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Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations 76177; telephone 817 222 5538; email mahmood.g.shah@faa.gov.
l 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. 552a and 1 CFR
part 51.
2 You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise.
i European Aviation Safety Agency EASA AD 20180176 dated August 21, 2018.
ii Reserved 3 For EASA AD 20180176, contact the EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https
ad.easa.europa.eu.
4 You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call 8172225110. This material may be found in the AD docket on the internet at https www.regulations.gov by searching for and locating Docket No.
FAA20201036.
5 You may view this material that is incorporated by reference 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.

correcting the electrical harness routing if it is incorrect. This AD was prompted by reports of the engine remaining in idle when the twist grip was turned from the forced idle position to the flight position. The actions of this AD
are intended to address an unsafe condition on these products.
DATES: This AD is effective April 1, 2021.
The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD
as of April 1, 2021.
ADDRESSES: For service information identified in this final rule, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052;
telephone 9726410000 or 800232
0323; fax 9726413775; or at https
www.airbus.com/helicopters/services/
technical-support.html. You may view the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N321, Fort Worth, TX
76177. It is also available on the internet at https www.regulations.gov by searching for and locating Docket No.
FAA20200907.

AGENCY:

Examining the AD Docket You may examine the AD docket on the internet at https
www.regulations.gov by searching for and locating Docket No. FAA2020
0907; 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 now European Union Aviation Safety Agency EASA AD, any service information that is incorporated by reference, any comments received, and other information. The street address for Docket Operations is U.S. Department of Transportation, Docket Operations, M
30, West Building Ground Floor, Room W12140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Ronnea Derby, Aviation Safety Engineer, Denver ACO Branch, FAA, 26805 E 68th Ave., Denver, CO 80249;
telephone 3033421093; email ronnea.l.derby@faa.gov.
SUPPLEMENTARY INFORMATION:

The FAA is adopting a new airworthiness directive AD for Airbus Helicopters Model AS350B3
helicopters. This AD requires modifying the electrical system of the throttle twist grip, inspecting the routing of a microswitch electrical harness, and
Discussion The FAA issued a notice of proposed rulemaking NPRM to amend 14 CFR
part 39 by adding an AD that would apply to Airbus Helicopters Model AS350B3 helicopters with a Turbomeca ARRIEL 2B engine installed. The NPRM
published in the Federal Register on October 15, 2020 85 FR 65285. The
Issued on January 27, 2021.
Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service.
FR Doc. 202103664 Filed 22421; 8:45 am BILLING CODE 491013P

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA20200907; Product Identifier 2017SW072AD; Amendment 3921429; AD 20210408
RIN 2120AA64

Airworthiness Directives; Airbus Helicopters Federal Aviation Administration FAA, DOT.
ACTION: Final rule.
SUMMARY:

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NPRM proposed to require, based on helicopter configuration, modifying the electrical system of the throttle twist grip. The proposed AD also proposed to require inspecting the routing of a microswitch electrical harness, and depending on the routing of that electrical harness, correcting the routing. The proposed requirements were intended to prevent failure of the electrical operation of the throttle twist grip, which can prevent switching from IDLE mode to FLIGHT mode.
During autorotation training or during governor failure training when the throttle grip is turned in the low flow direction, this condition prohibits recovery from a practice autorotation and compels 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, damage to the helicopter, and injury to occupants.
The NPRM was prompted by EASA
AD No. 20170035, dated February 20, 2017 EASA AD 20170035, to correct an unsafe condition for Airbus Helicopters formerly Eurocopter Model AS 350 B3 helicopters with ARRIEL 2B engines installed. EASA
advises of an initial report of the microswitch pin jammed in the pushedin position resulting in the engine remaining in idle when the twist grip had been turned back to the flight position during an autorotation training exercise. This condition could also occur during governor failure training when the twist grip is turned in the low flow rate direction. EASA also advises of two later reports of this condition, with one of those reports related to an incorrectly routed electrical harness.
EASA advises that this condition, if not detected and corrected, could lead to reduced control of the helicopter.
EASA initially issued AD No. 2006
0094, dated April 21, 2006, which required repetitive testing of the microswitch and established a life limit for the microswitch. Subsequent EASA
AD action required reducing that life limit, inspecting the travel of the collective lever, performing an additional check of the collective lever for free travel, and installing a terminating action modification that was available for certain helicopter configurations. That modification gave priority to the HydroMechanical Unit HMU flight position when the microswitch failed to operate correctly at forced idle. EASA most recently issued AD 20170035, which prompted this AD action, to include all of the previous AD requirements and expand the terminating action modification to other helicopter configurations.

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