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

14153 

Vol. 87, No. 49 

Monday, March 14, 2022 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0157; Project 

Identifier AD–2022–00193–R; Amendment 

39–21969; AD 2022–06–03] 

RIN 2120–AA64 

Airworthiness Directives; Bell Textron 

Inc. (Type Certificate Previously Held 

by Bell Helicopter Textron Inc.) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2022–02– 

02 which applied to certain Bell Textron 

Inc. (type certificate previously held by 

Bell Helicopter Textron Inc.) Model 

204B, 205A, 205A–1, 205B, 210, and 

212 helicopters with a certain main 

rotor hub strap pin (pin) installed. AD 

2022–02–02 required removing certain 

outboard pins from service and 

prohibited installing them on any 

helicopter. This AD expands the 

applicability to all affected pins, 

regardless if they are outboard or 

inboard. This AD also requires 

inspecting the removed pin for any 

deformation and if it is deformed, 

removing the mating strap fitting 

(fitting) from service. This AD was 

prompted by the discovery that AD 

2022–02–02 inadvertently limited its 

applicability to only outboard pins 

when, in fact, all pins are subject to the 

unsafe condition and the determination 

that a deformed pin may have damaged 

the fitting. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective March 16, 

2022. 

The FAA must receive any comments 

on this AD by April 28, 2022. 

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 service information identified in 

this final rule, contact Bell Textron, Inc., 

P.O. Box 482, Fort Worth, TX, 76101; 

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

8023; fax (450) 433–0272; email 

productsupport@bellflight.com; or at 

https://www.bellflight.com/support/ 

contact-support. 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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0157; 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 street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Kuethe Harmon, Safety Management 

Program Manager, Certification & 

Program Management Section, DSCO 

Branch, Compliance & Airworthiness 

Division, FAA, 10101 Hillwood Pkwy., 

Fort Worth, TX 76177; telephone (817) 

222–5198; email kuethe.harmon@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued Emergency AD 2021– 

15–51 on July 6, 2021, and it published 

as a Final rule; request for comments on 

August 9, 2021 as Amendment 39– 

21678 (86 FR 43406) (AD 2021–15–51). 

AD 2021–15–51 applied to Bell Textron 

Inc. Model 204B, 205A, 205A–1, 205B, 

and 212 helicopters with a pin part 

number (P/N) 204–012–104–005 with a 

serial number (S/N) prefix ‘‘FNFS’’ 

installed. AD 2021–15–51 was 

prompted by a fatal accident of a Model 

212 helicopter in which the affected pin 

sheared off during flight, resulting in the 

main rotor blade and the main rotor 

head detaching from the helicopter. The 

pin had accumulated only 20 total hours 

time-in-service (TIS). An inspection of a 

different Model 212 helicopter revealed 

that another pin installed, and made by 

the same manufacturer and with the 

same S/N prefix, was deformed; this pin 

had accumulated only 29 total hours 

TIS. Because an affected pin could also 

be installed on other helicopters, AD 

2021–15–51 also applied to Model 

204B, 205A, 205A–1, and 205B 

helicopters. Failure of a pin could result 

in the main rotor blade detaching from 

the helicopter and subsequent loss of 

control of the helicopter. 

After AD 2021–15–51 was issued, it 

was determined that an affected pin 

could also be installed on Model 210 

helicopters. Therefore, the FAA issued 

superseding AD 2022–02–02 (87 FR 

1668, January 12, 2022) (AD 2022–02– 

02) which retained all of the 

requirements in AD 2021–15–51 and 

added Model 210 helicopters to the 

applicability. However, as published, 

the AD number in the regulatory text 

was incorrectly specified as FAA–2021– 

1003; the correct AD number was 2022– 

02–02. The FAA subsequently issued 

corrected AD 2022–02–02 (87 FR 7368, 

February 9, 2022) to correct the AD 

number. 

