80952 Federal Register / Vol. 88, No. 223 / Tuesday, November 21, 2023 / Rules and Regulations 

7 5 U.S.C. 601 et seq. 

8 Id. at 603(a); NCUA Interpretive Ruling and 

Policy Statement 15–2. 

9 5 U.S.C. 551. 

10 Id. 

and Budget (OMB) control number. 

OMB has approved the current 

information collection requirements and 

assigned them control number 3133– 

0133. This rule adds a new entity to the 

definition of a ‘‘qualified charity.’’ 

NCUA does not anticipate an increase in 

the recordkeeping requirement 

associated with CDAs. 

B. Regulatory Flexibility Act 

The Regulatory Flexibility Act 7

requires the NCUA to prepare an 

analysis to describe any significant 

economic impact a regulation may have 

on a substantial number of small entities 

(defined as credit unions with under 

$100 million in assets).8 This rule 

merely adds an additional category of 

permissible entities to which a Federal 

credit union may donate through a CDA. 

Currently, there are only 136 Federal 

credit unions utilizing CDAs, with an 

average size of approximately $1.74 

billion. Of these 136, only 18 are ‘‘small 

entities,’’ as defined in the first sentence 

of this paragraph. The NCUA estimates 

that a limited number of Federal credit 

unions would utilize the authority 

granted in this rule. In addition, as the 

rule merely adds another category of 

permissible entities a Federal credit 

union may donate to through a CDA, the 

NCUA does not find that this rule 

would impose a cost or burden on any 

Federal credit unions. As such, the 

NCUA certifies that this rule will not 

have a significant economic impact on 

a substantial number of small entities. 

C. Executive Order 13132 

Executive Order 13132 encourages 

independent regulatory agencies to 

consider the impact of their actions on 

State and local interests. The NCUA, an 

independent regulatory agency as 

defined in 44 U.S.C. 3502(5), voluntarily 

complies with the Executive Order to 

adhere to fundamental federalism 

principles. 

This rule will not have substantial 

direct effects 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. The rule will 

affect only Federal credit unions. 

Federally insured, State-chartered credit 

unions derive their investment and 

incidental powers authority from State 

law, and the NCUA’s regulations do not 

determine the permissibility of such 

investments or activities. The NCUA has 

therefore determined that this rule does 

not constitute a policy that has 

federalism implications for purposes of 

the Executive Order. 

D. Assessment of Federal Regulations 

and Policies on Families 

The NCUA has determined that this 

rule will not affect family well-being 

within the meaning of section 654 of the 

Treasury and General Government 

Appropriations Act, 1999, Public Law 

105–277, 112 Stat. 2681 (1998). The 

final rule could increase charitable 

donations by Federal credit unions to 

organizations that provide benefits or 

services to veterans’ households, but the 

Board believes that the connection will 

not be direct and is uncertain. 

E. Small Business Regulatory 

Enforcement Fairness Act— 

Congressional Review Act 

The Congressional Review chapter of 

the Small Business Regulatory 

Enforcement Fairness Act of 1996 

(SBREFA) generally provides for 

congressional review of agency rules.9 A 

reporting requirement is triggered in 

instances where the NCUA issues a final 

rule as defined in the Administrative 

Procedure Act.10 Besides being subject 

to congressional oversight, an agency 

rule may also be subject to a delayed 

effective date if it is a ‘‘major rule.’’ The 

NCUA does not believe this rule is a 

‘‘major rule’’ within the meaning of the 

relevant sections of the statute. As 

required by the statute, the NCUA will 

submit this final rule to OMB for it to 

determine if this final rule is a ‘‘major 

rule’’ for purposes of the statute. The 

NCUA also will file appropriate reports 

with Congress and the Government 

Accountability Office so this rule may 

be reviewed. 

List of Subjects in 12 CFR Part 721 

Credit unions. 

By the NCUA Board on November 16, 

2023. 

