Federal Register / Vol. 89, No. 187 / Thursday, September 26, 2024 / Rules and Regulations 78785 

List of Subjects in 8 CFR Part 217 

Air carriers, Aliens, Maritime carriers, 

Passports and visas. 

Amendments to the Regulations 

For the reasons stated in the 

preamble, DHS amends part 217 of title 

8 of the Code of Federal Regulations (8 

CFR part 217) as set forth below. 

PART 217—VISA WAIVER PROGRAM 

■ 1. The authority citation for part 217 

continues to read as follows: 

Authority: 8 U.S.C. 1103, 1187; 8 CFR part 

2. 

■ 2. In § 217.2(a), revise the definition of 

‘‘Designated country’’ to read as follows: 

§ 217.2 Eligibility. 

(a) * * * 

Designated country refers to Andorra, 

Australia, Austria, Belgium, Brunei, 

Chile, Croatia, Czech Republic, 

Denmark, Estonia, Finland, France, 

Germany, Greece, Hungary, Iceland, 

Ireland, Israel, Italy, Japan, Latvia, 

Liechtenstein, Lithuania, Luxembourg, 

Malta, Monaco, the Netherlands, New 

Zealand, Norway, Poland, Portugal, 

Qatar, Republic of Korea, San Marino, 

Singapore, Slovak Republic, Slovenia, 

Spain, Sweden, Switzerland, Taiwan, 

and the United Kingdom. The United 

Kingdom refers only to British citizens 

who have the unrestricted right of 

permanent abode in the United 

Kingdom (England, Scotland, Wales, 

Northern Ireland, the Channel Islands, 

and the Isle of Man); it does not refer to 

British overseas citizens, British 

dependent territories’ citizens, or 

citizens of British Commonwealth 

countries. Taiwan refers only to 

individuals who have unrestricted right 

of permanent abode on Taiwan and are 

in possession of an electronic passport 

bearing a personal identification 

(household registration) number. 

* * * * * 

Alejandro N. Mayorkas, 

Secretary. 

[FR Doc. 2024–22050 Filed 9–25–24; 8:45 am] 

BILLING CODE 9110–9M–P 

FEDERAL ELECTION COMMISSION 

11 CFR Part 110 

[Notice 2024–24] 

Fraudulent Misrepresentation of 

Campaign Authority 

AGENCY: Federal Election Commission. 

ACTION: Interpretive rule. 

SUMMARY: The Federal Election 

Commission is issuing guidance on the 

fraudulent misrepresentation of 

campaign authority. 

DATES: This interpretive rule is effective 

September 26, 2024. 

FOR FURTHER INFORMATION CONTACT: Mr. 

Robert M. Knop, Assistant General 

Counsel, or Ms. Jennifer Waldman, 

Attorney, 1050 First Street NE, 

Washington, DC 20463, (202) 694–1650 

or (800) 424–9530. 

SUPPLEMENTARY INFORMATION: The 

Federal Election Campaign Act (‘‘FECA’’ 

or ‘‘Act’’) prohibits the fraudulent 

misrepresentation of campaign 

authority. It does so in two ways: (1) by 

barring Federal candidates or their 

agents from fraudulently 

misrepresenting themselves or 

organizations under their control as 

‘‘speaking or writing or otherwise acting 

for or on behalf of any other candidate 

or political party or employee or agent 

thereof on a matter which is damaging 

to such other candidate or political 

party or employee or agent thereof’’ or 

‘‘willfully and knowingly’’ participating 

in or conspiring to do so; and (2) by 

barring any person from ‘‘fraudulently 

misrepresent[ing]’’ themselves ‘‘as 

speaking, writing, or otherwise acting 

for or on behalf of any candidate or 

political party or employee or agent 

thereof for the purpose of soliciting 

contributions or donations’’ or 

‘‘willfully and knowingly’’ participating 

in or conspiring to do so. 52 U.S.C. 

30124; see also 11 CFR 110.16. 

It has been suggested that this statute 

may have a specific application in light 

of new developments in technology, 

especially content generated with the 

assistance of artificial intelligence 

(‘‘AI’’). For this reason, the Commission 

is issuing this guidance to clarify that 52 

U.S.C. 30124 and 11 CFR 110.16 apply 

irrespective of the technology used to 

conduct fraudulent misrepresentation. 

