This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents.

Rules and Regulations Federal Register

31087 

Vol. 86, No. 111 

Friday, June 11, 2021 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0199; Project 

Identifier MCAI–2021–00016–R;Amendment 

39–21579; AD 2021–11–17] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH (AHD) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Deutschland GmbH (AHD) 

Model EC135P1, EC135P2, EC135P2+, 

EC135P3, EC135T1, EC135T2, 

EC135T2+, and EC135T3 helicopters. 

This AD was prompted by a report of 

increased control force in the collective 

axis. This AD requires a one-time visual 

inspection of the main rotor actuator 

(MRA), 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 July 16, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 16, 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–2021–0199. 

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–2021– 

0199; 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: 

Katherine Venegas, Aviation Safety 

Engineer, Los Angeles ACO Branch, 

FAA, 3960 Paramount Blvd., Lakewood, 

California 90712; telephone (562) 627– 

5353; email katherine.venegas@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2018–0284, 

dated December 20, 2018 (EASA AD 

2018–0284), to correct an unsafe 

condition for Airbus Helicopters 

Deutschland GmbH (AHD) Model EC135 

P1, EC135 P2, EC135 P2+, EC135 P3, 

EC135 T1, EC135 T2, EC135 T2+, EC135 

T3, EC635 P2+, EC635 P3, EC635 T1, 

EC635 T2+, and EC635 T3 helicopters. 

Model EC635 P2+, EC635 P3, EC635 T1, 

and EC635 T3 helicopters are not 

certificated by the FAA and are not 

included on the U.S. type certificate 

data sheet; this AD therefore does not 

include those helicopters in the 

applicability. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to Model EC135P1, EC135P2, 

EC135P2+, EC135P3, EC135T1, 

EC135T2, EC135T2+, and EC135T3 

helicopters. The NPRM published in the 

Federal Register on March 30, 2021 (86 

FR 16550). The NPRM was prompted by 

a report of increased control force in the 

collective axis on an AHD Model EC135 

helicopter. Subsequent inspections 

determined that a nut on a piston of the 

MRA had cracked and separated from 

the piston rod. The NPRM proposed to 

require a one-time visual inspection of 

the MRA, as specified in an EASA AD. 

The FAA is issuing this AD to prevent 

failure of the MRA and subsequent loss 

of control of the helicopter. See EASA 

AD 2018–0284 for additional 

background information. 

Discussion of Final Airworthiness 

Directive 

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. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2018–0284 describes 

procedures for a one-time visual 

inspection of the MRA and depending 

on the results, replacing the affected 

parts. 

This material 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. 

Differences Between This AD and the 

EASA AD 

The EASA AD requires contacting 

Airbus Helicopters or replacing an 

affected part, whereas this AD requires 

performing the corrective action in 

accordance with FAA-approved 

procedures or removing the affected 

parts from service instead. Where the 

EASA AD specifies a compliance time 

for the inspection in terms of calendar 

time or flight hours, this AD requires a 

compliance time in terms of hours timein-service instead. Where the EASA AD 

specifies a compliance time of 15 days 

for reporting the inspection results, this 

AD requires that the findings be 

reported within 30 days. 

Interim Action 

The FAA considers this AD interim 

action. If final action is later identified, 


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31088 Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations 

the FAA might consider further 

rulemaking then. 

Costs of Compliance 

The FAA estimates that this AD 

affects 331 helicopters of U.S. Registry. 

Labor rates are estimated at $85 per 

work-hour. Based on these numbers, the 

FAA estimates that operators may incur 

the following costs in order to comply 

with this AD. 

Inspecting the nuts on the MRA 

pistons takes about 1 work-hour for an 

estimated cost of $85 per helicopter and 

$28,135 for the U.S. fleet. Replacing the 

MRA takes about 7 work-hours and 

parts cost $325,081 for an estimated cost 

of $325,676 per helicopter. Repairing 

the MRA takes up to about 8 work-hours 

and parts cost about $110 for an 

estimated cost of up to $790 per MRA. 

Reporting information takes about 1 

hour for an estimated cost of $85 per 

helicopter and $28,135 for the U.S. fleet. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to Information 

Collection Clearance Officer, Federal 

Aviation Administration, 10101 

Hillwood Pkwy., Fort Worth, TX 76177– 

1524. 

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. 

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: 

2021–11–17 Airbus Helicopters 

Deutschland GmbH (AHD): Amendment 

39–21579; Docket No. FAA–2021–0199; 

Project Identifier MCAI–2021–00016–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 16, 2021. 

(b) Affected Airworthiness Directives (ADs) 

None. 

(c) Applicability 

This AD applies to all Airbus Helicopters 

Deutschland GmbH (AHD) Model EC135P1, 

EC135P2, EC135P2+, EC135P3, EC135T1, 

EC135T2, EC135T2+, and EC135T3 

helicopters, certificated in any category. 

Note 1 to paragraph (c): Helicopters with 

an EC135P3H designation are Model 

EC135P3 helicopters. Helicopters with an 

EC135T3H designation are Model EC135T3 

helicopters. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code: 6710, Main Rotor Control. 

(e) Reason 

This AD was prompted by a report of 

increased control force in the collective axis. 

The FAA is issuing this AD to prevent failure 

of the main rotor actuator 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 2018–0284, dated 

December 20, 2018 (EASA AD 2018–0284). 

(h) Exceptions to EASA AD 2018–0284 

(1) Where EASA AD 2018–0284 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where paragraph (3) of EASA AD 2018– 

0284 specifies contacting Airbus Helicopters, 

this AD requires performing the corrective 

action in accordance with FAA-approved 

procedures. 

(3) Where paragraph (4) of EASA AD 2018– 

0284 specifies an alternative method to 

comply with the requirements of paragraph 

(3) of EASA AD 2018–0284 by replacing an 

affected part, this AD requires removing the 

affected part from service as an alternative 

method. 

(4) Where paragraph (1) of EASA AD 2018– 

0284 specifies a compliance time of ‘‘3 

months or 50 flight hours, whichever occurs 

first,’’ this AD requires a compliance time of 

within 50 hours time-in-service (TIS) from 

the effective date of this AD. 

(5) Where paragraph (2) of EASA AD 2018– 

0284 specifies a compliance time of ‘‘15 

days,’’ this AD requires using a compliance 

time of ‘‘30 days.’’ 

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

2018–0284 does not apply to this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, International Validation 

Branch, 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 International Validation 

Branch, send it to the attention of the person 

identified in paragraph (j) of this AD. 

Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 


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Federal Register / Vol. 86, No. 111 / Friday, June 11, 2021 / Rules and Regulations 31089 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(j) Related Information 

For more information about this AD, 

contact Katherine Venegas, Aviation Safety 

Engineer, Los Angeles ACO Branch, FAA, 

3960 Paramount Blvd., Lakewood, California 

90712; telephone (562) 627–5353; email 

katherine.venegas@faa.gov. 

(k) 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 2018–0284, dated December 20, 

2018. 

(ii) [Reserved] 

(3) For EASA AD 2018–0284, 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–2021–0199. 

(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 May 20, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–12227 Filed 6–10–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0185; Project 

Identifier MCAI–2020–00265–R; Amendment 

39–21581; AD 2021–11–19] 

RIN 2120–AA64 

Airworthiness Directives; Bell Textron 

Canada Limited (Type Certificate 

Previously Held by Bell Helicopter 

Textron Canada Limited) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Bell 

Textron Canada Limited (type certificate 

previously held by Bell Helicopter 

Textron Canada Limited) (Bell) Model 

505 helicopters. This AD was prompted 

by the discovery of a gap between the 

transmission restraint assembly aft 

attachment hardware lower washer and 

mating airframe truss assembly (truss 

assembly) clevis lower lug. This AD 

requires inspecting the transmission 

restraint aft attachment hardware 

installation for a gap and corrective 

action depending on the inspection 

results. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective July 16, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of July 16, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact Bell 

Textron Canada Limited, 12,800 Rue de 

l’Avenir, Mirabel, Quebec J7J1R4; 

telephone 450–437–2862 or 800–363– 

8023; fax 450–433–0272; or at https://

www.bellcustomer.com. 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. Service information that is 

incorporated by reference is also 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0185. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0185; 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, the Transport Canada AD, 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: Matt 

Fuller, AD Program Manager, General 

Aviation & Rotorcraft Unit, 

Airworthiness Products Section, 

Operational Safety Branch, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone 817–222–5110; email 

matthew.fuller@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to Bell Model 505 helicopters 

with a truss assembly part number 

(P/N) SLS–030–056–015 with a serial 

number (S/N) listed in Attachment A of 

Bell Alert Service Bulletin (ASB) 505– 

19–12, Revision A, dated July 11, 2019 

(505–19–12 Rev A). The NPRM 

published in the Federal Register on 

March 22, 2021 (86 FR 15146). In the 

NPRM, the FAA proposed to require the 

following within 100 hours time-inservice (TIS): 

• Accessing and cleaning the lower 

attachment hardware securing the 

restraint to the truss assembly, 

loosening the torque on each lower nut 

to measure the tare, and adding a torque 

value of 20 inch-lbs to the measured tare 

of each nut and torqueing each nut to 

this new total value. 

• Inspecting for a gap around the 

circumference between the nut and the 

washer and between the washer and the 

truss assembly clevis lower lug 

mounting surface of the right-hand (RH) 

and left-hand (LH) sides, and if there is 

a gap, measuring the gap. 

• If there is a gap that is less than 

0.003 inch (0.076 mm), installing the 

hardware using the original torque value 

of 40 to 58 foot-pounds (55 to 78 Nm) 

plus tare and completing the installation 

of the attachment point. 

• If there is a gap that is 0.003 inch 

(0.076 mm) to 0.020 inch (0.508 mm) 

inclusive, installing the hardware with 

a decreased torque value limit of 20 to 

60 inch-pounds (2.3 to 6.8 Nm) plus tare 

and completing the installation of the 

attachment point. The NPRM also 

proposed to require updating records for 

your helicopter to indicate the new 

torque limits on one or both sides. 

Thereafter, within 100 hours TIS, and 

thereafter at intervals not to exceed 100 

hours TIS, the NPRM proposed to 


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