Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations 11417 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(i) Related Information 

(1) The subject of this AD is addressed in 

Transport Canada AD CF–2019–03, dated 

January 31, 2019. This Transport Canada AD 

may be found in the AD docket on the 

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

searching for and locating Docket No. FAA– 

2020–0860. 

(2) For more information about this AD, 

contact Matt Fuller, AD Program Manager, 

Continued Operational Safety Branch, 

Airworthiness Products Section, General 

Aviation and Rotorcraft Unit, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone 817–222–5110; email 9-ASW-FTWAMOC-Requests@faa.gov. 

(3) Bell Model 429 Maintenance Planning 

Information BHT–429–MPI, Chapter 4, 

Airworthiness Limitations Schedule, DMC– 

429–A–04–00–00–00A–288A–A, Issue 1, 

dated January 10, 2019, which is not 

incorporated by reference, contains 

additional information about the subject of 

this AD. For service information identified in 

this AD that is not incorporated by reference, 

contact Bell Textron Canada Limited, 12,800 

Rue de l’Avenir, Mirabel, Quebec J7J 1R4; 

telephone (450) 437–2862 or (800) 363–8023; 

fax (450) 433–0272; or at https://

www.bellcustomer.com. 

(j) Material Incorporated by Reference 

None. 

Issued on January 28, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–03659 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–2020–1036; Project 

Identifier MCAI–2020–01430–R; Amendment 

39–21409; AD 2021–03–06] 

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 certain 

Airbus Helicopters Model SA–365N, 

SA–365N1, AS–365N2, AS 365 N3, EC 

155B, and EC155B1 helicopters. This 

AD was prompted by the FAA’s 

determination that to improve the 

process and performance in collecting 

metal particles in the main gear box 

(MGB) certain existing magnetic plugs 

(electrical and nonelectrical) installed in 

the MGB pump intake must be replaced 

with improved non-electrical magnetic 

plugs. This AD requires replacing the 

existing magnetic plug with an 

improved non-electrical magnetic plug, 

as specified in a European Aviation 

Safety Agency (now European Union 

Aviation Safety Agency) (EASA) AD, 

which is incorporated by reference. The 

FAA is issuing this AD to address the 

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 publication listed in this AD 

as of April 1, 2021. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, 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 

material on the EASA website at https:// 

ad.easa.europa.eu. You may view this 

material 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. It is also 

available in the AD docket on the 

internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2020–1036. 

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– 

1036; 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 final rule, 

any comments received, and other 

information. The 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: 

Mahmood Shah, Aviation Safety 

Engineer, Fort Worth ACO Branch, 

FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone 817–222– 

5538; email mahmood.g.shah@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The EASA, which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2018–0176, dated August 21, 2018 

(EASA AD 2018–0176) (also referred to 

as the Mandatory Continuing 

Airworthiness Information, or the 

MCAI), to correct an unsafe condition 

for certain Airbus Helicopters Model 

SA–365N, SA–365N1, AS–365N2, AS 

365 N3, EC 155B, and EC155B1 

helicopters. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Airbus Helicopters 

Model SA–365N, SA–365N1, AS– 

365N2, AS 365 N3, EC 155B, and 

EC155B1 helicopters. The NPRM 

published in the Federal Register on 

November 30, 2020 (85 FR 76495). The 

NPRM was prompted by the FAA’s 

determination that to improve the 

process and performance in collecting 

metal particles in the MGB certain 

existing magnetic plugs (electrical and 

non-electrical) installed in the MGB 

pump intake must be replaced with 

improved non-electrical magnetic plugs. 

The NPRM proposed to require 

replacing the existing magnetic plug 

with an improved non-electrical 

magnetic plug, as specified in an EASA 

AD. 

The FAA is issuing this AD to address 

metal particles causing seizure of the 

MGB, loss of power to the main rotor, 

and subsequent loss of control of the 

helicopter. See the MCAI for additional 

background information. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The FAA received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Conclusion 

The FAA reviewed the relevant data 

and determined that air safety and the 

public interest require adopting this 

final rule as proposed, except for minor 

editorial changes. The FAA has 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2018–0176 describes 

procedures for replacing the existing 

magnetic plug (electrical and nonelectrical) installed in the MGB pump 

intake with an improved non-electrical 

magnetic plug. This material is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

11418 Federal Register / Vol. 86, No. 36 / Thursday, February 25, 2021 / Rules and Regulations 

or by the means identified in the 

ADDRESSES section. 

Interim Action 

The FAA considers this AD interim 

action. If final action is later identified, 

the FAA might consider further 

rulemaking then. 

Costs of Compliance 

The FAA estimates that this AD 

affects 52 helicopters of U.S. registry. 

The FAA estimates the following costs 

to comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Up to 7.5 work-hours × $85 per hour = $637.50 ............................................................ $55 Up to $692.50 Up to $36,010 

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 products 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: 

2021–03–06 Airbus Helicopters: 

Amendment 39–21409; Docket No. 

FAA–2020–1036; Project Identifier 

MCAI–2020–01430–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective April 1, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model SA–365N, SA–365N1, AS–365N2, AS 

365 N3, EC 155B, and EC155B1 helicopters, 

certificated in any category, equipped with 

magnetic plugs, part number (P/N) 1B7807 or 

P/N 704A34543017 (electrical), or P/N 

365A32–1711–00 (non-electrical), as 

applicable, installed in the main gearbox 

(MGB) pump intake. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 6320, Main Rotor Gearbox. 

(e) Reason 

This AD was prompted by the FAA’s 

determination that to improve the process 

and performance in collecting metal particles 

in MGB certain existing magnetic plugs 

(electrical and non-electrical) installed in the 

MGB pump intake must be replaced with 

improved non-electrical magnetic plugs. The 

FAA is issuing this AD to address metal 

particles causing seizure of the MGB, loss of 

power to the main rotor, and subsequent loss 

of control of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, European Aviation Safety 

Agency (now European Union Aviation 

Safety Agency) (EASA) AD 2018–0176, dated 

August 21, 2018 (EASA AD 2018–0176). 

(h) Exceptions to EASA AD 2018–0176 

(1) Where EASA AD 2018–0176 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) The ‘‘Remarks’’ section of EASA AD 

2018–0176 does not apply to this AD. 

(3) Although the service information 

referenced in EASA AD 2018–0176 specifies 

to discard certain parts, this AD does not 

include that requirement. 

(4) Where EASA AD 2018–0176 refers to 

flight hours (FH), this AD requires using 

hours time-in-service. 

(i) Special Flight Permit 

Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199 

to operate the helicopter to a location where 

the helicopter can be modified (if the 

operator elects to do so), provided the 

helicopter is operated using day visual flight 

rules and no passengers are onboard. 

(j) 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. Information 

may be emailed to: 9-ASW-FTW-AMOCRequests@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. 

(k) Related Information 

For more information about this AD, 

contact Mahmood Shah, Aviation Safety 

Engineer, Fort Worth ACO Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

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.