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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14156 Federal Register / Vol. 87, No. 49 / Monday, March 14, 2022 / Rules and Regulations 

operation until the affected windshield 

assemblies are replaced. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective April 18, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 18, 2022. 

ADDRESSES: For service information 

identified in this final rule, contact 

Honda Aircraft Company LLC, 6430 

Ballinger Road, Greensboro, NC 27410; 

phone: (336) 662–0246; website: http:// 

www.hondajet.com. You may view this 

service information at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 64106. For information 

on the availability of this material at the 

FAA, call (817) 222–5110. It is also 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0838. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0838; 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: 

Bryan Long, Aviation Safety Engineer, 

Atlanta ACO Branch, FAA, 1701 

Columbia Avenue, College Park, GA 

30337; phone: (404) 474–5578; email: 

bryan.long@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 certain serial-numbered Honda 

Model HA–420 airplanes. The NPRM 

published in the Federal Register on 

September 30, 2021 (86 FR 54126). The 

NPRM was prompted by a report of inflight smoke and fire that initiated from 

the windshield heat power wire braid 

on a Honda Model HA–420 airplane. An 

investigation identified that certain 

Honda Model HA–420 airplanes could 

have a severed windshield heat power 

wire braid from installation of the 

windshield heat wiring during 

manufacture. The severed windshield 

heat power wire braid could cause 

arcing that ignites the wire sheathing 

and sealant and the windshield acrylic. 

This condition, if not addressed, could 

lead to cockpit smoke and fire. In the 

NPRM, the FAA proposed to require 

incorporating temporary revisions into 

the AFM and the QRH that modify 

procedures for windshield heat 

operation until the affected windshield 

assemblies are replaced. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

three commenters. The commenters 

were an individual, an anonymous 

commenter, and Honda. The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Comment Regarding Whether 

Windshield Replacement Is Justified 

An individual requested that the 

NPRM be re-evaluated. The commenter 

stated that although fire is one of the 

greatest dangers in the cockpit, there is 

insufficient data to justify requiring 

windshield assembly replacement. The 

commenter noted that the proposed AD 

is based on a single occurrence of 

cockpit smoke and fire. 

The FAA considered not only the 

occurrence of cockpit smoke and fire 

but also the possible results of a severed 

windshield heat power wire braid. A 

severed windshield heat power wire 

braid could ignite the wire sheathing 

and sealant and the windshield acrylic 

and lead to cockpit smoke and fire. The 

FAA’s analysis determined that an 

unsafe condition exists and is likely to 

exist or develop in airplanes of the same 

type design. Accordingly, this condition 

warrants corrective action through an 

AD. The FAA did not change this AD 

based on this comment. 

Request To Extend the Compliance 

Time for Replacing the Windshield 

Assembly 

Honda requested that the FAA extend 

the compliance time for replacing the 

windshield assembly in paragraph (h) of 

the proposed AD from within 24 months 

to within 36 months after the effective 

date of the AD. In support, Honda stated 

that there is a shortage of parts due to 

supply chain disruptions caused by the 

COVID–19 pandemic. Honda explained 

that extending the compliance time 

would not increase risk to affected 

airplanes because of other mitigating 

actions in place, such as service 

information detailing the risk of 

windshield electrical arcing and the 

revised flight manual procedures, which 

reduce the exposure to an arcing event. 

The FAA has determined that the 24- 

month compliance time for windshield 

assembly replacement is the maximum 

time allowable for the affected airplanes 

to continue to safely operate. While the 

FAA makes every effort to avoid 

grounding aircraft, the FAA cannot base 

its AD action on whether spare parts are 

available or can be produced. However, 

operators may request approval to 

extend the compliance time as an 

alternative method of compliance 

(AMOC) under paragraph (j)(1) of this 

final rule, provided sufficient data are 

submitted. The FAA did not change this 

AD based on this comment. 

Request To Consider Honda’s 

Recommendation 

An anonymous commenter requested 

that the FAA consider Honda’s 

recommendation to replace the 

windshield assembly and incorporate it 

into the mandatory maintenance of the 

airplane. The commenter stated that 

although Honda issued a service 

bulletin, the FAA did not include it in 

the NPRM. 

