[Federal Register Volume 83, Number 153 (Wednesday, August 8, 2018)]
[Proposed Rules]
[Pages 39007-39009]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-16494]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0669; Product Identifier 2017-SW-041-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Previously 
Eurocopter France)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2016-25-
19 for Airbus Helicopters (previously Eurocopter France) Model AS350B3 
and EC130B4 helicopters. AD 2016-25-19 requires inspecting the pilot's 
and co-pilot's throttle twist for proper operation. This proposed AD 
would retain the requirements of AD 2016-25-19 and add certain model 
helicopters to the applicability. The actions of this proposed AD are 
intended to address the unsafe condition on these helicopters.

DATES: We must receive comments on this proposed AD by October 9, 2018.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
    <bullet> Fax: 202-493-2251.
    <bullet> Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
    <bullet> Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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-
0669; 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 proposed AD, the European Aviation Safety Agency (EASA) AD, the 
economic evaluation, any comments received and other information. The 
street address for Docket Operations (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.
    For service information identified in this proposed rule, contact 
Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at 
http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You may review service information at the FAA, Office 
of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 
6N-321, Fort Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: George Schwab, Aviation Safety 
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; 
email <a href="/cdn-cgi/l/email-protection#3a5d5f55485d5f144959524d5b587a5c5b5b145d554c"><span class="__cf_email__" data-cfemail="a1c6c4ced3c6c48fd2c2c9d6c0c3e1c7c0c08fc6ced7">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to participate in this rulemaking by submitting 
written comments, data, or views. We also invite comments relating to 
the economic, environmental, energy, or federalism impacts that might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. To 
ensure the docket does not contain duplicate comments, commenters 
should send only one copy of written comments, or if comments are filed 
electronically, commenters should submit only one time.
    We will file in the docket all comments that we receive, as well as 
a report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    We issued AD 2016-25-19, Amendment 39-18745 (81 FR 95854, December 
29, 2016) (AD 2016-25-19), for Airbus Helicopters Model AS350B3 and 
EC130B4 helicopters with the ARRIEL 2B1 engine with the two-channel 
Full Authority Digital Engine Control (FADEC) and with new twist grip 
modification (MOD) 073254 (for the Model AS350B3 helicopter) or MOD 
073773 (for the Model EC130B4 helicopter). AD 2016-25-19 requires 
repetitively inspecting the wiring, performing an insulation test, 
inspecting the pilot and copilot throttle twist grip controls, and 
testing the pilot and copilot throttle twist grip controls for proper 
functioning. AD 2016-25-19 was prompted by AD No. 2013-0191-E, dated 
August 22, 2013 (EASA AD 2013-0191-E), issued by EASA, which is the 
Technical Agent for the Member States of the European Union. EASA 
advised that the switches in the engine ``IDLE'' or ``FLIGHT'' control 
system could be affected by the corrosive effects of a salt-laden 
atmosphere, which could lead to engine power loss. EASA AD 2013-0191-E 
required repetitive inspections for corrosion, application of corrosion 
protection on the switches, and testing of the insulation and switches 
of the engine idle and flight control system. The actions required in 
AD 2016-25-19 are intended to prevent unintended touchdown to the 
ground at a flight-idle power setting during a practice autorotation, 
damage to the helicopter, and injury to occupants.

Actions Since AD 2016-25-19 Was Issued

    Since we issued AD 2016-25-19, EASA issued AD No. 2017-0052, dated 
March 24, 2017, which superseded EASA AD No. 2013-0191-E, dated August 
22, 2013. EASA advised that Airbus Helicopters had added

[[Page 39008]]

clarifications to the operational procedure, introduced a modification 
to apply water-tight protection to the microswitch connectors, and 
extended the applicability to helicopters with a Turbomecca ARRIEL 2D 
engine installed.
    EASA subsequently issued AD No. 2017-0059, dated April 6, 2017, 
which superseded EASA AD No. 2017-0052 to correct the applicability by 
including Model EC130T2 helicopters.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
France and are approved for operation in the United States. Pursuant to 
our bilateral agreement with France, EASA, its technical 
representative, has notified us of the unsafe condition described in 
its AD. We are proposing this AD because we evaluated all known 
relevant information and determined that an unsafe condition is likely 
to exist or develop on other products of the same type design.

