[Federal Register Volume 86, Number 47 (Friday, March 12, 2021)]
[Proposed Rules]
[Pages 14017-14020]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-05047]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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 

  Federal Register / Vol. 86, No. 47 / Friday, March 12, 2021 / 
Proposed Rules  

[[Page 14017]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0137; Project Identifier MCAI-2020-00269-E]
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: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2014-04-06, which applies to all Safran Helicopter Engines, S.A. 
(Safran Helicopter Engines) Arrius 2B1, 2B1A, 2B2, and 2K1 model 
turboshaft engines. AD 2014-04-06 requires initial and repetitive 
inspections of the hydro-mechanical metering unit (HMU) high pressure 
pump drive gear shaft splines, cleaning and inspections of the sleeve 
assembly splines, and replacement of the sleeve assembly on the 
affected high pressure pump drive gear shaft or replacement of the HMU 
if the HMU fails inspection. Since the FAA issued AD 2014-04-06, the 
manufacturer has published new service information that revises the 
inspections for certain HMUs and reduces compliance times for initial 
inspections. This proposed AD would require revised inspections and 
continue to require cleaning of the sleeve assembly splines, and 
replacement of the sleeve assembly on the affected high pressure pump 
drive gear shaft or replacement of the HMU if the HMU fails an 
inspection. The FAA is proposing this AD to address the unsafe 
condition on these products.

DATES: The FAA must receive comments on this proposed AD by April 26, 
2021.

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 https://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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0137; 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 NPRM, the 
mandatory continuing airworthiness information (MCAI), any comments 
received, and other information. The street address for Docket 
Operations is listed above.

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: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2021-0137; Project Identifier 
MCAI-2020-00269-E'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
the proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to Wego 
Wang, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803. Any commentary that the FAA receives which is not 
specifically designated as CBI will be placed in the public docket for 
this rulemaking.

Background

    The FAA issued AD 2014-04-06, Amendment 39-17764 (79 FR 9990, 
February 24, 2014), (AD 2014-04-06), for all Turbomeca S.A. Arrius 2B1, 
2B1A, 2B2, and 2K1 model turboshaft engines. AD 2014-04-06 was prompted 
by in-flight shutdowns caused by interrupted fuel supply at the HMU. AD 
2014-04-06 requires initial and repetitive inspections of the HMU high 
pressure pump drive gear shaft splines, cleaning and inspections of the 
sleeve assembly splines, and replacement of the sleeve assembly on the 
affected high pressure pump drive gear shaft or replacement of the HMU 
if the HMU fails inspection. The agency issued AD 2014-04-06 to prevent 
in-flight shutdown and damage to the engine.

[[Page 14018]]

Actions Since AD 2014-04-06 Was Issued

    Since the FAA issued AD 2014-04-06, the manufacturer has published 
new service information that revises the inspections for certain HMUs, 
reduces compliance times for initial inspections, and allows 
application of non-cumulative tolerance of 10% of operating hours to be 
applied to the timing of the repetitive inspection of HMUs installed on 
certain engines.
    The European Union Aviation Safety Agency (EASA), which is the 
Technical Agent for the Member States of the European Community, has 
issued EASA AD 2020-0033, dated February 25, 2020 (referred to after 
this as ``the MCAI''), to address the unsafe condition on these 
products. The MCAI states:

    A number of in-flight shutdown (IFSD) occurrences have been 
reported for ARRIUS 2 engines. The results of the technical 
investigations concluded that these events were caused by 
deterioration of the splines on the high pressure (HP)/low pressure 
(LP) pump assembly drive shaft of the HMU, which eventually 
interrupted the fuel supply to the engine.
    This condition, if not detected and corrected, could lead to 
further cases of engine IFSD, possibly resulting in forced landing 
with consequent damage to the helicopter and injury to occupants. To 
address these occurrences, Turbomeca published MSB 319 73 2825 (up 
to version G) to provide instructions for inspection of the HMU and 
sleeve assembly. Consequently, EASA issued AD 2013-0082 to require 
repetitive inspections of the drive gear shaft splines of the HP 
pump, and, depending on findings, accomplishment of applicable 
corrective action(s).
    Since that [EASA] AD was issued, SAFRAN published the MSB to 
provide specific inspection instructions for HMU installed on a 
helicopter after 31 January 2013, to reduce the compliance time for 
the initial inspection of Group 1 engines that were not previously 
inspected in accordance with version G or later of the MSB, and to 
provide some operational margin before the first inspection in all 
possible scenarios.
    For the reason described above, this [EASA] AD retains the 
requirements of AD 2013-0082, which is superseded, and requires 
accomplishment of the actions in accordance with the instructions of 
the MSB, as defined in this [EASA] AD.

    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-2021-0137.

FAA's Determination

    This product has been approved by EASA and is approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Community, EASA has notified the agency of 
the unsafe condition described in the MCAI and service information. The 
FAA is issuing this NPRM because the agency 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.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Safran Helicopter Engines Mandatory Service 
Bulletin (MSB) No. 319 73 2825, Version J, dated March 15, 2019. The 
MSB describes procedures for inspecting the HMU high pressure pump 
drive gear shaft splines and cleaning and inspecting the sleeve 
assembly splines. 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.

Proposed AD Requirements in This NPRM

    This proposed AD would retain certain requirements of AD 2014-04-
06. This proposed AD would require initial and repetitive inspections 
of the HMU high pressure pump drive gear shaft splines. This proposed 
AD would require cleaning of the sleeve assembly splines. This proposed 
AD would also require replacing the HMU or the sleeve assembly on the 
affected high pressure pump drive gear shaft if the HMU fails 
inspection.

Differences Between This Proposed AD and the Service Information or the 
MCAI

    EASA AD 2020-0033 identifies applicable engines as Safran 
Helicopter Engines Arrius 2B1, 2B1A, 2B2, 2G1, 2K1 and 2K2 model 
turboshaft engines, all serial numbers. This AD does not include Safran 
Helicopter Engines Arrius 2G1 and 2K2 model turboshaft engines in its 
applicability since these engines are not type certificated in the 
United States.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 194 engines installed on helicopters of U.S. registry.
    The FAA estimates the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Visual inspection of drive gear shaft   2 work-hours x $85 per              $900          $1,070        $207,580
 splines; cleaning and inspection of     hour = $170.
 sleeve assembly splines.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
replacements that would be required based on the results of the 
proposed inspection. The agency has no way of determining the number of 
aircraft that might need these replacements.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace sleeve assembly on high-pressure pump   1 work-hour x $85 per hour = $85            $898            $983
 drive gear shaft.
Replace HMU...................................  1 work-hour x $85 per hour = $85          45,000          45,085
----------------------------------------------------------------------------------------------------------------


[[Page 14019]]

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

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would 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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:
0
a. Removing Airworthiness Directive 2014-04-06, Amendment 39-17764 (79 
FR 9990, February 24, 2014), and
0
b. Adding the following new airworthiness directive:

Safran Helicopter Engines, S.A. (Type Certificate previously held by 
Turbomeca, S.A.): Docket No. FAA-2021-0137; Project Identifier MCAI-
2020-00269-E.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) action by April 26, 2021.

(b) Affected ADs

    This AD replaces AD 2014-04-06, Amendment 39-17764 (79 FR 9990, 
February 24, 2014).

(c) Applicability

    This AD applies to Safran Helicopter Engines, S.A. (Type 
Certificate previously held by Turbomeca, S.A.) Arrius 2B1, 2B1A, 
2B2, and 2K1 model turboshaft engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7320--Fuel 
Controlling System.

(e) Unsafe Condition

    This AD was prompted by in-flight shutdowns caused by 
interrupted fuel supply at the hydro-mechanical metering unit (HMU). 
The FAA is issuing this AD to prevent interrupted fuel supply at the 
HMU. The unsafe condition, if not addressed, could result in engine 
in-flight shutdown, forced landing of the helicopter, damage to the 
helicopter and injury to occupants.

