Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations 11419 

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. 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 this AD specifies otherwise. 

(i) European Aviation Safety Agency 

(EASA) AD 2018–0176 dated August 21, 

2018. 

(ii) [Reserved] 

(3) For EASA AD 2018–0176, 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 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call 817–222–5110. This 

material may be found in the AD docket on 

the internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2020–1036. 

(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. 

Issued on January 27, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–03664 Filed 2–24–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0907; Product 

Identifier 2017–SW–072–AD; Amendment 

39–21429; AD 2021–04–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: 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 

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 972–641–0000 or 800–232– 

0323; fax 972–641–3775; 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 6N–321, Fort Worth, TX 

76177. It is also available on the internet 

at https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0907. 

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. FAA–2020– 

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 

W12–140, 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 303–342–1093; email 

ronnea.l.derby@faa.gov. 

SUPPLEMENTARY INFORMATION: 

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 

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. 2017–0035, dated February 20, 

2017 (EASA AD 2017–0035), 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 2017–0035, which prompted 

this AD action, to include all of the 

previous AD requirements and expand 

the terminating action modification to 

other helicopter configurations. 

11420 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. 

FAA’s Determination 

This helicopter has been approved by 

EASA and is approved for operation in 

the United States. Pursuant to the FAA’s 

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. 

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. 

AS350–67.00.43, 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 

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. 

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. 

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 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 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. 

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 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2021–04–08 Airbus Helicopters: 

Amendment 39–21429; Docket No. 

FAA–2020–0907; Product Identifier 

2017–SW–072–AD. 

(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 

Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations 11421 

within 330 hours time-in-service, whichever 

occurs first, modify the electrical operation of 

the throttle twist grip to give priority to the 

HydroMechanical Unit flight position when 

the microswitch does not operate correctly at 

forced idle (corresponds to Airbus 

Helicopters Modification (MOD) 073357) as 

follows: 

(1) For helicopters without MOD 073087 

and without MOD 073135 installed: 

(i) Install box ‘‘69K’’ on the Full Authority 

Digital Engine Control plate, relay ‘‘81K’’ on 

frame X1310, install fuses on the console end 

comprising circuit-breaker panels ‘‘31 

ALPHA’’ and ‘‘32 ALPHA,’’ and modify the 

electrical wiring by following the 

Accomplishment Instructions, paragraph 

3.B.2.a. of Airbus Helicopters Alert Service 

Bulletin No. AS350–67.00.43, Revision 3, 

dated June 16, 2016 (ASB AS350–67.00.43), 

except you are not required to discard parts. 

(ii) Inspect the routing of microswitch 

electrical harness ‘‘53K’’ for correct 

installation by following paragraph 3.B.2.e. of 

ASB AS350–67.00.43. If the wiring routing is 

incorrect, before further flight, correct the 

wiring routing by following paragraph 

3.B.2.f. of ASB AS350–67.00.43. 

(2) For helicopters with MOD 073087 

(series) and without MOD 073135 installed: 

(i) Install relays ‘‘54K’’ and ‘‘81K’’ on frame 

X1310 and modify the electrical wiring by 

following paragraph 3.B.2.b. of ASB AS350– 

67.00.43. 

(ii) Inspect the routing of microswitch 

electrical harness ‘‘53K’’ for correct 

installation by following paragraph 3.B.2.e. of 

ASB AS350–67.00.43. If the wiring routing is 

incorrect, before further flight, correct the 

wiring routing by following paragraph 

3.B.2.f. of ASB AS350–67.00.43. 

(3) For helicopters with MOD 073087 

(retrofit) and without MOD 073135 installed: 

(i) Install relay ‘‘81K’’ on frame X1310 and 

modify the electrical wiring by following 

paragraph 3.B.2.c. of ASB AS350–67.00.43. 

(ii) Inspect the routing of microswitch 

electrical harness ‘‘53K’’ for correct 

installation by following paragraph 3.B.2.e. of 

ASB AS350–67.00.43. If the wiring routing is 

incorrect, before further flight, correct the 

wiring routing by following paragraph 

3.B.2.f. of ASB AS350–67.00.43. 