Related Service Information Under 1 CFR Part 51

    We reviewed one document that co-publishes three Emergency Alert 
Service Bulletin (EASB) identification numbers: No. 05.00.61, Revision 
3, dated June 15, 2015, for Model AS350B3 helicopters; No. 05.00.41, 
Revision 2, dated June 15, 2015, for the non-FAA type certificated 
Model AS550C3 helicopter; and No. 05A009, Revision 3, dated June 15, 
2015, for Model EC130B4 helicopters. EASB Nos. 05.00.61 and 05A009 are 
incorporated by reference in AD 2016-25-19 and will be retained for the 
requirements of this proposed AD. EASB No. 05.00.41 is not incorporated 
by reference in AD 2016-25-19 and will not be incorporated by reference 
in this proposed AD. This service information applies to helicopters 
with an Arriel 2B1 engine installed and describes procedures for a 
functional check and installation of protection for micro-contacts 
(microswitches) 53Ka, 53Kb, and 65K (IDLE/FLIGHT mode).
    We also reviewed one document that co-publishes three EASB 
identification numbers: No. 05.00.77, Revision 1, dated June 15, 2015, 
for Model AS350B3 helicopters; No. 05.00.52, Revision 1, dated June 15, 
2015, for the non-FAA type certificated Model AS550C3 helicopter; and 
No. 05A014, Revision 1, dated June 15, 2015, for Model EC130T2 
helicopters. EASB Nos. 05.00.77 and 05A014 will be incorporated by 
reference in this proposed AD. EASB No. 05.00.52 will not be 
incorporated by reference in this proposed AD. This service information 
applies to helicopters with an Arriel 2D engine installed and describes 
procedures for a check of the protection for micro-contacts 
(microswitches) 53Ka, 53Kb, and 65K (IDLE/FLIGHT mode).
    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.

Proposed AD Requirements

    This proposed AD would retain the inspection requirements of AD 
2016-25-19 but would add Model AS350B3 helicopters with an Arriel 2D 
engine installed and Model EC130T2 helicopters.

Differences Between This Proposed AD and the EASA AD

    The EASA AD requires the initial inspections within 10 flight hours 
or 7 days; this proposed AD requires compliance before the next 
autorotation training flight or before 100 hours time-in-service, 
whichever occurs earlier, as the unsafe condition only occurs when 
transitioning the throttle in flight from flight to idle and back to 
flight, such as during a practice autorotation.
    Additionally, the EASA AD requires installing Airbus Helicopters 
modification 074263; this proposed AD does not as it does not correct 
the unsafe condition.

Interim Action

    We consider this proposed AD to be an interim action. If final 
action is later identified, we might consider further rulemaking then.

Costs of Compliance

    We estimate that this proposed AD would affect 692 helicopters of 
U.S. Registry.
    We estimate that operators will incur the following costs in order 
to comply with this proposed AD. At an average labor rate of $85 per 
work hour, it would take about 4 work hours for the inspections and any 
necessary maintenance, for a total cost of $340 per helicopter and 
$235,280 for the U.S. fleet per inspection cycle.

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.

Regulatory Findings

    We 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, I certify this proposed regulation:
    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.
    We prepared an economic evaluation of the estimated costs to comply 
with this proposed AD and placed it in the AD docket.

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 removing Airworthiness Directive (AD) 
2016-25-19, Amendment 39-18745 (81 FR 95854, December 29, 2016), and 
adding the following new AD:


[[Page 39009]]


Airbus Helicopters (Previously Eurocopter France): Docket No. FAA-
2018-0669; Product Identifier 2017-SW-041-AD.

