Document ID: FAA-2018-0184-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Safran Helicopter Engines, S.A., Turboshaft Engines
Posted Date: 2018-04-12T04:00Z

[Federal Register Volume 83, Number 71 (Thursday, April 12, 2018)]
[Rules and Regulations]
[Pages 15731-15733]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-07541]

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 Rules and Regulations
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  Federal Register / Vol. 83, No. 71 / Thursday, April 12, 2018 / Rules 
and Regulations  

[[Page 15731]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0184; Product Identifier 2018-NE-07-AD; Amendment 
39-19248; AD 2018-07-17]
RIN 2120-AA64

Airworthiness Directives; Safran Helicopter Engines, S.A., 
Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Safran Helicopter Engines, S.A., Arrius 2B1, 2B1A, 2B2, and 2K1 
turboshaft engines. This AD requires inspecting the power turbine wheel 
(PTW) assembly and replacing the PTW if the turbine blade dampers are 
found missing. This AD was prompted by the manufacturer reporting a 
number of PTW assemblies may have been assembled without the blade 
dampers. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD becomes effective April 27, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 27, 
2018.
    We must receive comments on this AD by May 29, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    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 & Propeller Standards Branch, 1200 
District Avenue, Burlington, MA 01803. 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-2018-0184.

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-2018-
0184; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the mandatory continuing airworthiness information 
(MCAI), the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (phone: 800-647-
5527) is listed above. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION 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].

SUPPLEMENTARY INFORMATION: 

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2018-0044, dated February 14, 2018 (referred to after this as the 
MCAI), to address an unsafe condition for the specified products. The 
MCAI states:

    During an ARRIUS 2B2 engine ground run check, the ``Degrade'' 
indicator illuminated and unusual vibration occurred. At the same 
time, bluish smoke and debris came out of the exhaust pipe. Both 
engines were shut down without further occurrences.
    Investigations at Safran Helicopter Engines revealed that 
missing dampers on the PTW assembly caused rupture of PTW blades. 
Further investigations identified a batch of potentially affected 
PTW.
    The dampers on the PTW blades reduce the mechanical stress 
exerted on the blades. With no dampers, mechanical stress on the 
blades can exceed the vibratory fatigue limit, eventually leading to 
rupture of the blades.
    This condition, if not corrected, could lead to In Flight Shut 
Down and release of low energy debris through exhaust pipe, 
potentially resulting in forced landing, damage to the helicopter 
and injury to occupants.
    To address this potential unsafe condition, Safran Helicopter 
Engines issued the SB to provide instructions for inspection and PTW 
replacement.
    For the reasons described above, this [EASA] AD requires 
replacement of potentially affected PTWs with serviceable parts.

    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-2018-0184.

Related Service Information Under 1 CFR Part 51

    We reviewed Safran Helicopter Engines Alert Mandatory Service 
Bulletin (MSB) No. A319 72 2854, Version A, dated February 9, 2018. The 
MSB describes procedures for replacing the PTW. 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.

FAA's Determination

    This product has been approved by 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 the relevant 
information provided by EASA and determined the unsafe condition 
described previously is likely to exist or develop in other products of 
the same type design.

[[Page 15732]]

AD Requirements

    This AD requires inspecting the PTW assembly and replacing the PTW 
if the turbine blade dampers are found missing.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies waiving notice and comment prior to adoption of this rule 
because the compliance time for the action is less than the time 
required for public comment. EASA made a determination of an unsafe 
condition warranting regulatory action and compliance within 20 flight 
hours or 30 days. Therefore, we find good cause that notice and 
opportunity for prior public comment are impracticable. In addition, 
for the reason stated above, we find that good cause exists for making 
this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this final rule. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number FAA-2018-
0184 and Product Identifier 2018-NE-07-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this final rule. We will 
consider all comments received by the closing date and may amend this 
final rule because of 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 we 
receive about this final rule.

Costs of Compliance

    We estimate that this AD affects 46 engines installed on 
helicopters 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
----------------------------------------------------------------------------------------------------------------
Records Search........................  1 work-hour x $85 per                 $0             $85          $3,910
                                         hour = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the mandated inspection. 
We have no way of determining the number of aircraft that might need 
these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
PTW replacement...............................  16 work-hours x $85 per hour =           $16,500         $17,860
                                                 $1,360.
----------------------------------------------------------------------------------------------------------------

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 Manager, Engine and Propeller Standards 
Branch, Policy and Innovation Division.

Regulatory Findings

    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, 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 15733]]

Sec.  39.13   [Amended]

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

2018-07-17 Safran Helicopter Engines (Type Certificate previously 
held by Turbomeca, S.A.): Amendment 39-19248; Docket No. FAA-2018-
0184; Product Identifier 2018-NE-07-AD.

(a) Effective Date

    This AD is effective April 27, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Safran Helicopter Engines, S.A., Arrius 2B1, 
2B1A, 2B2, and 2K1 turboshaft engines with a power turbine wheel 
(PTW) assembly having a serial number listed in Appendix 2.1 of 
Safran Helicopter Engines Mandatory Service Bulletin (MSB) No. A319 
72 2854, Version A, dated February 9, 2018.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
Section.

(e) Unsafe Condition

    This AD was prompted by an engine failure caused by missing 
turbine blade dampers. We are issuing this AD to prevent failure of 
a power turbine blade. The unsafe condition, if not addressed, could 
result in loss of engine power in flight and reduced control of the 
helicopter.

(f) Compliance

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

(g) Required Actions

    Within 20 flight hours or 30 days after the effective date of 
this AD, whichever occurs first:
    (1) Inspect the PTW in accordance with paragraph 2.4.2.3 of 
Safran Helicopter Engines MSB No. A319 72 2854, Version A, dated 
February 9, 2018; and
    (2) If, as a result of the inspection required by paragraph 
(g)(1) of this AD, any dampers are found missing, replace the PTW 
with a part eligible for installation before further flight.

(h) Installation Prohibition

    Do not install an engine with a PTW with a serial number listed 
in Appendix 2.1 of Safran Helicopter Engines MSB A319 72 2854, 
Version A, dated February 9, 2018, unless all thirty-one blade 
dampers are installed.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO Branch, FAA, 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 
certification office, send it to the attention of the person 
identified in paragraph (j)(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.

(j) 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 European Aviation Safety Agency (EASA) AD 2018-
0044, dated February 14, 2018, 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-2018-0184.

(k) 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) Safran Helicopter Engines Alert Mandatory Service Bulletin 
No. A319 72 2854, Version A, dated February 9, 2018.
    (ii) Reserved.
    (3) For Safran Helicopter Engines service information identified 
in this AD, contact Safran Helicopter Engines, S.A., 40220 Tarnos, 
France; phone: (33) 05 59 74 40 00; fax: (33) 05 59 74 45 15.
    (4) You may view this service information at FAA, Engine & 
Propeller Standards Branch, 1200 District Avenue, Burlington, MA. 
For information on the availability of this material at the FAA, 
call 781-238-7759.
    (5) You may view this service information that is incorporated 
by reference 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 6, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-07541 Filed 4-11-18; 8:45 am]
 BILLING CODE 4910-13-P