(4) For helicopters with MOD 073087 and 

with MOD 073135 installed: 

(i) Install relay ‘‘81K’’ on frame X1310 and 

modify the electrical wiring by following 

paragraph 3.B.2.d. of ASB AS350–67.00.43. 

(ii) Inspect the routing of microswitch 

electrical harness ‘‘53K’’ for correct 

installation by following paragraph 3.B.2.e. of 

ASB AS350–67.00.43. If the wiring routing is 

incorrect, before further flight, correct the 

wiring routing by following paragraph 

3.B.2.f. of ASB AS350–67.00.43. 

(5) For helicopters with MOD 073084 and 

with MOD 073222 installed: 

(i) Install relay ‘‘81K’’ on frame X1310 and 

modify the electrical wiring by following 

paragraph 3.B.2.g. of ASB AS350–67.00.43, 

except you are not required to scrap parts. 

(ii) Inspect the routing of microswitch 

electrical harness ‘‘53K’’ for correct 

installation by following paragraph 3.B.2.e. of 

ASB AS350–67.00.43. If the wiring routing is 

incorrect, before further flight, correct the 

wiring routing by following paragraph 

3.B.2.f. of ASB AS350–67.00.43. 

(6) For helicopters with optional Autopilot 

‘‘81K’’ and without MOD 073222 installed: 

(i) Position relay ‘‘81K’’ on frame X1310 by 

following paragraph 3.B.2.h. of ASB AS350– 

67.00.43. 

(ii) Inspect the routing of microswitch 

electrical harness ‘‘53K’’ for correct 

installation by following ASB AS350– 

67.00.43, paragraph 3.B.2.e. If the wiring 

routing is incorrect, before further flight, 

correct the wiring routing by following 

paragraph 3.B.2.f. of ASB AS350–67.00.43. 

(f) Special Flight Permits 

Special flight permits are prohibited. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Strategic Policy 

Rotorcraft Section, 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 Strategic Policy 

Rotorcraft Section, send it to: Manager, 

Strategic Policy Rotorcraft Section, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone 817–222–5110; email 9- 

ASW-FTW-AMOC-Requests@faa.gov. 

(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. 

(h) Additional Information 

(1) Eurocopter Alert Service Bulletin No. 

05.00.49, Revision 3, dated March 8, 2012, 

which is not incorporated by reference, 

contains additional information about the 

subject of this AD. For 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 

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 6N– 

321, Fort Worth, TX 76177. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (now 

European Union Aviation Safety Agency) 

(EASA) AD No. 2017–0035, dated February 

20, 2017. You may view the EASA AD on the 

internet at https://www.regulations.gov in the 

AD Docket. 

(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 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. 

(i) Airbus Helicopters Alert Service 

Bulletin No. AS350–67.00.43, Revision 3, 

dated June 16, 2016. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, Airbus Helicopters, 2701 N Forum 

Drive, Grand Prairie, TX 75052; telephone 

972–641–0000 or 800–232–0323; fax 972– 

641–3775; or at https://www.airbus.com/ 

helicopters/services/technical-support.html. 

(4) You may view this service information 

at the 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. 

(5) 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, 

email fedreg.legal@nara.gov, or go to: https:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on February 4, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–03657 Filed 2–24–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 73 

[Docket No. FAA–2013–1063; Airspace 

Docket No. 13–ASO–25] 

RIN 2120–AA66 

Amendment of Restricted Areas R– 

3008A, R–3008B, R–3008C, and R– 

3008D; Grand Bay Weapons Range, 

GA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action amends the time 

of designation for restricted areas R– 

3008A, R–3008B, R–3008C, and R– 

3008D; Grand Bay Weapons Range, GA, 

by expanding the timeframe during 

which the areas may be activated 

without prior issuance of a Notice to 

Airmen (NOTAM). The expansion of the 

published designated times for these 

restricted areas reflects their routine 

actual use. This change better informs 

the flying public of actual routine use 

periods of the restricted areas and 

reduces NOTAM System workload. 

DATES: Effective date 0901 UTC, April 

22, 2021. 

FOR FURTHER INFORMATION CONTACT: Paul 

Gallant, Rules and Regulations Group, 

Office of Policy, Federal Aviation 

Administration, 800 Independence