Actions Since AD 2022–02–02 Was 

Issued 

Since the FAA issued AD 2022–02– 

02, it was discovered that the word 

‘‘outboard’’ was inadvertently included 

in that AD’s applicability, resulting in 

the possibility that corrective actions for 

the inboard pin may not be 

accomplished. Additionally, the FAA 

determined, after further review of the 

related service information, that 

inspecting the affected pin for any 

deformity and removing the fitting P/N 

212–010–103–ALL or 204–012–103– 

ALL from service is required to address 

the unsafe condition. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 


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14154 Federal Register / Vol. 87, No. 49 / Monday, March 14, 2022 / Rules and Regulations 

FAA’s Determination 

The FAA is issuing this AD because 

the agency determined the unsafe 

condition described previously is likely 

to exist or develop in other products of 

the same type designs. 

Related Service Information 

The FAA reviewed Bell Alert Service 

Bulletins (ASBs), each Revision A and 

dated July 22, 2021: 

• ASB 204B–21–74 for Model 204B 

helicopters, S/Ns 2001 through 2070 

and 2196 through 2199; 

• ASB 205–21–117 for Model 205A 

and 205A–1 helicopters, S/Ns 30001 

through 30065, 30067 through 30165, 

30167 through 30187, 30189 through 

30296, and 30298 through 30332; 

• ASB 205B–21–71 for Model 205B 

helicopters, S/Ns 30066, 30166, 30188, 

and 30297; 

• ASB 210–21–14 for all Model 210 

helicopters, and 

• ASB 212–21–165 for Model 212 

helicopters, S/Ns 30501 through 30999, 

31101 through 31311, 32101 through 

32142, and 35001 through 35103. 

The ASBs specify removing all P/N 

204–012–104–005 pins with an S/N 

prefix ‘‘FNFS’’ before further flight. The 

ASBs also specify inspecting removed 

pins for deformation and scrapping the 

fitting, P/N 212–010–103–ALL or 204– 

012–103–ALL, if the pin is deformed. 

The ASBs also specify that, although the 

investigation is still in progress, 

removing these pins from service is 

required. The ASBs state that these pins 

may not have been manufactured in 

accordance with the engineering design 

requirements and may therefore shear as 

a result of this nonconformance. 

AD Requirements 

This AD requires, before further flight, 

removing from service each pin P/N 

204–012–104–005 with an S/N prefix 

‘‘FNFS’’ and inspecting it for any 

deformation. If there is any deformation, 

this AD also requires removing the 

fitting from service before further flight. 

Finally, this AD prohibits installing the 

affected pin on any helicopter as of the 

effective date of this AD. 

Interim Action 

The FAA considers this AD to be an 

interim action. If final action is later 

identified, the FAA might consider 

further rulemaking. 

Justification for Immediate Adoption 

and Determination of the Effective Date 

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

Administrative Procedure Act (APA) (5 

U.S.C. 551 et seq.) 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 providing notice and 

seeking comment prior to issuance. 

Further, section 553(d) of the APA 

authorizes agencies to make rules 

effective in less than thirty days, upon 

a finding of good cause. 

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 foregoing notice 

and comment prior to adoption of this 

rule because an affected pin was 

involved in a fatal accident in which the 

pin sheared off during flight, resulting 

in the main rotor blade and the main 

rotor head detaching from the 

helicopter. That pin had accumulated 

only 20 total hours TIS. An additional 

investigation revealed that another pin 

installed on a different helicopter and 

made by the same manufacturer and 

with the same S/N prefix was deformed. 

This pin had accumulated only 29 total 

hours TIS. The wording in AD 2022–02– 

02 could have caused an inboard pin 

with the same part number and S/N 

prefix, which is subject to the same 

unsafe condition, to be left in service. 

Failure of an affected pin could occur at 

any time without any previous 

indication, which could result in the 

failure of parts critical to the control of 

the helicopter. Thus, an urgent unsafe 

condition exists and corrective actions 

must be accomplished before further 

flight. 

Accordingly, notice and opportunity 

for prior public comment are 

impracticable and contrary to the public 

interest pursuant to 5 U.S.C. 

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

found good cause to forgo notice and 

comment. 

Comments Invited 

The FAA invites you to send any 

written data, views, or arguments about 

this final rule. Send your comments to 

an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2022–0157 

and Project Identifier AD 2022–00193– 

R’’ at the beginning of your comments. 

The most helpful comments reference a 

specific portion of the proposal, 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 final rule 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 final rule. 

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 Kuethe Harmon, 

Safety Management Program Manager, 

Certification & Program Management 

Section, DSCO Branch, Compliance & 

Airworthiness Division, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177. 