For purposes of 52 U.S.C. 30124, it 

does not matter whether a regulated 

person uses any particular form of 

technology, including AI, in order to 

‘‘fraudulently misrepresent himself or 

any committee or organization under his 

control as speaking or writing or 

otherwise acting for or on behalf’’ of 

another ‘‘candidate or political party or 

employee or agent’’ or to engage in the 

‘‘[f]raudulent solicitation of funds’’ by 

‘‘misrepresent[ing] the person as 

speaking, writing, or otherwise acting 

for or on behalf of any candidate or 

political party or employee or agent 

thereof for the purpose of soliciting 

contributions or donations.’’ 52 U.S.C. 

30124(a)–(b). The legal question is 

whether the actor fraudulently holds 

himself or herself out as ‘‘acting for or 

on behalf of any other candidate or 

political party or employee or agent 

thereof.’’ Id. This fraud may be 

accomplished using AI-assisted media, 

forged signatures, physically altered 

documents or media, false statements, 

or any other means. The statute, and the 

Commission’s implementing regulation, 

is technology neutral. 

The Commission believes that this 

interpretation of its statute and 

attendant regulation will clarify the 

scope of 52 U.S.C. 30124 in connection 

with evolving technology, including AIassisted media and future developments 

that remain unknown and 

unpredictable. 

This interpretive rule announces the 

general course of action that the 

Commission intends to follow. This 

interpretive rule does not constitute an 

agency action requiring notice of 

proposed rulemaking, opportunities for 

public participation, prior publication, 

or delay in effective date under 5 U.S.C. 

533. It does not bind the Commission or 

any members of the general public, nor 

does it create or remove any rights, 

duties, or obligations. The provisions of 

the Regulatory Flexibility Act, which 

apply when notice and comment are 

required by the Administrative 

Procedure Act or other relevant statute, 

do not apply here. See 5 U.S.C. 603(a). 

Dated: September 20, 2024. 

On behalf of the Commission, 

Sean J. Cooksey, 

Chairman, Federal Election Commission. 

[FR Doc. 2024–21983 Filed 9–25–24; 8:45 am] 

BILLING CODE P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–0237; Project 

Identifier AD–2023–00491–R; Amendment 

39–22853; AD 2024–19–11] 

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 all 

Robinson Helicopter Company Model 

R44 and R44 II helicopters. This AD was 

prompted by reports of a fractured 

clutch shaft forward yoke (yoke) on the 

main rotor (M/R) drive due to fatigue 

cracking. This AD requires visually 


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78786 Federal Register / Vol. 89, No. 187 / Thursday, September 26, 2024 / Rules and Regulations 

inspecting a certain part-numbered flex 

plate assembly (flex plate) and certain 

part-numbered yokes, including each 

flex plate bolt, and depending on the 

inspection results, removing an affected 

part from service and replacing an 

affected part with an airworthy part. 

This AD also requires removing a 

certain part-numbered yoke from service 

after accumulating a certain number of 

hours time-in-service (TIS) or a certain 

number of years, or as an alternative to 

removing the part from service, 

performing a 10× or higher power 

magnification visual inspection and, if 

needed, a magnetic particle inspection. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective October 31, 

2024. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–0237; 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. 

Related Material: For Robinson 

material identified in this AD, contact 

Robinson Helicopter Company, 

Technical Support Department, 2901 

Airport Drive, Torrance, CA 90505; 

phone: (310) 539–0508; fax: (310) 539– 

5198; email: ts1@robinsonheli.com; or at 

robinsonheli.com. 

FOR FURTHER INFORMATION CONTACT: Eric 

Moreland, Aviation Safety Engineer, 

FAA, 3960 Paramount Boulevard, 

Lakewood, CA 90712; phone: (562) 627– 

5364; email: Eric.R.Moreland@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

After receiving a report of a failed 

yoke in the M/R drive system, the FAA 

issued Special Airworthiness 

Information Bulletin AIR–22–08, dated 

April 11, 2022 (SAIB) to remind owners 

and operators of any Robinson 

Helicopter Company Model R44 

helicopters of the importance of 

adhering to existing inspection 

procedures in the applicable operating 

handbooks and maintenance manuals. 

According to Robinson Helicopter 

Company, the yoke had fractured due to 

fatigue cracking and improper torque at 

the bolt hole and the yoke cross-section. 

After the FAA issued the SAIB, 

Robinson Helicopter Company reported 

an additional incident on a Model R44 

helicopter where the yoke was fractured 

and separated from the drive train, again 

due to fatigue cracks and improper 

torquing. 