(f) Compliance

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

(g) Required Actions

    (1) Within the compliance time specified in Table 1 to paragraph 
(g)(1) of this AD, as applicable, and before re-installation of the 
HMU after each removal from the engine, visually inspect the drive 
gear shaft splines of the high pressure pump, and clean and inspect 
the sleeve assembly splines in accordance with paragraphs 2.4.2 and 
2.4.3, or 4.4.2 and 4.4.3, as applicable, of Safran Helicopter 
Engines Mandatory Service Bulletin (MSB) 319 73 2825, Version J, 
dated March 15, 2019.

                       Table 1 to Paragraph (g)(1)
------------------------------------------------------------------------
          HMU group/condition                    Compliance time
------------------------------------------------------------------------
Group 1/150 HMU operating hours or more  Within 50 HMU operating hours
 accumulated since new or since last      after the effective date of
 overhaul..                               this AD.
Group 1/Less than 150 HMU operating      Before exceeding 200 HMU
 hours accumulated since new or since     operating hours after the
 last overhaul..                          effective date of this AD.
Group 2................................  Within 500 HMU operating hours
                                          since the last inspection or
                                          since first installation of
                                          the HMU.
------------------------------------------------------------------------

    (2) Repeat the inspection required by paragraph (g)(1) of this 
AD at intervals not to exceed 500 HMU operating hours since the 
previous inspection.

    Note 1 to paragraph (g)(2): A non-cumulative tolerance of 10% of 
HMU operating hours (hrs) may be applied to the timing of each 
repetitive inspection, with a maximum allowable tolerance of +50 HMU 
operating hrs. For example, counting from the initial inspection, 
the repeat inspections would occur at the following times, with the 
tolerance noted in parentheses; 500 HMU operating hrs (+50 hrs), 
1000 HMU operating hrs (+50 hrs), 1500 HMU operating hrs (+50 hrs).

    (3) If a rejectable indication is found during any inspection 
required by paragraphs (g)(1) or (2) of this AD, replace the sleeve 
assembly on the affected high-pressure pump drive gear shaft or 
replace the affected HMU in accordance with paragraph 2.4.2 or 4.4.2 
of the MSB.

(h) Definitions

    (1) A Group 1 HMU is an HMU that was first installed on or 
before January 31, 2013, and that has not previously been inspected 
in accordance with Safran Helicopter Engines MSB 319 73 2825 version 
G or later.
    (2) A Group 2 HMU is an HMU that was first installed after 
January 31, 2013, or a HMU that has previously been inspected in 
accordance with Safran Helicopter Engines MSB 319 73 2825 version G 
or later.

(i) No Reporting Requirement

    The reporting requirements specified in the Accomplishment 
Instructions, paragraph 2.4.2, of the MSB are not required by this 
AD.

(j) Credit for Previous Actions

    You may take credit for any initial inspection or replacement of 
an HMU or the sleeve assembly on the affected high-pressure pump 
drive gear shaft required by paragraph (g) of this AD if you 
performed the inspection or replacement in accordance with Safran 
Helicopter Engines MSB 319 73 2825, version G, dated January 24, 
2013; version H, dated

[[Page 14020]]

September 1, 2014; or version I, dated April 26, 2016.

(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 
ECO Branch, send it to the attention of the person identified in 
Related Information. Information may be emailed 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.

(l) 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: [email protected].
    (2) Refer to European Union Aviation Safety Agency (EASA) AD 
2020-0033, dated February 25, 2020, for more information. You may 
examine the EASA AD in the AD docket at http://www.regulations.gov 
by searching for and locating it in Docket No. FAA-2021-0137.
    (3) For service information identified in this AD, contact 
Safran Helicopter Engines, S.A., Avenue du 1er Mai, Tarnos, France; 
phone: +33 (0) 5 59 74 40 00. You may view this referenced 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.

    Issued on March 5, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-05047 Filed 3-11-21; 8:45 am]
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