
[Federal Register Volume 84, Number 41 (Friday, March 1, 2019)]
[Rules and Regulations]
[Pages 6962-6965]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-03641]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0949; Product Identifier 2018-NE-20-AD; Amendment 
39-19484; AD 2018-22-11]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Safran Helicopter Engines, S.A. (Safran Helicopter Engines), ASTAZOU 
XIV B and H model engines with certain 3rd-stage turbine wheels 
installed. This AD requires initial and repetitive inspections of the 
3rd-stage turbine wheels. This AD was prompted by a report that six 
3rd-stage turbine wheels were returned to service after a repair that 
could result in exceedance of the allowable vibration threshold during 
operation. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective March 18, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 18, 
2019.
    We must receive comments on this AD by April 15, 2019.

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 Safran Helicopter Engines service information identified in 
this final rule, contact Safran Helicopter Engines, S.A., 40220 Tarnos, 
France; phone: +33 5 59 74 45 15; internet address: https://www.safran-helicopter-engines.com/services/technical-assistance. 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-2018-0949.

Examining the AD Docket

    You may examine the AD docket on the internet at http://
www.regulations

[[Page 6963]]

.gov by searching for and locating Docket No. FAA-2018-0949; 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: Barbara Caufield, Aerospace Engineer, 
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 
781-238-7146; fax: 781-238-7199; email: barbara.caufield@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    The European Union Aviation Safety Agency (EASA), which is the 
Technical Agent for the Member States of the European Community, has 
issued EASA AD 2018-0085, dated April 13, 2018 (referred to after this 
as ``the MCAI''), to address an unsafe condition for the specified 
products. The MCAI states:

    Safran Helicopter Engines reported that an identified batch of 
stage 3 turbine wheels were released to service after repair in 
spite of the fact that the natural frequency of the turbine blades 
installed on those wheels did not comply with the acceptance 
criteria. Excessive turbine blade vibration may lead to progressive 
crack initiation on the rear face of the affected turbine wheel.
    This condition, if not detected and corrected, could lead to 
rupture of a turbine blade and its associated piece of rim, possibly 
resulting in an un-commanded engine in-flight shut-down and/or 
release of high energy debris, with consequent damage to, and/or 
reduced control of, the helicopter.
    To address this potentially unsafe condition, Safran Helicopter 
Engines issued the MSB to provide inspections instructions.
    For the reasons described above, this AD requires repetitive 
inspections of the affected parts and, depending on findings, 
accomplishment of applicable corrective action(s).

    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-2018-0949.

Related Service Information Under 1 CFR Part 51

    We reviewed Safran Helicopter Engines Mandatory Service Bulletin 
(MSB) 283 72 0813, Version A, dated February 26, 2018. The MSB 
describes procedures for inspecting the rear face 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.

FAA's Determination

    This product has been approved by EASA, 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.

AD Requirements

    This AD requires initial and repetitive inspections of 3rd-stage 
turbine wheels.

FAA's Justification and Determination of the Effective Date

    No domestic operators use this product. Therefore, we find good 
cause that notice and opportunity for prior public comment are 
unnecessary. 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-
0949 and Product Identifier 2018-NE-20-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 zero engines installed on 
helicopters of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
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                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
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Inspect the 3rd-stage turbine wheel...  5 work-hours x $85 per                $0            $425              $0
                                         hour = $425.
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    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need this 
replacement:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace the 3rd-stage turbine wheel...........  8 work-hours x $85 per hour =           $217,131        $217,811
                                                 $680.
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[[Page 6964]]

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

    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.


Sec.  39.13   [Amended]

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

2018-22-11 Safran Helicopter Engines (Type Certificate previously 
held by Turbomeca, S.A.): Amendment 39-19484; Docket No. FAA-2018-
0949; Product Identifier 2018-NE-20-AD.