Accordingly, the FAA issued a notice 

of proposed rulemaking (NPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to all Robinson 

Helicopter Company Model R44 and 

R44 II helicopters. The NPRM published 

in the Federal Register on February 28, 

2024 (89 FR 14596). In the NPRM, the 

FAA proposed to require visually 

inspecting a certain part-numbered flex 

plate for any loose fasteners, cracks, 

fretting, corrosion, wear, and to ensure 

that the washers are bonded to both 

sides of the flex plate arms and 

depending on the inspection results, 

removing the flex plate from service and 

replacing it with an airworthy flex plate. 

In the NPRM, the FAA also proposed 

to require visually inspecting certain 

part-numbered yokes for any cracks, 

corrosion, and fretting, and depending 

on the inspection results, removing the 

yoke from service and replacing it with 

an airworthy yoke. Additionally, the 

FAA proposed to require visually 

inspecting each yoke bolt for a torque 

stripe, loose fastener, loose nut, and to 

determine if a certain part-numbered 

nut and palnut are installed. If there are 

any missing torque stripes, loose 

fasteners, loose nuts, or if certain nuts 

or palnuts are not installed, the FAA 

proposed to require removing the 

associated yoke from service and 

replacing it with an airworthy yoke. 

Additionally in the NPRM, the FAA 

proposed to require removing from 

service certain part-numbered yokes 

that have accumulated more than 12 

years or 2,200 total hours TIS, 

whichever occurs first since first 

installation on any helicopter, and 

replacing them with a certain-partnumbered yoke that has accumulated 

less than 2,200 total hours TIS or 12 

years, whichever occurs first since first 

installation on any helicopter. As an 

alternative to replacing any yoke that 

has accumulated more than 12 years or 

2,200 total hours TIS since first 

installation on a helicopter, the FAA 

proposed to allow removing paint from 

the yoke and using 10× or higher power 

magnifying glass to inspect for any 

crack, seam, lap, shut, missing cadmium 

plating, or any flaw which is open to the 

surface, and depending on the 

inspection results, removing the yoke 

from service and replacing it with an 

airworthy yoke. If the yoke is not 

replaced as a result of the alternate 

inspection, the FAA proposed to require 

performing a magnetic particle 

inspection of the yoke for any crack, 

seam, lap, shut, or any flaw which is 

open to the surface, and depending on 

the inspection results, removing the 

yoke from service and replacing with an 

airworthy yoke. 

Finally, if the yoke is replaced as a 

result of the actions required by the 

NPRM, the FAA proposed to require 

torquing each bolt, nut, and palnut 

using the torque value information in 

Appendix 1 to the proposed AD. 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 

two commenters. The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Comment Supporting the NPRM 

One individual commenter supported 

the NPRM without change. 

Comments Requesting Changes to the 

Required Actions 

Request: Robinson Helicopter 

Company stated the 2,200 hours TIS 

requirement to replace the affected part 

or to perform the magnetic particle 

inspection in the proposed AD 

corresponds with the engine overhaul, 

service life limit, and interval for 

additional maintenance. However, 

Robinson Helicopter Company stated for 

Model R44 Cadet helicopters, the hours 

TIS requirement to replace the affected 

part or to perform the magnetic particle 

inspection is a 2,400 hours TIS 

requirement because of that model’s 

more restrictive operating limitations on 

maximum takeoff weight and engine 

power. Therefore, Robinson Helicopter 

Company requested the FAA increase 

the hours TIS interval for the 

replacement of the affected part or the 

magnetic particle inspection to 2,400 

hours TIS for Model R44 Cadet 

helicopters to allow the operator to 

coordinate the airworthiness directive 

requirements with other mandatory 

maintenance requirements. 

FAA Response: The FAA partially 

agrees with the request. The FAA 

disagrees with revising this final rule to 

refer to Model R44 Cadet helicopters 

because the ‘‘Cadet’’ is not a recognized 

type-certificated model on the FAA type 

certificate data sheet. However, the FAA 

agrees to allow Model R44 helicopters 

having serial numbers (S/N) 30001 and 

subsequent (also known as ‘‘Cadet’’ 

helicopters) to have 2,400 hours TIS to 

replace an affected part or to perform a 

magnetic particle inspection. The FAA 

has revised paragraphs (g)(2) and (3) of 


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Federal Register / Vol. 89, No. 187 / Thursday, September 26, 2024 / Rules and Regulations 78787 

this final rule accordingly to reflect that 

Model R44 helicopters having S/Ns 

30001 and subsequent, on which a yoke 

replacement as specified in this final 

rule was not accomplished is required 

to remove that yoke from service and 

replace it with an airworthy yoke, prior 

to the accumulation of 2,400 total hours 

TIS or within 12 years since first 

installation, whichever occurs first. 

