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2021-05-08 SAFRAN HELICOPTER ENGINES, S.A. (TYPE CERTIFICATE PREVIOUSLY HELD BY TURBOMECA, S.A.): Amendment 39-21451; Docket No. FAA-2020-1118; Project Identifier MCAI-2020-00516-E.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective April 15, 2021.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies to all Safran Helicopter Engines, S.A.  (Type Certifi-
    cate previously held by Turbomeca, S.A.)  Arriel 2C, 2C1, 2S1, and 2S2
    model turboshaft engines.

(d) SUBJECT

    Joint Aircraft System Component (JASC)  Code 7712,  Engine BMEP/Torque
    Indicating.

(e) UNSAFE CONDITION

    This AD was prompted  by investigations by the  manufacturer following
    level 1 failures in flight  (minor anomalies) and level 2  failures on
    the ground (minor failures), where  cracks were found on the  soldered
    joints of  torque conformation  boxes. The  FAA is  issuing this AD to
    prevent failure of the torque conformation box. The unsafe  condition,
    if not  addressed, could  result in  failure of  the engine, in-flight
    shutdown, and loss of the helicopter.

(f) COMPLIANCE

    Comply with this AD within the compliance times specified,  unless al-
    ready done.

(g) REQUIRED ACTIONS

(1) For engines with the torque conformation box in pre-modification TU 34
    configuration installed on Arriel 2C and 2C1 model turboshaft engines;
    pre-modification TU 34  or post-modification TU 188 configuration, in-
    stalled on Arriel 2S1 model turboshaft engines or post-modification TU
    188 configuration, installed on Arriel 2S2 model turboshaft engines:

(i) Within 600 engine hours (EHs)  or 180 days after the effective date of
    this AD, whichever occurs first,  perform an initial inspection of the
    resistance values of the torque conformation box.

Note 1 to paragraph (g)(1)(i):  You may delay the initial inspection by up
to 60 EHs to align with other scheduled maintenance tasks.

(ii) Thereafter,  perform repetitive inspections  of the resistance values
     of the  torque conformation  box before  exceeding 600  EHs since the
     last inspection of the  resistance values of the  torque conformation
     box.

(2) Use  the  Accomplishment  Instructions,  paragraph 2.3.2 or 4.3.2,  of
    Safran Helicopter Engines  Mandatory Service Bulletin No. 292 72 2868,
    Version A, dated December 2018,  to  perform  the  inspections  of the
    resistance values of the torque conformation box required by paragraph
    (g)(1) of this AD.

(3) If,  during any inspection required  by paragraph (g)(1) of this AD, a
    non-conforming  resistance  value  is  found,  before  further flight,
    remove the torque conformation box from service and replace it with  a
    part eligible for installation.

(h) DEFINITION

    For the purpose of  this AD,  a "part eligible for installation" is  a
    zero hour torque  conformation box or  a torque conformation  box that
    has been inspected as required by paragraph (g)(1) of this AD.

(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 Related
    Information. You may email your request to: ANE-AD-AMOC@faa.gov.

(2) Before using any approved AMOC,  notify your appropriate principal in-
    spector, 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 Wego Wang, Aviation Safety
    Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803;
    phone: (781) 238-7134; fax: (781) 238-7199; email: wego.wang@faa.gov.

(2) Refer to European Union  Aviation Safety Agency  (EASA)  AD 2019-0110,
    dated May 21, 2019, for more information.  You may examine the EASA AD
    in the AD docket  at https://www.regulations.gov  by searching for and
    locating Docket No. FAA-2020-1118.

(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  Mandatory Service Bulletin No. 292 72 2868,
    Version A, dated December 2018.

(ii) [Reserved]

(3) For Safran Helicopter Engines  service information  identified in this
    AD, contact Safran Helicopter Engines, S.A., Avenue du 1er Mai, Tarnos
    France; phone: +33 (0) 5 59 74 45 11.

(4) You may view this service information at FAA,  Airworthiness  Products
    Section,  Operational Safety 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 refer-
    ence at the National Archives and Records Administration  (NARA).  For
    information on the availability  of  this  material  at  NARA,  email:
    fedreg.legal@nara.gov,  or  go  to:  https://www.archives.gov/federal-
    register/cfr/ibr-locations.html.

