Document ID: FAA-2018-0669-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Helicopters (Previously Eurocopter France) Helicopters
Posted Date: 2018-12-26T05:00Z

[Federal Register Volume 83, Number 246 (Wednesday, December 26, 2018)]
[Rules and Regulations]
[Pages 66093-66095]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-27715]

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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; Amendment 
39-19532; AD 2018-26-02]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters (Previously 
Eurocopter France) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2016-25-19 for 
Airbus Helicopters (previously Eurocopter France) Model AS350B3 and 
EC130B4 helicopters. AD 2016-25-19 required inspecting the pilot's and 
co-pilot's throttle twist for proper operation. This new AD retains the 
requirements of AD 2016-25-19 and adds certain model helicopters to the 
applicability. The actions of this AD are intended to address an unsafe 
condition on these products.

DATES: This AD is effective January 30, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 30, 
2019.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
February 2, 2017 (81 FR 95854, December 29, 2016).

ADDRESSES: For service information identified in this final 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 the review service information at the FAA, 
Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., 
Room 6N-321, Fort Worth, TX 76177. It is also available on the internet 
at http://www.regulations.gov by searching for and locating Docket No. 
FAA-2018-0669.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov in 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 AD, the European Aviation 
Safety Agency (EASA) AD, any incorporated-by-reference service 
information, the economic evaluation, any comments received, and other 
information. The address for Docket Operations (phone: 800-647-5527) is 
Docket Operations, 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: George Schwab, Aviation Safety 
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; 
email george.schwab@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to remove AD 2016-25-19, Amendment 39-18745 (81 FR 95854, 
December 29, 2016) (AD 2016-25-19) and add a new AD. AD 2016-25-19 
applied to Airbus Helicopters Model AS350B3 and EC130B4 helicopters 
with an 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 required 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. The actions 
required in AD 2016-25-19 were 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.
    The NPRM published in the Federal Register on August 8, 2018 (83 FR 
39007). The NPRM proposed to retain the requirements of AD 2016-25-19 
and expand the applicability by adding Model AS350B3 helicopters with 
an ARRIEL 2D engine installed and Model EC130T2 helicopters with an 
ARRIEL 2D engine installed.
    The NPRM was prompted by AD No. 2017-0059, dated April 6, 2017 
(EASA AD 2017-0059), issued by EASA, which is the Technical Agent for 
the Member States of the European Union, for Airbus Helicopters Model 
AS 350 B3, EC 130 B4, and EC 130 T2 helicopters. EASA advises that 
Airbus Helicopters added 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 Turbomeca ARRIEL 2D engine installed. Accordingly, EASA AD 2017-
0059 retains the required actions and corrects the applicability of the 
previous EASA AD.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM.

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 have reviewed the relevant information and determined that 
an unsafe condition exists and is likely to exist or develop on other 
helicopters of these same type designs and that air

[[Page 66094]]

safety and the public interest require adopting the AD requirements as 
proposed.

Interim Action

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

Differences Between This AD and the EASA AD

    The EASA AD requires the initial inspections within 10 flight hours 
or 7 days; this 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 
MOD 074263; this AD does not as it does not correct the unsafe 
condition.

Related Service Information Under 1 CFR Part 51

    We reviewed one document that co-publishes three Airbus Helicopters 
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 are retained for the requirements of this AD. EASB No. 05.00.41 is 
not incorporated by reference in AD 2016-25-19 and is not incorporated 
by reference in this 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 Airbus 
Helicopters 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 are 
incorporated by reference in this AD. EASB No. 05.00.52 is not 
incorporated by reference in this 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.

Costs of Compliance

    We estimate that this AD affects 692 helicopters of U.S. Registry. 
We estimate that operators may incur the following costs in order to 
comply with this AD.
    At an average labor rate of $85 per work-hour, it takes 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 have determined that 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under 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 removing Airworthiness Directive (AD) 
2016-25-19, Amendment 39-18745 (81 FR 95854, December 29, 2016), and 
adding the following new AD:

2018-26-02 Airbus Helicopters (Previously Eurocopter France): 
Amendment 39-19532; 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) Effective Date

    This AD becomes effective January 30, 2019.

[[Page 66095]]

(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 Section, 
Rotorcraft Standards Branch, FAA, 10101 Hillwood Parkway, Fort 
Worth, Texas 76177; telephone (817) 222-5110; email 9-ASW-FTW-AMOC-Requests@faa.gov.
    (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 Docket 
No. FAA-2018-0669.

(i) Subject

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

(j) 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.
    (3) The following service information was approved for IBR on 
January 30, 2019.
    (i) Airbus Helicopters Emergency Alert Service Bulletin (EASB) 
No. 05.00.77, Revision 1, dated June 15, 2015.
    (ii) Airbus Helicopters EASB No. 05A014, Revision 1, dated June 
15, 2015.
    Note 1 to paragraph (j)(3): Airbus Helicopters EASB Nos. 
05.00.77 and 05A014, both Revision 1 and dated June 15, 2015, are 
co-published as one document along with Airbus Helicopters EASB No. 
05.00.52, Revision 1, dated June 15, 2015, which is not incorporated 
by reference in this AD.
    (4) The following service information was approved for IBR on 
February 2, 2017 (81 FR 95854, December 29, 2016).
    (i) Airbus Helicopters EASB No. 05.00.61, Revision 3, dated June 
15, 2015.
    (ii) Airbus Helicopters EASB No. 05A009, Revision 3, dated June 
15, 2015.
    Note 2 to paragraph (j)(4): Airbus Helicopters EASB Nos. 
05.00.61 and 05A009, both Revision 3 and dated June 15, 2015, are 
co-published as one document along with Airbus Helicopters EASB No. 
05.00.41, Revision 2, dated June 15, 2015, which is not incorporated 
by reference in this AD.
    (5) For Airbus Helicopters service information identified in 
this AD, 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.
    (6) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-
321, Fort Worth, TX 76177. For information on the availability of 
this material at the FAA, call (817) 222-5110.
    (7) 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 Fort Worth, Texas, on December 13, 2018.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2018-27715 Filed 12-21-18; 8:45 am]
 BILLING CODE 4910-13-P