Request: Robinson Helicopter 

Company stated paragraph (g)(3)(i) of 

the proposed AD requires the yoke to be 

replaced if there is any missing 

cadmium plating. Robinson Helicopter 

Company stated cadmium plating 

provides corrosion protection without 

complete coverage and also can be 

inadvertently removed during 

installation and removal of hardware. 

Robinson Helicopter Company further 

stated that the requirement to remove 

the yoke if there is any missing 

cadmium plating will cause the 

unnecessary removal of many yokes. 

Therefore, Robinson Helicopter 

Company requested the FAA add an 

exception for cadmium plating and the 

removal of the yoke from service due to 

cadmium plating. 

FAA Response: The FAA agrees and 

has revised this AD accordingly by not 

adopting the inspection and corrective 

actions associated with cadmium 

plating proposed in the NPRM. 

Request: Robinson Helicopter 

Company stated paragraph (g)(1)(iii) of 

the proposed AD requires ensuring that 

nut part number (P/N) D210–6 and 

palnut P/N B330–19 are installed. 

Robinson stated that per type design, 

only the two bolts on the flex plate 

assembly have palnut P/N B330–19 

installed. Robinson Helicopter Company 

stated the wording in the proposed AD 

could cause some Model R44 

helicopters to replace a yoke 

unnecessarily. Robinson Helicopter 

Company requested the FAA revise 

paragraph (g)(1)(iii) of the final rule to 

only apply to bolts shared with the flex 

plate assembly. Robinson Helicopter 

Company further stated it is possible 

some yokes do not have nut P/N D210– 

6 installed and would therefore also be 

subject to an unnecessary yoke 

replacement. Robinson Helicopter 

Company requested the FAA revise the 

wording of paragraph (g)(1)(iii) in the 

final rule to remove the reference to nut 

P/N D210–6. 

FAA Response: The FAA agrees with 

these requests and revised paragraph 

(g)(1)(iii) of this AD to clarify that the 

inspection area is only for the flex plate 

assembly bolts and to remove any 

references to nut P/N D210–6. 

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. Except for minor editorial 

changes, any other changes described 

previously, and a clarification note 

added to paragraph (g)(1)(i) of this final 

rule, this AD is adopted as proposed in 

the NPRM. None of the changes will 

increase the economic burden on any 

operator. 

Related Material 

The FAA reviewed Robinson 

Helicopter Company R44 Maintenance 

Manual and Instructions for Continued 

Airworthiness, Volume 1, Chapter 2 and 

Chapter 23, dated September 2023, 

which specifies procedures for 

inspecting the yoke and flex plate of the 

M/R drive, removing paint, applying 

torque, and performing a magnetic 

particle inspection. This material also 

contains the information specified in 

Appendix 1 to this AD, which specifies 

torque values, and Figure 1 to paragraph 

(g)(1) of this AD, which depicts the 

areas for the flex plate inspection. 

Costs of Compliance 

The FAA estimates that this AD 

affects 1,725 helicopters of U.S. registry. 

The FAA estimates the following costs 

to comply with this AD. Labor costs are 

estimated at $85 per work-hour. 

Visually inspecting a flex plate will 

take approximately 0.25 work-hour for 

an estimated cost of $21 per helicopter 

and $36,225 for the U.S. fleet. 

Visually inspecting a yoke, including 

inspecting each yoke bolt, will take 

approximately 1.25 work-hours for an 

estimated cost of $106 per helicopter 

and $182,850 for the U.S. fleet. 

Replacing a yoke will take 

approximately 6 work-hours and parts 

will cost approximately $890 for an 

estimated cost of $1,400 per helicopter. 

Removing paint and inspecting a yoke 

using 10X or higher power magnifying 

glass will take approximately 1.5 workhours for an estimated cost of $128 per 

helicopter. 

Performing a magnetic particle 

inspection will take approximately 1.5 

work-hours for an estimated cost of 

$128 per helicopter. 