Melane Conyers-Ausbrooks, 

Secretary of the Board. 

For the reasons discussed in the 

preamble, the NCUA Board is amending 

12 CFR part 721 as follows: 

PART 721—INCIDENTAL POWERS 

■ 1. The authority citation for part 721 

continues to read as follows: 

Authority: 12 U.S.C. 1757(17), 1766, and 

1789. 

■ 2. Amend § 721.3 by revising 

paragraph (b)(2)(vii)(B) to read as 

follows: 

§ 721.3 What categories of activities are 

preapproved as incidental powers 

necessary or requisite to carry on a credit 

union’s business? 

* * * * * 

(b) * * * 

(2) * * * 

(vii) * * * 

(B) Qualified charity is a charitable 

organization or other non-profit entity 

recognized as exempt from taxation 

under section 501(c)(3) or 501(c)(19) of 

the Internal Revenue Code. 

* * * * * 

[FR Doc. 2023–25749 Filed 11–20–23; 8:45 am] 

BILLING CODE 7535–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–2140; Project 

Identifier AD–2023–01071–T; Amendment 

39–22590; AD 2023–22–06] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 96–12–20, 

which applied to certain Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company Model 382, 382B, 

382E, 382F, and 382G airplanes. AD 96– 

12–20 required visual inspections to 

detect loose, missing, or deformed 

fasteners in the upper truss mounts of 

certain engines, visual inspections to 

detect cracking in the associated lugs, 

repetitive ultrasonic inspections to 

detect cracking of the upper lugs, and 

replacement of damaged or cracked 

parts. AD 96–12–20 also provided for an 

optional terminating action for the 

repetitive inspections. This AD was 

prompted by reports of fatigue cracking 

of the lugs of the upper truss mount, 

and by reports of cracks found prior to 

the initial inspection times required by 

AD 96–12–20 and the determination 

that the terminating action is no longer 

valid. This AD requires one-time 

inspections for cracked or severed 

engine truss mount upper lugs of the 

outboard engines, and replacement of 

the engine truss mount if necessary. 

This AD also revises the applicability to 

include all Model 382, 382B, 382E, 

382F, and 382G airplanes, and all Model 


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Federal Register / Vol. 88, No. 223 / Tuesday, November 21, 2023 / Rules and Regulations 80953 

EC–130Q, C–130H, HP–C–130A, C– 

130A, and C–130B (including Model 

282–44A–05) airplanes. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective November 

21, 2023. 

The FAA must receive comments on 

this AD by January 5, 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 by searching 

for and locating Docket No. FAA–2023– 

2140; 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: Fred 

Caplan, Aviation Safety Engineer, FAA, 

1701 Columbia Avenue, College Park, 

GA 30337; phone: 404–474–5507; email: 

9-ASO-ATLACO-ADs@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 ADDRESSES. 

Include ‘‘Docket No. FAA–2023–2140 

and Project Identifier AD–2023–01071– 

T’’ 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 Fred Caplan, Aviation 

Safety Engineer, FAA, 1701 Columbia 

Avenue, College Park, GA 30337; phone: 

404–474–5507; email: 9-ASO-ATLACOADs@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. 

Background 

The FAA issued AD 96–12–20, 

Amendment 39–9663 (61 FR 29279, 

June 10, 1996; corrected August 16, 

1996 (61 FR 42549)) (AD 96–12–20), for 

certain Lockheed Martin Corporation/ 

Lockheed Martin Aeronautics Company 

Model 382, 382B, 382E, 382F, and 382G 

airplanes. AD 96–12–20 required visual 

inspections to detect loose, missing, or 

deformed fasteners in the upper truss 

mounts of certain engines; inspections 

to detect cracking in the associated lugs; 

repetitive ultrasonic inspections to 

detect cracking of the upper lugs; and 

replacement of damaged and cracked 

parts. This amendment also provides for 

an optional terminating action for the 

repetitive inspections. AD 96–12–20 

was prompted by reports of fatigue 

cracking of the lugs of the upper truss 

mount. The FAA issued AD 96–12–20 to 

prevent multiple failures of the upper 

truss mounts due to problems associated 

with fatigue cracking, which could 

adversely affect the integrity of the 

engine mount structure. 

