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Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations
Comments The FAA gave the public the opportunity to participate in developing this final rule, but the FAA did not receive any comments on the NPRM or on the determination of the cost to the public.

routing of microswitch electrical harness number 53K.
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.

FAAs Determination This helicopter has been approved by EASA and is approved for operation in the United States. Pursuant to the FAAs bilateral agreement with the European Union, EASA has notified the FAA of the unsafe condition described in its AD. The FAA is issuing this AD after evaluating all of the information provided by EASA and determining the unsafe condition exists and is likely to exist or develop on other helicopters of the same type design and that air safety and the public interest require adopting the AD requirements as proposed, except for a minor editorial change. The FAA has determined that this minor editorial change is consistent with the intent that was proposed in the NPRM
for addressing the unsafe condition and does not add any additional burden upon the public than was already proposed in the NPRM.

Other Related Service Information The FAA also reviewed Eurocopter ASB No. 05.00.49, Revision 3, dated March 8, 2012. This service information specifies procedures, for helicopters without MOD 073357 installed, for repetitive testing of the microswitch, a life limit for the microswitch, inspecting the travel of the collective lever, and verifying correct wiring harness installation.

Differences Between This AD and the EASA AD
The EASA AD specifies a repetitive test of the microswitch, a life limit for the microswitch, and inspecting the travel of the collective lever, until the terminating action of modifying the electrical system of the throttle twist grip and inspecting the routing of a microswitch electrical harness are completed. This AD only requires modifying the electrical system of the throttle twist grip and inspecting the routing of a microswitch electrical harness. The EASA AD specifies performing that terminating action in a compliance time of calendar months.
This AD requires performing the required actions before the next practice autorotation, before the next simulated governor failure, or within 330 hours time-in service, whichever occurs first.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Airbus Helicopters Alert Service Bulletin ASB No.
AS35067.00.43, Revision 3, dated June 16, 2016, which specifies procedures, based on different configurations, to modify the electrical operation to give priority to the HMU flight position when the microswitch does not operate correctly at forced idle corresponds to Airbus Helicopters Modification MOD
073357. This service information also specifies instructions to inspect the
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Costs of Compliance The FAA estimates that this AD
affects 517 helicopters of U.S. Registry.
The FAA estimates that operators may incur the following costs in order to comply with this AD. Labor costs are estimated at $85 per work-hour.
Modifying the electrical system and inspecting the electrical harness routing takes about 30 work-hours and parts will cost about $9,692 for an estimated cost of $12,242 per helicopter and $6,329,114 for the U.S. fleet.
Authority for This Rulemaking Title 49 of the United States Code specifies the FAAs 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 Agencys 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 helicopters 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.

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For the reasons discussed above, I
certify that 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.
Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.
39.13

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

20210408 Airbus Helicopters:
Amendment 3921429; Docket No.
FAA20200907; Product Identifier 2017SW072AD.
a Applicability This airworthiness directive AD applies to Airbus Helicopters Model AS350B3
helicopters, certificated in any category, with a Turbomeca ARRIEL 2B engine installed.
b Unsafe Condition This AD defines the unsafe condition as 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.
c Effective Date This AD becomes effective April 1, 2021.
d 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.
e Required Actions Before the next practice autorotation, before the next simulated governor failure, or
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