Applying torque to one bolt, nut, and 

palnut will take approximately 1 workhour for an estimated cost of $85 per 

hardware set. 

If required, replacing a flex plate will 

take approximately 1 work-hour and 

parts will cost approximately $1,240 for 

an estimated cost of $1,325 per 

helicopter. 

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. 


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78788 Federal Register / Vol. 89, No. 187 / Thursday, September 26, 2024 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2024–19–11 Robinson Helicopter Company: 

Amendment 39–22853; Docket No. 

FAA–2024–0237; Project Identifier AD– 

2023–00491–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 31, 2024. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Robinson Helicopter 

Company Model R44 and R44 II helicopters, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code: 6310, Engine/Transmission coupling. 

(e) Unsafe Condition 

This AD was prompted by reports of a 

fractured clutch shaft forward yoke (yoke) on 

the main rotor (M/R) drive due to fatigue 

cracking. The FAA is issuing this AD to 

detect fatigue cracking on the yoke. The 

unsafe condition, if not addressed, could 

result in loss of M/R drive and subsequent 

loss of control of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within 100 hours time-in-service (TIS) 

after the effective date of this AD, accomplish 

the actions required by paragraphs (g)(1)(i) 

through (iii) of this AD. 

(i) Visually inspect forward flex plate 

assembly (flex plate) part number (P/N) 

C947–1 for any loose fasteners, cracks, 

fretting, corrosion, wear, and to ensure that 

the washers are bonded to both sides of each 

flex plate arm, in the areas depicted in Figure 

1 to paragraph (g)(1)(i) of this AD. If there is 

any loose fastener (can be moved by hand), 

crack, fretting, corrosion, or wear that 

consists of the washers not securely bonded 

to both sides of each flex plate arm, before 

further flight, remove the flex plate from 

service and replace with an airworthy flex 

plate. 

Note 1 to paragraph (g)(1)(i): The flex plate 

may be installed in order to accomplish the 

visual inspection. 

Figure 1 to Paragraph (g)(1)(i)—Flex Plate 

Inspection 

(ii) Visually inspect yoke P/N C907–1 or 

C907–2, as applicable to your model 

helicopter, and yoke P/N C908–1, for any 

cracks, corrosion, and fretting. If there is any 

crack, corrosion, or fretting, before further 

flight, remove the yoke from service and 

replace it with an airworthy yoke, and torque 

each newly-installed bolt, nut, and palnut 

using the torque value information in 

Appendix 1 to this AD. 

(iii) Visually inspect each flex plate bolt for 

a torque stripe, loose fastener, and a loose 

nut, and to ensure that palnut P/N B330–19 

is installed. If there is a missing torque stripe, 

loose fastener on any nut (can be moved by 

hand), or if any nut is loose (nut can be 

turned by hand), or if palnut P/N B330–19 is 

not installed, before further flight, remove the 

associated yoke from service and replace it 

with an airworthy yoke, and torque each 

newly-installed bolt, nut, and palnut using 

the torque value information in Appendix 1 

to this AD. 

(2) For Model R44 helicopters having serial 

number 0002, or 0004 through 9999 

inclusive, except not 1140, and R44 II 

helicopters having serial number 1140 or 

10001 through 29999 inclusive on which a 

yoke replacement as specified in paragraph 

(g)(1)(ii) or (iii) of this AD was not 

accomplished: Prior to the accumulation of 

2,200 total hours TIS on any yoke P/N C907– 

1 or C907–2 or within 12 years since first 

installation of yoke P/N C907–1 or C907–2 on 

any helicopter, whichever occurs first; or 

within 100 hours TIS after the effective date 

of this AD; whichever occurs later, remove 

that yoke from service and replace it with an 

airworthy yoke, and torque each newlyinstalled bolt, nut, and palnut using the 

torque value information in Appendix 1 to 

this AD. 

(3) For Model R44 helicopters having serial 

number 30001 and subsequent, on which a 

yoke replacement as specified in paragraph 

(g)(1)(ii) or (iii) of this AD was not 

accomplished: Prior to the accumulation of 

2,400 total hours TIS on any yoke P/N C907– 

1 or C907–2 or within 12 years since first 

installation of yoke P/N C907–1 or C907–2 on 

any helicopter, whichever occurs first; or 

within 100 hours TIS after the effective date 

of this AD; whichever occurs later, remove 

that yoke from service and replace it with an 

airworthy yoke, and torque each newlyinstalled bolt, nut, and palnut using the 


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Give special attention to 

these areas for cracks 

Inspect entire periphery for 

cracks and corrosion. 