Any commentary that the FAA receives 

which is not specifically designated as 

CBI will be placed in the public docket 

for this rulemaking. 

Regulatory Flexibility Act 

The requirements of the Regulatory 

Flexibility Act (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 prior 

notice and comment, RFA analysis is 

not required. 

Costs of Compliance 

The FAA estimates that this AD 

affects 155 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. 

Replacing up to four pins takes about 

20 work-hours and parts cost about 

$1,756 for four pins for an estimated 

cost of up to $3,456 per helicopter, and 

up to $535,680 for the U.S. fleet. 


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Federal Register / Vol. 87, No. 49 / Monday, March 14, 2022 / Rules and Regulations 14155 

Replacing up to 4 fittings takes about 

2 work-hours and parts cost about 

$14,400 for an estimated cost of up to 

$14,570 per helicopter, and up to 

$2,258,350 for the U.S. fleet. 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, some of the 

costs of this AD may be covered under 

warranty, thereby reducing the cost 

impact on affected individuals. 

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, 

and 

(2) Will not affect intrastate aviation 

in Alaska. 

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: 

■ a. Removing Airworthiness Directive 

(AD) 2022–02–02, Amendment 39– 

21899 (87 FR 1668, January 12, 2022; 

corrected 87 FR 7368, February 9, 2022); 

and 

■ b. Adding the following new AD: 

2022–06–03 Bell Textron Inc. (Type 

Certificate Previously Held by Bell 

Helicopter Textron Inc.: Amendment 

39–21969; Docket No. FAA–2022–0157; 

Project Identifier AD–2022–00193–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 16, 2022. 

(b) Affected ADs 

This AD replaces AD 2022–02–02, 

Amendment 39–21899 (87 FR 1668, January 

12, 2022) and corrected as AD 2022–02–02, 

Amendment 39–21899 (87 FR 7368, February 

9, 2022). 

(c) Applicability 

This AD applies to Bell Textron Inc. (type 

certificate previously held by Bell Helicopter 

Textron Inc.) Model 204B, 205A, 205A–1, 

205B, 210, and 212 helicopters, certificated 

in any category, with a main rotor hub strap 

pin (pin) part number 204–012–104–005 with 

a serial number prefix ‘‘FNFS’’ installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code: 6200, Main Rotor System. 

(e) Unsafe Condition 

This AD was prompted by a fatal accident 

in which a pin sheared off during flight, 

which resulted in the main rotor blade and 

the main rotor head detaching from the 

helicopter. The FAA is issuing this AD to 

address this unsafe condition and prevent 

loss of control of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Before further flight after the effective 

date of this AD, remove from service any pin 

that is identified in paragraph (c) of this AD 

and inspect it for any deformity. If the pin 

is deformed, remove from service the mating 

strap fitting (P/N 212 –010–103–ALL or 204– 

012–103–ALL). 

(2) As of the effective date of this AD, do 

not install any pin that is identified in 

paragraph (c) of this AD on any helicopter. 

(h) Special Flight Permit 

Special flight permits are prohibited. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, DSCO Branch, 

Compliance & Airworthiness Division, 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 DSCO Branch, 

send it to the attention of the person 

identified in paragraph (j) of this AD. 

Information may be emailed to: 9-ASW-190- 

COS@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. 

(j) Related Information 

For more information about this AD, 

contact Kuethe Harmon, Safety Management 

Program Manager, Certification & Program 

Management Section, DSCO Branch, 

Compliance & Airworthiness Division, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5198; email 

kuethe.harmon@faa.gov. 

(k) Material Incorporated by Reference 

None. 

Issued on March 4, 2022. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–05378 Filed 3–10–22; 11:15 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0838; Project 

Identifier AD–2020–01590–A; Amendment 

39–21965; AD 2022–05–13] 

RIN 2120–AA64 

Airworthiness Directives; Honda 

Aircraft Company LLC Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Honda Aircraft Company LLC (Honda) 

Model HA–420 airplanes. This AD was 

prompted by a report of in-flight smoke 

and fire that initiated from the 

windshield heat power wire braid. This 

AD requires incorporating temporary 

revisions into the airplane flight manual 

(AFM) and the quick reference 

handbook (QRH) that modify 

procedures for windshield heat 


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