The commenter’s requested change is 

not necessary because paragraph (h) of 

this AD already requires windshield 

assembly replacement in accordance 

with the steps in the Honda service 

bulletin. In addition, as 14 CFR part 39 

requires that operators comply with 

ADs, replacement of the windshield 

assembly is mandatory. The FAA did 

not change this AD based on this 

comment. 

Conclusion 

The FAA reviewed the relevant data, 

considered any comments received, and 

determined that air safety requires 

adopting this AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. This AD is adopted as 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed the following 

temporary revisions. 

• Honda Aircraft Company 

Temporary Revision TR 04A–1, dated 

2020, for Airplane Flight Manual HJI– 

29001–003–001 Rev C. 

• HondaJet Temporary Revision TR 

04A–1, dated 2020, for Quick Reference 

Handbook HJ1–29000–007–001 Rev C. 

• Honda Aircraft Company 

Temporary Revision TR 04A–1, dated 

2020, for Airplane Flight Manual HJ1– 

29001–003–001 Rev E. 

• HondaJet Temporary Revision TR 

04A–1, dated 2020, for Quick Reference 


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Federal Register / Vol. 87, No. 49 / Monday, March 14, 2022 / Rules and Regulations 14157 

Handbook Normal Procedures Rev E, 

HJ1–29001–007–001. 

These temporary revisions provide 

modified procedures for windshield 

heat operation to reduce exposure to 

potential windshield heat for the 

applicable serial numbers specified on 

the documents. 

The FAA also reviewed Honda 

Service Bulletin SB–420–56–002, 

Revision B, dated April 19, 2021 (Honda 

SB–420–002B). The service bulletin 

specifies identifying and replacing 

affected windshield assemblies. The 

service bulletin also specifies removing 

the temporary revisions to the AFM, 

QRH, and electronic checklist (ECL) 

after the affected windshield assemblies 

have been replaced. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

Differences Between This AD and the 

Service Information 

Honda issued temporary revisions to 

the AFM, QRH, and ECL prior to issuing 

Honda SB–420–002B, which specifies 

replacement of the windshield 

assemblies. Honda SB–420–002B does 

not specify incorporating the temporary 

revisions to the AFM, QRH, and ECL but 

addresses removal if the temporary 

revisions were incorporated. This AD 

does not require incorporating or 

removing the temporary revisions to the 

ECL because the ECL is not part of the 

approved type design of the airplane. 

All pertinent requirements would be 

addressed through the AFM. 

Costs of Compliance 

The FAA estimates that this AD 

affects 156 airplanes of U.S. registry. 

There are 475 affected windshield 

assemblies worldwide, and the FAA has 

no way of knowing the number of 

affected windshield assemblies installed 

on U.S. airplanes. The estimated cost on 

U.S. operators reflects the maximum 

possible cost based on the 156 airplanes 

of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Insert revised procedures in the AFM and 

QRH.

1 work-hour × $85 per hour = $85 ............... Not applicable ... $85 $13,260 

* Windshield assembly replacement (both 

left and right assemblies).

154 work-hours × $85 per hour = $13,090 .. $153,286 .......... 166,376 25,954,656 

Remove revised procedures from the AFM 

and QRH.

1 work-hour × $85 per hour = $85 ............... Not applicable .. 85 13,260 

* On most airplanes, both the left and right windshield assemblies have a serial number affected by the unsafe condition, and the above costs 

represents replacement of both the left and right windshield assemblies. However, some airplanes may only have one affected windshield assembly and not require replacement of both. 

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: 

2022–05–13 Honda Aircraft Company LLC: 

Amendment 39–21965; Docket No. 

FAA–2021–0838; Project Identifier AD– 

2020–01590–A. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective April 18, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Honda Aircraft 

Company LLC Model HA–420 airplanes, 

serial numbers 42000011 through 42000179, 

42000182, and 42000187, certificated in any 

category, with a windshield assembly 

installed that has a part number and serial 

number listed in table 5 of the 

Accomplishment Instructions in Honda 

Aircraft Company Alert Service Bulletin SB– 

420–56–002, Revision B, dated April 19, 

2021 (Honda SB–420–56–002, Revision B). 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 3040, Windshield/Door Rain/Ice 

Removal. 