Inspect this area for cracks. 

Inspect area around washers 

for fretting. 
Federal Register / Vol. 89, No. 187 / Thursday, September 26, 2024 / Rules and Regulations 78789 

torque value information in Appendix 1 to 

this AD. 

(4) As an alternative to removing the yoke 

from service as required by paragraph (g)(2) 

or (3) of this AD as applicable, remove yoke 

P/N C907–1 or C907–2, as applicable to your 

model helicopter, remove the paint on the 

yoke using Cee-Bee stripper A–292, without 

using a plastic media abrasive paint stripper, 

and accomplish paragraphs (g)(4)(i) and (ii) 

of this AD, as applicable. 

(i) Using 10X or higher power magnifying 

glass, visually inspect the yoke for any crack, 

seam, lap, shut, and any flaw which is open 

to the surface. If there is any crack, seam, lap, 

shut, or flaw, before further flight, remove the 

yoke from service and replace it with an 

airworthy yoke, and torque each newlyinstalled bolt, nut, and palnut using the 

torque value information in Appendix 1 to 

this AD. 

(ii) If the yoke is not removed from service 

as a result of the actions required by 

paragraph (g)(4)(i) of this AD, inspect it for 

any crack, seam, lap, shut, or any flaw which 

is open to the surface by performing a 

magnetic particle inspection using a method 

in accordance with FAA-approved 

procedures. If there is any crack, seam, lap, 

shut, or flaw, before further flight, remove the 

yoke from service and replace with an 

airworthy yoke, and torque each newlyinstalled bolt, nut, and palnut using the 

torque value information in Appendix 1 to 

this AD. 

(h) Special Flight Permit 

A one-time flight permit may be issued in 

accordance with 14 CFR 21.197 and 21.199 

in order to fly to a maintenance area to 

perform the required actions in this AD, 

provided there are no passengers onboard. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, West Certification 

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 West Certification 

Branch, send it to the attention of the person 

identified in paragraph (j) of this AD. 

Information may be emailed to: 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. 

(j) Related Information 

For more information about this AD, 

contact Eric Moreland, Aviation Safety 

Engineer, FAA, 3960 Paramount Boulevard, 

Lakewood, CA 90712; phone: (562) 627– 

5364; email: Eric.R.Moreland@faa.gov. 

(k) Material Incorporated by Reference 

None. 

Appendix 1 to AD 2024–19–11 

BILLING CODE 4910–13–P 


khammond on DSKJM1Z7X2PROD with RULES
78790 Federal Register / Vol. 89, No. 187 / Thursday, September 26, 2024 / Rules and Regulations 


khammond on DSKJM1Z7X2PROD with RULESER26SE24.001</GPH>

NOTE 

1. Torque v--... l!tre In ln(lh-pound$ ~11·1$ otherwls. $Ptli(illfied. 

2. Torque vafu.. Include nut Nlf-loeldng torque. 

3. lncreese torque '1191ues 1 O!ffi. If torqued l!lt boh; head. 

4. Wet Indicates threads lubrlceted wllh A257•9 entkelze. 

5. For elbow tlind tee fittings which requl11e alignment, torque to lndiceted 

vaue. then tighten to desired podtkln. 

a. Tder,nce Is ::t! 1 O!ffi. unfe.K renge 1$ spedfled. 

7. Unless ohrwlse spedfled~ threed slQs S·U and smaller are not used tor 

primary strue11.11"e end do not require control of torques. 

10-32 NAS8EI03 

NAS8803 thru NAS8808 Bobs 114-28 NAS8804 

NAS 1303 thru NAS 1308 Bobs 5116-24 NASeeos NASEl23 Screws 318-24 NASeeoe NAS1351 ,l NAS1352 Screws 

NASOOO thru NAS80S Screws 7/16-20 NAS6607 

112~20 NAseeoa 

A142 SCNWS AN502 Screws 10-32 A142-1, ·3, -4; AN3 

AN503 ScreW$ AN3 BdU AN509 Screws 114--28 AN4 

AN4BdU; 