(a) Effective Date

    This AD is effective March 18, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Safran Helicopter Engines, S.A. (Safran 
Helicopter Engines), ASTAZOU XIV B and H model engines with the 3rd-
stage turbine wheels specified in Figure 1 to paragraph (c) of this 
AD installed.

     Figure 1 to Paragraph (c) of This AD--3rd-Stage Turbine Wheels
------------------------------------------------------------------------
              Part Nos.                           Serial Nos.
------------------------------------------------------------------------
0 265 25 706 0......................  AD78691AD, AD78703AD, AD93845AD,
                                       CC52860, RD39596
0 265 25 705 0......................  L232AD
------------------------------------------------------------------------

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report that six 3rd-stage turbine 
wheels were returned to service after a repair that could result in 
exceedance of the allowable vibration threshold during operation. We 
are issuing this AD to prevent failure of the 3rd-stage turbine 
wheel. The unsafe condition, if not addressed, could result in loss 
of engine power and reduced control of the helicopter.

(f) Compliance

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

(g) Required Action

    (1) Perform an inspection of the 3rd-stage turbine wheel as 
follows:
    (i) Before exceeding 400 engine cycles since the last engine 
overhaul, or within 50 engine start stop cycles after the effective 
date of this AD, whichever occurs later, inspect the rear face of 
each affected 3rd-stage turbine wheel in accordance with the 
Accomplishment Instructions, paragraphs 2.4.2 and 2.4.3, in Safran 
Helicopter Engines Mandatory Service Bulletin (MSB) 283 72 0813, 
Version A, dated February 26, 2018.
    (ii) After that, repeat the inspection required by paragraph 
(g)(1)(i) of this AD at intervals not to exceed 400 engine cycles 
since the last inspection.
    (iii) A one-time, non-cumulative tolerance of 50 engine cycles 
may be applied to the repetitive inspection interval required by 
paragraph (g)(1)(ii) of this AD.
    (2) If a crack indication is found during any inspection 
required by paragraph (g)(1) of this AD, remove the engine from 
service and repair the 3rd-stage turbine wheel in accordance with 
the Accomplishment Instructions, paragraph 4.3, in Safran Helicopter 
Engines MSB 283 72 0813, Version A, dated February 26, 2018.

(h) Terminating Action

    A repair of the 3rd-stage turbine wheel in accordance with the 
Accomplishment Instructions, paragraph 4.3, in Safran Helicopter 
Engines MSB 283 72 0813, Version A, dated February 26, 2018, 
constitutes terminating action for the requirements of this AD for 
that engine.

(i) Definition

    For the purpose of this AD, calculate ``non-cumulative 
tolerance'' by adding 50 engine cycles to the inspection interval of 
400 engine cycles since the last inspection. For example, you may 
add 50 additional engines cycles to the 400 cycles since last 
inspection requirement to obtain an inspection interval of 450 
engine cycles. Once this non-cumulative tolerance has been applied, 
all repetitive inspection intervals are required within 400 engine 
cycles of the previous inspection.

(j) No Reporting Requirement

    No reporting requirement contained within the MSB referenced in 
paragraphs (g)(1) and (2) of this AD are required by this AD.

(k) 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 (l)(1) of this AD. You may email your 
request to: ANE-AD-AMOC@faa.gov.
    (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.

(l) Related Information

    (1) For more information about this AD, contact Barbara 
Caufield, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7146; fax: 781-238-7199; email: 
barbara.caufield@faa.gov.

[[Page 6965]]

    (2) Refer to European Union Aviation Safety Agency (EASA) AD 
2018-0085, dated April 13, 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-2018-0949.

(m) 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 Mandatory Service Bulletin 283 72 
0813, Version A, dated February 26, 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 5 59 74 45 15; internet address: https://www.safran-helicopter-engines.com/services/technical-assistance.
    (4) You may view this service information at 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.
    (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 February 21, 2019.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2019-03641 Filed 2-28-19; 8:45 am]
 BILLING CODE 4910-13-P