(a) Applicability

    This AD applies to the following helicopters, certificated in 
any category:
    (1) Model AS350B3 helicopters with an ARRIEL 2B1 engine with the 
two-channel Full Authority Digital Engine Control (FADEC) and with 
new twist grip modification (MOD) 073254 or with an ARRIEL 2D engine 
installed;
    (2) Model EC130B4 helicopters with an ARRIEL 2B1 engine with the 
two-channel FADEC and with new twist grip MOD 073773 installed; and
    (3) Model EC130T2 helicopters with an ARRIEL 2D engine 
installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of one of the 
two contactors, 53Ka or 53Kb, which can prevent switching from 
``IDLE'' mode to ``FLIGHT'' mode during autorotation training making 
it impossible to recover from a practice autorotation and compelling 
the pilot to continue the autorotation to the ground. This condition 
could result in unintended touchdown to the ground at a flight-idle 
power setting during a practice autorotation, damage to the 
helicopter, and injury to occupants.

(c) Affected ADs

    This AD replaces AD 2016-25-19, Amendment 39-18745 (81 FR 95854, 
December 29, 2016).

(d) Comments Due Date

    We must receive comments by October 9, 2018.

(e) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(f) Required Actions

    (1) Before the next practice autorotation or within 100 hours 
time-in-service (TIS), whichever occurs first, inspect the wiring, 
perform an insulation test, inspect the pilot and copilot throttle 
twist grip controls, and test the pilot and copilot throttle twist 
grip controls for proper functioning by following the Accomplishment 
Instructions, paragraph 3.B.1 through 3.B.6, of Airbus Helicopters 
Emergency Alert Service Bulletin (EASB) No. 05.00.61, Revision 3, 
dated June 15, 2015, for Model AS350B3 helicopters with an ARRIEL 
2B1 engine; EASB No. 05.00.77, Revision 1, dated June 15, 2015, for 
Model AS350B3 helicopters with an ARRIEL 2D engine; EASB No. 05A009, 
Revision 3, dated June 15, 2015, for Model EC130B4 helicopters; or 
EASB No. 05A014, Revision 1, dated June 15, 2015, for Model EC130T2 
helicopters, as appropriate for your model helicopter.
    (2) Repeat the inspections in paragraph (f)(1) of this AD at 
intervals not to exceed the following compliance times. For purposes 
of this AD, salt laden conditions exist when a helicopter performs a 
flight from a takeoff and landing area, heliport, or airport less 
than 0.5 statute mile from salt water or performs a flight within 
0.5 statute mile from salt water below an altitude of 1,000 ft. 
above ground or sea level.
    (i) For helicopters that have operated in salt laden conditions 
since the previous inspection required by this AD, at intervals not 
to exceed 330 hours TIS.
    (ii) For helicopters that have not operated in salt laden 
conditions since the previous inspection required by this AD, at 
intervals not to exceed 660 hours TIS.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, Rotorcraft Standards 
Branch, FAA, may approve AMOCs for this AD. Send your proposal to: 
George Schwab, Aviation Safety Engineer, Safety Management Group, 
Rotorcraft Directorate, 10101 Hillwood Parkway, Fort Worth, Texas 
76177; telephone (817) 222-5110; email <a href="/cdn-cgi/l/email-protection#d0e9fd918387fd968487fd919d9f93fd82b5a1a5b5a3a4a390b6b1b1feb7bfa6"><span class="__cf_email__" data-cfemail="99a0b4d8caceb4dfcdceb4d8d4d6dab4cbfce8ecfceaedead9fff8f8b7fef6ef">[email protected]</span></a>.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office before operating any aircraft 
complying with this AD through an AMOC.

(h) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2017-0059, dated April 6, 2017. You may view 
the EASA AD on the internet at http://www.regulations.gov in the AD 
Docket.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 7697 Engine 
Control System Wiring.

    Issued in Fort Worth, Texas, on July 11, 2018.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2018-16494 Filed 8-7-18; 8:45 am]
BILLING CODE 4910-13-P


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