ANS BdUi AN525 Screws 318-24 ANG 

• MS24894 Screws AN8 BdUi MS270:J9 Screws 112-20 AN8 

10-32 8330-7 (MS2.7151•7l 

STAMPED NUTS 114-28 8330-13 CMS27151· 13l 

(fl'ALNUTS) 5/16-24 8330-18 IMS27151·18l 

Pelnuts are to be usied onlY ·~ 318-24 8330-19 •MS27151·19l 1:1nd repleced with new w'-' 

removed. 7116-20 8330-21 IMS27151-21 l 

112·20 8330-24 (MS27151-241 

118-27 8"notll 5 

Straight fittings Qnly 

1/4-18 8"note 5 

Streight fittings Qnly 

TAPERED PIPE 318-18 8"not• 5 

THREADS Str,alght fittings Qnly 

112-14 See note 5 

Str,alght flttlnm only 

314-14 See note 5 

Str.alght flttiR9$ only 

10-32 AN3t5-3 

ROD END JAM NUTS 114-28 AN3Hl-4 

(AN315 and AN318) 5116-24 AN316-5 

318-24 AN31·8--6 

50 

120 

240 

350 

885 

995 

3,7 

90 

280 

795 

6-15 

11-25 

20-40 

29-80 

42-85 

54-110 

00 

120 

85, 

no 

110 

220 

180 

320 

230 

480 

15 

40 

80 

110 
Federal Register / Vol. 89, No. 187 / Thursday, September 26, 2024 / Rules and Regulations 78791 

Issued on September 19, 2024. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2024–21921 Filed 9–25–24; 8:45 am] 

BILLING CODE 4910–13–C 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2319; Project 

Identifier AD–2024–00498–R; Amendment 

39–22859; AD 2024–19–17] 

RIN 2120–AA64 

Airworthiness Directives; Bell Textron 

Inc. and Various Restricted Category 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Bell 

Textron Inc. Model 204B, 205A, 205A– 

1, 205B, 210, and 212 helicopters and 

various restricted category helicopters 

with certain part-numbered tension 

torsion (TT) straps installed by 

supplemental type certificate (STC) No. 

SR03408CH. This AD was prompted by 

an accident involving failure of a TT 

strap. This AD requires removing the 

specified part-numbered TT straps from 

service and prohibits installing those TT 

straps. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective October 11, 

2024. 

The FAA must receive comments on 

this AD by November 12, 2024. 

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 

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. 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–2319; 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: 

Brian Hanley, Aviation Safety Engineer, 

FAA, 1801 S Airport Road, Wichita, KS 

67209; phone: (847) 294–8140; email: 

Brian.Hanley@faa.gov. 

SUPPLEMENTARY INFORMATION: 

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 the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2024–2319; Project Identifier AD–2024– 

00498–R’’ at the beginning of your 

comments. The most helpful comments 

reference a specific portion of the final 

rule, 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 

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 Brian Hanley, 

Aviation Safety Engineer, FAA, 1801 S 

Airport Road, Wichita, KS 67209; 

phone: (847) 294–8140; email: 

Brian.Hanley@faa.gov. Any commentary 

that the FAA receives which is not 

specifically designated as CBI will be 

placed in the public docket for this 

rulemaking. 

Background 

This AD was prompted by an accident 

involving a Bell Textron Inc. Model 212 

helicopter, which experienced a 

separation of a main rotor blade from 

the main rotor head and subsequent 

impact into terrain shortly after takeoff. 

Initial investigation determined the TT 

strap failed at 664 total hours time-inservice (TIS). Investigations into 

individual wire failure mechanisms are 

ongoing with early indications 

suggesting some wires possibly failed in 

tensile overload and others in fatigue. 

Bell Textron Inc. Model 204B, 205A, 

205A–1, 205B, and 210 helicopters and 

various restricted category helicopters 

are also affected by this unsafe 

condition since the affected TT straps 

may also be installed on these model 

helicopters. 

This condition, if not addressed, 

could result in loss of a main rotor blade 

and subsequent loss of control of the 

helicopter. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

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. 

AD Requirements 

This AD requires removing TT straps 

part numbers AA–204–310–101–101, 

AA–204–310–101–101C, AA–204–310– 

101–103, and AA–204–310–101–103C 

installed by STC No. SR03408CH from 

service and prohibits installing those TT 

straps on any helicopter. 

Interim Action 

The FAA considers this AD to be an 

interim action. If final action is later 

identified, the FAA might consider 

further rulemaking then. 

Justification for Immediate Adoption 

and Determination of the Effective Date 

Section 553(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 


khammond on DSKJM1Z7X2PROD with RULES