 2E turboshaft engines. This AD 
was prompted by reports of ruptured front support pins on the accessory 
gearbox front support. This AD requires replacement of the accessory 
gearbox front support. We are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD becomes effective June 11, 2018.

ADDRESSES: For service information identified in this final rule, 
contact Safran Helicopter Engines, S.A., 40220 Tarnos, France; phone: 
(33) 05 59 74 40 00; fax: (33) 05 59 74 45 15. You may view this 
service information at the FAA, Engine and Propeller Standards Branch, 
1200 District Avenue, Burlington, MA. For information on the 
availability of this material at the FAA, call 781-238-7759. It is also 
available on the internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2017-0838.

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-2017-
0838; 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 Docket Operations (phone: 800-647-5527) is 
Docket Operations, 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: Robert Green, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue; phone: 781-238-7754; 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 all Safran Helicopter 
Engines, S.A., Arriel 2E turboshaft engines. The NPRM published in the 
Federal Register on November 3, 2017 (82 FR 51170). The NPRM was 
prompted by reports of ruptured front support pins on the accessory 
gearbox front support. The NPRM proposed to require replacement of the 
accessory gearbox front support. We are issuing this AD to address the 
unsafe condition on these products.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2016-0235, dated November 24, 2016 (referred to after this as the 
MCAI), to

[[Page 19929]]

address the unsafe condition on these products. The MCAI states:

    Some cases were reported of ruptured front support pins on 
ARRIEL 1E2 engines. That condition, if not detected and corrected, 
could lead to the loss of the load path integrity of the engine 
front support. Consequently, Turbom[eacute]ca issued Mandatory 
Service Bulletin (MSB) 292 72 0842 to provide instructions for the 
inspection of the pins and front support replacement, and EASA 
issued AD 2015-0064 (later revised) to require those actions. Since 
EASA AD 2015-0064R1 was issued, SAFRAN Helicopter Engines developed 
a new pin design, in order to increase the mechanical strength of 
the pin, through modification TU380, for ARRIEL 1E2 engines. 
Although no cases of front support pin rupture have been reported on 
ARRIEL 2E engines, since the ARRIEL 1E2 and 2E type designs have the 
same front support, SAFRAN Helicopter Engines decided to also apply 
this new pin design on ARRIEL 2E engines through modification TU197. 
To address this potential unsafe condition, SAFRAN Helicopter 
Engines decided, as precautionary measure, to replace the front 
support on ARRIEL 2E engines, and published MSB 292 72 2197 to 
provide instructions for in-service front support replacement. For 
the reasons described above, this [EASA] AD requires modification of 
the affected engines by replacement of each pre-mod TU197 front 
support.

    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-2017-0838.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. We received no comments on the NPRM or on the 
determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this final rule as proposed.

Related Service Information

    We reviewed Safran Helicopter Engines, S.A., Mandatory Service 
Bulletin (MSB) No. 292 72 2197, Version A, dated September 15, 2016. 
The MSB describes procedures for replacement of the accessory gearbox 
front support.

Costs of Compliance

    We estimate that this AD affects 28 engines installed on aircraft 
of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Front support replacement.............  2 work-hours x $85 per           $19,731         $19,901        $557,228
                                         hour = $170.
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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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to engines, propellers, and 
associated appliances to the Manager, Engine and Propeller Standards 
Branch, Policy and Innovation Division.

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):

2018-10-01 Safran Helicopter Engines, S.A.: Amendment 39-19275; 
Docket No. FAA-2017-0838; Product Identifier 2017-NE-33-AD.

(a) Effective Date

    This AD is effective June 11, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Safran Helicopter Engines, S.A., Arriel 
2E turboshaft engines with front support, part number 0 292 11 715 
0, installed (pre-mod TU 197 configuration).

(d) Subject

    Joint Aircraft System Component (JASC) Code 8300, Accessory 
Gearboxes.

(e) Unsafe Condition

    This AD was prompted by reports of ruptured front support pins 
on the accessory gearbox front support. We are issuing this AD to 
prevent failure of a front support, loss of

[[Page 19930]]

engine thrust control and reduced control of the helicopter.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    Before the accessory gearbox and transmission shaft module 
(Module 01) accumulates 1,600 engine operating hours since new, or 
within 80 engine operating hours after the effective date of this 
AD, whichever occurs later, replace the front support with a part 
eligible for installation.

(h) Definition

    For the purpose of this AD, a part eligible for installation is 
a Module 01 with a pre-mod TU 197 front support, that has not 
accumulated more than 1,680 engine operating hours since new; or a 
Module 01 with a post-mod TU 197 front support.

(i) Installation Prohibition

    As of the effective date of this AD, you may not install a pre-
mod TU 197 front support on any engine with a post-mod TU 197 front 
support installed.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, FAA, ECO Branch, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the manager of the 
ECO Branch, send it to the attention of the person identified in 
paragraph (k)(1) of this AD. You may email your request to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(k) Related Information

    (1) For more information about this AD, contact Robert Green, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7754; fax: 781-238-7199; email: 
[email protected].
    (2) Refer to EASA AD 2016-0235, dated November 24, 2016, for 
more information. You may examine the EASA AD in the AD docket on 
the internet at http://www.regulations.gov by searching for and 
locating it in Docket No. FAA-2017-0838.

(l) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on May 1, 2018.
Karen M. Grant,
Acting Manager, Engine and Propeller Standards Branch, Aircraft 
Certification Service.
[FR Doc. 2018-09466 Filed 5-4-18; 8:45 am]
 BILLING CODE 4910-13-P