(e) Unsafe Condition 

This AD was prompted by a report of inflight smoke and fire that initiated from the 


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14158 Federal Register / Vol. 87, No. 49 / Monday, March 14, 2022 / Rules and Regulations 

windshield heat power wire braid. The FAA 

is issuing this AD to prevent arcing of the 

windshield heat power wire braid, which 

could ignite the wire sheathing and sealant 

and the windshield acrylic. This condition, 

if not addressed, could lead to cockpit smoke 

and fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Temporary Revisions to the Airplane 

Flight Manuals (AFMs) and Quick Reference 

Handbooks (QRHs) 

(1) Within 15 days after the effective date 

of this AD, revise the existing AFM and QRH 

for your airplane by inserting the pages 

identified in the applicable temporary 

revisions listed in paragraphs (g)(1)(i) 

through (iv) of this AD. 

(i) Honda Aircraft Company Temporary 

Revision TR 04A–1, dated 2020, for Airplane 

Flight Manual HJI–29001–003–001 Rev C. 

(ii) HondaJet Temporary Revision TR 04A– 

1, dated 2020, for Quick Reference Handbook 

HJ1–29000–007–001 Rev C. 

(iii) Honda Aircraft Company Temporary 

Revision TR 04A–1, dated 2020, for Airplane 

Flight Manual HJ1–29001–003–001 Rev E. 

(iv) HondaJet Temporary Revision TR 04A– 

1, dated 2020, for Quick Reference Handbook 

Normal Procedures Rev E, HJ1–29001–007– 

001. 

(2) The actions required by paragraph (g)(1) 

of this AD 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. 

(h) Windshield Assembly Replacement 

Within 24 months after the effective date 

of this AD, for each windshield assembly 

with a part number and serial number listed 

in table 5 of the Accomplishment 

Instructions in Honda SB–420–56–002, 

Revision B, replace the windshield assembly 

in accordance with step (2) or (3) of the 

Accomplishment Instructions in Honda SB– 

420–56–002, Revision B. 

(i) Removal of Revisions to the AFMs and 

QRHs 

Before further flight after replacing the 

windshield assemblies required by paragraph 

(h) of this AD, remove the AFM and QRH 

pages that were required by paragraph (g) of 

this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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 paragraph (k) 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. 

(3) For service information that contains 

steps that are labeled as ‘‘Required for 

Compliance’’ (RC), the following provisions 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(k) Related Information 

For more information about this AD, 

contact Bryan Long, Aviation Safety 

Engineer, Atlanta ACO Branch, FAA, 1701 

Columbia Avenue, College Park, GA 30337; 

phone: (404) 474–5578; email: Bryan.Long@

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 the AD specifies otherwise. 

(i) Honda Aircraft Company Temporary 

Revision TR 04A–1, dated 2020, for Airplane 

Flight Manual HJI–29001–003–001 Rev C. 

(ii) Honda Aircraft Company Temporary 

Revision TR 04A–1, dated 2020, for Airplane 

Flight Manual HJ1–29001–003–001 Rev E. 

(iii) HondaJet Temporary Revision TR 

04A–1, dated 2020, for Quick Reference 

Handbook HJ1–29000–007–001 Rev C. 

(iv) HondaJet Temporary Revision TR 04A– 

1, dated 2020, for Quick Reference Handbook 

Normal Procedures Rev E, HJ1–29001–007– 

001. 

(v) Honda Aircraft Company Alert Service 

Bulletin SB–420–56–002, Revision B, dated 

April 19, 2021. 

(3) For service information identified in 

this AD, contact Honda Aircraft Company 

LLC, 6430 Ballinger Road, Greensboro, NC 

27410; phone: (336) 662–0246; website: 

https://www.hondajet.com. 

(4) You may view this service information 

at FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 64106. For information on 

the availability of this material at the FAA, 

call (817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

email: fr.inspection@nara.gov, or go to: 

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on February 25, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–05222 Filed 3–11–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0158; Project 

Identifier AD–2022–00199–R; Amendment 

39–21971; AD 2022–06–05] 

RIN 2120–AA64 

Airworthiness Directives; Various 

Restricted Category Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2021–15– 

52 which applied to various restricted 

category helicopters originally 

manufactured by Bell Textron Inc. with 

a certain main rotor hub strap pin (pin) 

installed. AD 2021–15–52 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 

2021–15–52 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. Finally, this AD updates the 

current type certificate holder 

information as reflected in the type 

certificate data sheet (TCDS) and 

expands the applicability of AD 2021– 

15–52. 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. 


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