Issued on February 19, 2021.  Lance T. Gant,  Director,  Compliance & Air-
worthiness Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Wego Wang,  Aviation Safety Engineer, ECO
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238-
7134; fax: (781) 238-7199; email: wego.wang@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-1118; Project Identifier MCAI-2020-00516-E;
Amendment 39-21451; AD 2021-05-08]
RIN 2120-AA64

Airworthiness Directives; Safran Helicopter Engines, S.A. (Type
Certificate Previously Held by Turbomeca, S.A.) Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Safran Helicopter Engines, S.A. Arriel 2C, 2C1, 2S1, and 2S2 model
turboshaft engines. This AD was prompted by investigations by the
manufacturer following level 1 failures in flight (minor anomalies) and
level 2 failures on the ground (minor failures), where cracks were
found on the soldered joints of torque conformation boxes. This AD
requires performing initial and repetitive inspections of the
resistance values of the torque conformation box and, depending on the
results of the inspections, replacement of the torque conformation box.
The FAA is issuing this AD to address the unsafe condition on these
products.

DATES: This AD is effective April 15, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 15,
2021.

ADDRESSES: For service information identified in this final rule,
contact Safran Helicopter Engines, S.A., Avenue du 1er Mai, Tarnos,
France; phone: +33 (0) 5 59 74 45 11. You may view this service
information at the FAA, Airworthiness Products Section, Operational
Safety 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 at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-1118.

Examining the AD Docket

You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-1118; 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), any comments
received, and other information. The address for Docket Operations is
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, Aviation Safety Engineer,
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone:
(781) 238-7134; fax: (781) 238-7199; email: wego.wang@faa.gov.

SUPPLEMENTARY INFORMATION:

Background

The FAA 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 2C, 2C1, 2S1, and 2S2 model turboshaft engines.
The NPRM published in the Federal Register on
December 10, 2020 (85 FR 79438). The NPRM was prompted by
investigations by the manufacturer following level 1 failures in flight
(minor anomalies) and level 2 failures on the ground (minor failures),
where cracks were found on the soldered joints of torque conformation
boxes. In the NPRM, the FAA proposed to require performing initial and
repetitive inspections of the resistance values of the torque
conformation box and, depending on the results of the inspections,
replacement of the torque conformation box. The FAA is issuing this AD
to address the unsafe condition on these products.
The European Union Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Community, has
issued EASA AD 2019-0110, dated May 21, 2019 (referred to after this as
``the MCAI''), to address the unsafe condition on these products. The
MCAI states:

It was reported that, during investigations following level 1
failures in flight (minor anomalies) and level 2 failures on the
ground (minor failures), cracks were found on the soldered joints of
certain torque conformation boxes. Although no events in operation
were reported of One Engine Inoperative (OEI) ratings maximum power
unavailability, the failure mode analysis for these boxes
demonstrated that such event could not be excluded. This condition,
if not detected and corrected, could lead to engine in-flight shut-
down, possibly resulting in reduced control of the helicopter.
To address this potential unsafe condition, SAFRAN Helicopter
Engines issued the SB [Service Bulletin], to provide instructions
for repetitive checks of the box resistance values. For the reasons
described above, this [EASA] AD requires repetitive checks of the
affected part and, depending on findings, replacement of the
affected part with a serviceable part.

You may obtain further information by examining the MCAI in the AD
docket at https://www.regulations.gov by searching for and locating
Docket No. FAA-2020-1118.

Discussion of Final Airworthiness Directive Comments

The FAA received no comments on the NPRM or on the determination of
the costs.

Conclusion

The FAA reviewed the relevant data and determined that air safety
requires adopting this AD as proposed. Accordingly, the FAA is issuing
this AD to address the unsafe condition on these products. This AD is
adopted as proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

The FAA reviewed Safran Helicopter Engines Mandatory Service
Bulletin (MSB) No. 292 72 2868, Version A, dated December 2018. This
service information specifies procedures for performing an inspection
of the resistance values of the torque conformation box. 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 ADDRESSES.

Costs of Compliance

The FAA estimates that this AD affects 257 engines installed on
helicopters of U.S. registry.
The FAA estimates the following costs to comply with this AD:

Estimated Costs

Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspect resistance values of the torque conformation box. 1 work-hour x $85 per hour = $85 $0 $85 $21,845

The FAA estimates the following costs to do any necessary
replacement that would be required based on the results of the
inspections. The agency has no way of determining the number of
aircraft that might need this replacement:

On-Condition Costs

Action Labor cost Parts cost Cost per product
Replace the torque conformation box 1 work-hour x $85 per hour = $85 $1,841 $1,926

The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected individuals.

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.
The FAA is 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

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) Will not affect intrastate aviation in Alaska, and
(3) 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.

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

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]

2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive: