Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Rules and Regulations 13159 

208B5344, 208B5346 through 208B5350, 

208B5353, 208B5354, 208B5356 through 

208B5359, 208B5362 through 208B5366, 

208B5401, 208B5403, 208B5404, and 

208B5408; certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code: 5520, Elevator Structure. 

(e) Unsafe Condition 

This AD was prompted by reports of loose 

elevator torque tube attach fasteners. The 

FAA is issuing this AD to detect and correct 

loosening and eventual failure of the elevator 

torque tube attach fasteners. The unsafe 

condition, if not addressed, could result in 

loss of elevator control, resulting in loss of 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Fastener Replacement 

(1) At the following compliance times, 

inspect each inboard and outboard elevator 

torque tube attach fastener for looseness and 

fretting by following sections 2.C. and 2.D. of 

Task 27–30–00–290, Left and Right Elevator 

Torque Tube Attach Points (Borescope) 

Special Detailed Inspection, dated October 1, 

2018, of the Cessna Model 208 Maintenance 

Manual. You must also inspect for 

incorrectly installed fasteners. 

(i) For airplanes that have accumulated less 

than 800 hours time-in-service (TIS) as of the 

effective date of this AD, complete the initial 

inspection before the airplane accumulates 

800 hours TIS or within 200 hours TIS after 

the effective date of the AD, whichever 

occurs later. Thereafter, repeat the visual 

inspection at intervals not to exceed 200 

hours TIS until the airplane has accumulated 

4,000 hours TIS or until all 48 elevator torque 

tube attach fasteners are replaced, whichever 

occurs first. 

(ii) For airplanes that have accumulated 

800 or more hours TIS but less than 4,000 

hours TIS as of the effective date of this AD, 

complete the initial inspection within 200 

hours TIS after the effective date of the AD. 

Thereafter, repeat the visual inspection at 

intervals not to exceed 200 hours TIS until 

the airplane has accumulated 4,000 hours 

TIS or until all 48 elevator torque tube attach 

fasteners are replaced, whichever occurs first. 

(iii) For airplanes that have accumulated 

4,000 or more hours TIS as of the effective 

date of this AD, complete a one-time visual 

inspection within 200 hours TIS after the 

effective date of the AD. No repetitive 

inspections are required after completion of 

the one-time visual inspection. 

(2) If there are any loose, fretting, or 

incorrectly installed fasteners, remove the 

elevator and replace all 48 elevator torque 

tube attach fasteners (24 per side, with 12 

each on the inboard and outboard elevator 

torque tube attach point) before further flight. 

Maintain proper alignment by marking each 

part prior to removal and by replacing one 

fastener at a time. Replacing all 48 fasteners 

is terminating action for the repetitive 

inspections required by paragraphs (g)(1)(i) 

and (ii) of this AD. 

(3) If all 48 fasteners were replaced before 

the effective date of this AD by following the 

instructions in paragraph (g)(2) of this AD, 

then the initial and recurring inspections 

detailed in paragraph (g)(1) of this AD are not 

required provided you report the information 

required by paragraph (h) of this AD. 

(h) Reporting Requirement 

Within 30 days after doing the initial 

inspection (regardless if loose, fretting, or 

incorrectly installed fasteners were found) or 

within 30 days after the effective date of this 

AD, whichever occurs later, and then within 

30 days after each inspection where loose, 

fretting, or incorrectly installed fasteners 

were found, report the following information 

to the FAA at Wichita-COS@faa.gov: 

(1) Name and address of owner. 

(2) Date of the inspection. 

(3) Name, address, phone number, and 

email address of person submitting the 

report. 

(4) Airplane serial number, registration 

number, and total hours TIS on the airplane 

at the time of the inspection. 

(5) If an earlier inspection identified loose, 

fretting, or incorrectly installed fasteners, 

identify the hours TIS on the airplane and 

which fasteners were replaced, if known, or 

if all fasteners were replaced. 

(6) If loose, fretting, or incorrectly installed 

fasteners were found, detailed information 

including a sketch or picture showing the 

location of the loose, fretting, or incorrectly 

installed fasteners and identification of any 

installed supplemental type certificates 

(STCs), alterations, repairs, or field approvals 

affecting the area of concern. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita ACO 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 

certification office, send it to the attention of 

the person identified in the Related 

Information section of this AD. 

(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. 

(j) Related Information 

For more information about this AD, 

contact Bobbie Kroetch, Aviation Safety 

Engineer, Wichita ACO Branch, FAA, 1801 

Airport Road, Wichita, KS 67209; phone: 

316–946–4155; fax: 316–946–4107; email: 

bobbie.kroetch@faa.gov or Wichita-COS@

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 the AD specifies otherwise. 

(i) Task 27–30–00–290, Left and Right 

Elevator Torque Tube Attach Points 

(Borescope) Special Detailed Inspection, 

dated October 1, 2018, of the Cessna Model 

208 Maintenance Manual. 

(ii) [Reserved] 

(3) For Textron Aviation, Inc. service 

information identified in this AD, contact 

Textron Aviation Inc., One Cessna 

Boulevard, Wichita, KS 67215; phone: 316– 

517–5800; email: teamturbopropsupport@

txtav.com; website: https://

support.cessna.com. 

(4) You may view this service information 

at FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust St., 

Kansas City, MO 64106. For information on 

the availability of this material at the FAA, 

call 816–329–4148. 

(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/ 

ibr-locations.html. 

Issued on February 8, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–03478 Filed 3–5–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0095; Project 

Identifier MCAI–2020–01658–R; Amendment 

39–21439; AD 2021–04–17] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Helicopters Model AS350B, 

AS350BA, AS350B1, AS350B2, 

AS350D, AS355E, AS355F, AS355F1, 

AS355F2, and AS355N helicopters. This 

AD was prompted by two reports of 

debonding of the tail rotor (T/R) blade 

leading edge protection shields. This 

AD requires repetitively inspecting 

certain T/R blades and depending on 

the inspection results, replacing the T/ 

R blade, as specified in a European 

Union Aviation Safety Agency (EASA) 

AD, which is incorporated by reference 

(IBR). This AD also prohibits installing 

certain T/R blades. The FAA is issuing 


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13160 Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Rules and Regulations 

this AD to address the unsafe condition 

on these products. 

DATES: This AD becomes effective 

March 23, 2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 23, 2021. 

The FAA must receive comments on 

this AD by April 22, 2021. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

https://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For IBR material 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–2021–0095. 

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– 

0095; 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, any 

comments received, and other 

information. The street address for 

Docket Operations is listed above. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Kristi Bradley, Aviation Safety Engineer, 

General Aviation & Rotorcraft Section, 

International Validation Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 

kristin.bradley@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The EASA, which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2020–0224R1, dated November 11, 2020 

(EASA AD 2020–0224R1), to correct an 

unsafe condition for all Airbus 

Helicopters Model AS 350 B, AS 350 

BA, AS 350 BB, AS 350 B1, AS350 B2, 

AS 350 D, AS 355 E, AS 355 F, AS 355 

F1, AS 355 F2, and AS 355 N 

helicopters. EASA AD 2020–0224R1 

revises EASA AD 2020–0224–E, dated 

October 16, 2020, to expand the list of 

serviceable parts (post-mod 075580). 

This AD was prompted by two reports 

of large debonding of the T/R blade 

leading edge protection shields. 

According to EASA, the design and 

assembly procedure of the affected part 

(pre-mod 075580) is such that rapid 

debonding can occur if humidity/liquid 

water reaches the bonding surface 

between the leading edge and blade 

spar. The FAA is issuing this AD to 

prevent failure of the T/R blade, which 

could result in loss of tail rotor control 

and subsequent loss of control of the 

helicopter. See the EASA AD for 

additional background information. 

Related IBR Material Under 1 CFR Part 

51 

EASA AD 2020–0224R1 specifies 

repetitively visually inspecting each T/ 

R blade leading edge protection shield 

and repetitively tap inspecting each T/ 

R blade leading edge. EASA AD 2020– 

0224R1 also prohibits the installation of 

an affected part and specifies a longerterm modification to replace each 

affected part with a serviceable part. 

EASA AD 2020–0224R1 states that 

replacing all affected parts with 

serviceable parts on a helicopter 

constitutes terminating action for the 

repetitive visual and tap inspections. 

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. 

FAA’s Determination 

These helicopters have been approved 

by EASA and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the 

European Union, EASA has notified the 

FAA about the unsafe condition 

described in its AD. The FAA is 

proposing this AD after evaluating all 

known relevant information and 

determining that the unsafe condition 

described previously is likely to exist or 

develop on other helicopters of these 

same type designs. 

Requirements of This AD 

This AD requires accomplishing the 

actions specified in EASA AD 2020– 

0224R1, described previously, as 

incorporated by reference, except for 

any differences identified as exceptions 

in the regulatory text of this AD and 

except as discussed under ‘‘Differences 

Between this AD and the EASA AD.’’ 

Additionally, the owner/operator (pilot) 

may perform the required visual checks 

but must enter compliance with the 

applicable paragraph of this AD in the 

helicopter maintenance records in 

accordance with 14 CFR 43.9(a)(1) 

through (4) and 91.417(a)(2)(v). A pilot 

may perform these checks because they 

only involve visually checking affected 

T/R blade leading edge protection 

shields and bonding strips. This action 

can be performed equally well by a pilot 

or a mechanic. This check is an 

exception to the FAA’s standard 

maintenance regulations. 

Explanation of Required Compliance 

Information 

In the FAA’s ongoing efforts to 

improve the efficiency of the AD 

process, the FAA initially worked with 

Airbus and EASA to develop a process 

to use certain EASA ADs as the primary 

source of information for compliance 

with requirements for corresponding 

FAA ADs. The FAA has since 

coordinated with other manufacturers 

and civil aviation authorities (CAAs) to 

use this process. As a result, EASA AD 

2020–0224R1 will be incorporated by 

reference in the FAA final rule. This AD 

would, therefore, require compliance 

with EASA AD 2020–0224R1 in its 

entirety, through that incorporation, 

except for any differences identified as 

exceptions in the regulatory text of this 

AD. Using common terms that are the 

same as the heading of a particular 

section in the EASA AD does not mean 

that operators need comply only with 

that section. For example, where the AD 

requirement refers to ‘‘all required 

actions and compliance times,’’ 

compliance with this AD requirement is 

not limited to the section titled 

‘‘Required Action(s) and Compliance 

Time(s)’’ in the EASA AD. Service 

information specified in EASA AD 

2020–0224R1 that is required for 

compliance with EASA AD 2020– 

0224R1 is available on the internet at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0095. 

Differences Between This AD and the 

EASA AD 

The EASA AD applies to all Model 

AS 350 B, AS 350 BA, AS 350 BB, AS 


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350 B1, AS350 B2, AS 350 D, AS 355 

E, AS 355 F, AS 355 F1, AS 355 F2, and 

AS 355 N helicopters, whereas this AD 

applies to Model AS350B, AS350BA, 

AS350B1, AS350B2, AS350D, AS355E, 

AS355F, AS355F1, AS355F2, and 

AS355N helicopters with certain partnumbered T/R blades installed instead. 

This AD does not apply to Model AS 

350 BB because this model is not FAA 

type-certificated. The EASA AD requires 

visually inspecting each T/R blade 

leading edge protection shield. This AD 

requires visually checking each T/R 

blade leading edge protection shield and 

bonding strip instead and allows a pilot 

to accomplish these visual checks. The 

EASA AD requires a longer-term 

modification of replacing each affected 

part with a serviceable part, whereas 

this AD does not. The FAA plans to 

publish a notice of proposed rulemaking 

to give the public an opportunity to 

comment on this longer-term 

requirement. 

FAA’s Justification and Determination 

of the Effective Date 

Section 553(b)(3)(B) of the 

Administrative Procedure Act (5 U.S.C.) 

authorizes agencies to dispense with 

notice and comment procedures for 

rules when the agency, for ‘‘good cause’’ 

finds that those procedures are 

‘‘impracticable, unnecessary, or contrary 

to the public interest.’’ Under this 

section, an agency, upon finding good 

cause, may issue a final rule without 

seeking comment prior to the 

rulemaking. 

An unsafe condition exists that 

requires the immediate adoption of this 

AD without providing an opportunity 

for public comments prior to adoption. 

The FAA has found that the risk to the 

flying public justifies waiving notice 

and comment prior to adoption of this 

rule because the visual repetitive checks 

must be done before each flight and the 

initial instance of the repetitive tap 

inspections must be done within 30 

hours time-in-service, a time period of 

up to about 1.5 months based on the 

average flight-hour utilization rate of 

these helicopters. Accordingly, the 

compliance time for the required actions 

is shorter than the time necessary for the 

public to comment and for publication 

of the final rule. Therefore, notice and 

opportunity for prior public comment 

are impracticable and contrary to public 

interest pursuant to 5 U.S.C. 

553(b)(3)(B). In addition, for the reasons 

stated above, the FAA finds that good 

cause exists pursuant to 5 U.S.C. 553(d) 

for making this amendment effective in 

less than 30 days. 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2021–0095; Project Identifier MCAI– 

2020–01658–R’’ at the beginning of your 

comments. The most helpful comments 

reference a specific portion of the AD, 

explain the reason for any 

recommended change, and include 

supporting data. The FAA will consider 

all comments received by the closing 

date and may amend this AD because of 

those comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to https://

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this AD. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this AD contain 

commercial or financial information 

that is customarily treated as private, 

that you actually treat as private, and 

that is relevant or responsive to this AD, 

it is important that you clearly designate 

the submitted comments as CBI. Please 

mark each page of your submission 

containing CBI as ‘‘PROPIN.’’ The FAA 

will treat such marked submissions as 

confidential under the FOIA, and they 

will not be placed in the public docket 

of this AD. Submissions containing CBI 

should be sent to Kristi Bradley, 

Aviation Safety Engineer, General 

Aviation & Rotorcraft Section, 

International Validation Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 

kristin.bradley@faa.gov. Any 

commentary that the FAA receives that 

is not specifically designated as CBI will 

be placed in the public docket for this 

rulemaking. 

Regulatory Flexibility Act (RFA) 

The requirements of the RFA do not 

apply when an agency finds good cause 

pursuant to 5 U.S.C. 553 to adopt a rule 

without prior notice and comment. 

Because the FAA has determined that it 

has good cause to adopt this rule 

without notice and comment, RFA 

analysis is not required. 

Costs of Compliance 

The FAA estimates that this AD 

affects 450 helicopters of U.S. Registry. 

Labor rates are estimated at $85 per 

work-hour. Based on these numbers, the 

FAA estimates the following costs to 

comply with this AD. 

Visually checking the T/R blades 

takes about 0.25 work-hour for an 

estimated cost of $21 per helicopter and 

$9,450 for the U.S. fleet, per inspection 

cycle. Tap inspecting the T/R blades 

takes about 0.5 work-hour for an 

estimated cost of $43 per helicopter and 

$19,350 for the U.S. fleet, per inspection 

cycle. Replacing a T/R blade takes about 

12 work-hours and parts cost about 

$10,000 for an estimated cost of $11,020 

per T/R blade. 

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 

The FAA determined that this AD 

would not have federalism implications 

under Executive Order 13132. This AD 

would 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 this regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

and 

(2) Will not affect intrastate aviation 

in Alaska. 


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13162 Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Rules and Regulations 

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: 

2021–04–17 Airbus Helicopters: 

Amendment 39–21439; Docket No. 

FAA–2021–0095; Project Identifier 

MCAI–2020–01658–R. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective March 23, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model AS350B, AS350BA, AS350B1, 

AS350B2, AS350D, AS355E, AS355F, 

AS355F1, AS355F2, and AS355N 

helicopters, certificated in any category, with 

a tail rotor (T/R) blade part number (P/N) 

listed in Appendix 1, Table 1, of European 

Union Aviation Safety Agency (EASA) AD 

2020–0224R1, dated November 11, 2020 

(EASA AD 2020–0224R1) (pre-mod 075580). 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 6410, Tail Rotor Blades. 

(e) Reason 

This AD was prompted by two reports of 

debonding of the T/R blade leading edge 

protection shields. The FAA is issuing this 

AD to prevent failure of the T/R blade, which 

could result in loss of tail rotor control 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, EASA AD 2020–0224R1. 

(h) Exceptions to EASA AD EASA AD 2020– 

0224R1 

(1) Where EASA AD 2020–0224R1 refers to 

flight hours (FH), this AD requires using 

hours time-in-service. 

(2) Where EASA AD 2020–0224R1 refers to 

October 20, 2020 (the effective date of the 

original issuance of its AD (EASA AD 2020– 

0224–E, dated October 16, 2020)) and its 

effective date, this AD requires using the 

effective date of this AD. 

(3) Where paragraph (1) of EASA AD 2020– 

0224R1 specifies visually inspecting each T/ 

R blade leading edge protection shield with 

instructions in the service information, this 

AD requires visually checking each T/R blade 

leading edge protection shield and bonding 

strip for a distortion, dent, and scratch; 

visually checking the area surrounding each 

T/R blade leading edge protection along the 

skin length for a gap; and visually checking 

the area surrounding the bonding strip for a 

crack. These visual checks may be performed 

by the owner/operator (pilot) holding at least 

a private pilot certificate and must be entered 

into the aircraft records showing compliance 

with this AD in accordance with 14 

CFR 43.9(a)(1) through (4) and 14 CFR 

91.417(a)(2)(v). The record must be 

maintained as required by 14 CFR 91.417, 

121.380, or 135.439. 

(4) Where paragraph (5) of EASA AD 2020– 

0224R1 specifies the modification of 

replacing each affected part with a 

serviceable part, this AD does not require this 

modification. 

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

2020–0224R1 does not apply to this AD. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, do not 

install a T/R blade identified in paragraph (c) 

of this AD on any helicopter. 

(j) Special Flight Permit 

Special flight permits are prohibited if an 

installed T/R blade does not pass the visual 

or tap inspections. 

(k) 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 (l)(1) 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, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(l) Related Information 

(1) For more information about this AD, 

contact Kristi Bradley, Aviation Safety 

Engineer, General Aviation & Rotorcraft 

Section, International Validation Branch, 

FAA, 10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 

kristin.bradley@faa.gov. 

(m) 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 Union Aviation Safety Agency 

(EASA) AD 2020–0224R1, dated November 

11, 2020. 

(ii) [Reserved] 

(3) For EASA AD 2020–0224R1, 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–2021–0095. 

(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 February 10, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–04803 Filed 3–4–21; 11:15 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0682; Product 

Identifier 2017–SW–028–AD; Amendment 

39–21433; AD 2021–04–12] 

RIN 2120–AA64 

Airworthiness Directives; Robinson 

Helicopter Company Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

Robinson Helicopter Company 

(Robinson) Model R66 helicopters. This 

AD was prompted by reports of tail rotor 

(T/R) drive shaft forward hanger bearing 

failures. This AD requires installing a 

certain part numbered kit and removing 

parts from service or replacing a certain 

part-numbered T/R drive shaft 

assembly. This AD also prohibits the 

installation of certain parts. The FAA is 


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