Actions Since AD 96–12–20 Was Issued 

Since the FAA issued AD 96–12–20, 

the FAA has been notified of additional 

crack findings in engine truss mount 

upper lugs occurring prior to the initial 

inspection times required by AD 96–12– 

20. The cracks were found to have 

progressed entirely through these parts 

and have been found on multiple 

airplanes. In addition, modified parts, 

required by the terminating action in 

AD 96–12–20, that were intended to 

have a longer operational life have not 

resulted in longer periods before cracks 

occur; therefore, the previous 

terminating action is not valid, and 

airplanes on which the terminating 

action was done must be inspected. The 

restricted category models EC–130Q, C– 

130H, HP–C–130A, C–130A, and C– 

130B (including Model 282–44A–05) 

were added to the Model 382 airplanes 

affected by AD 96–12–20, since they 

share the same type design in the area 

where cracking is occurring. Fatigue 

cracking of a single engine truss mount 

upper lug could reduce the static 

strength of an engine mount to limit 

load, while cracking of both lugs can 

lead to separation of the engine, 

catastrophic structural damage, and loss 

of control of the airplane. 

FAA’s Determination 

The FAA is issuing this AD because 

the agency has determined the unsafe 

condition described previously is likely 

to exist or develop in other products of 

the same type design. 

AD Requirements 

This AD does not retain the 

requirements of AD 96–12–20. This AD 

revises the applicability of AD 96–12–20 

by expanding to all Model 382, 382B, 

382E, 382F, and 382G airplanes, and 

adding Model EC–130Q, C–130H, HP– 

C–130A, C–130A, and C–130B 

(including Model 282–44A–05) 

airplanes. This AD requires one-time 

inspections to detect cracking of the No. 

1 and No. 4 engine truss mount upper 

lugs, lower surfaces, at outer wing 

station (OWS) 162 and OWS 197; 

cracking of the No. 1 and No. 4 engine 

truss mount upper lug side surfaces, 

inboard and outboard, at OWS 162 and 

OWS 197; and severed engine truss 

mount upper lugs; and replacement of 

the engine truss mount if found with 

cracked or severed engine truss mount 

upper lugs. 

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. 

Impact on Intrastate Aviation in Alaska 

In light of the heavy reliance on 

aviation for intrastate transportation in 

Alaska, the FAA fully considered the 

effects of this AD (including costs to be 

borne by affected operators) from the 

earliest possible stages of AD 

development. This AD is based on those 

considerations, and was developed with 


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80954 Federal Register / Vol. 88, No. 223 / Tuesday, November 21, 2023 / Rules and Regulations 

regard to minimizing the economic 

impact on operators to the extent 

possible, consistent with the safety 

objectives of this AD. In any event, the 

Federal Aviation Regulations require 

operators to correct an unsafe condition 

identified on an airplane to ensure 

operation of that airplane in an 

airworthy condition. The FAA has 

determined in this case that the 

requirements are necessary and the 

indirect costs would be outweighed by 

the safety benefits of the AD. 

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 forgoing notice 

and comment prior to adoption of this 

rule because fatigue cracking of a single 

engine truss mount upper lug reduces 

the static strength of an engine mount to 

limit load, while cracking of both lugs 

can lead to separation of the engine, 

catastrophic structural damage, and loss 

of control of the airplane. Further, based 

upon the additional applicability of 

affected airplanes and the previously 

insufficient service information, it is 

likely that further fatigue cracking and 

reduction in static strength has occurred 

and could result in imminent separation 

of the engine, catastrophic structural 

damage, and loss of control of the 

airplane. Finally, the compliance time 

for the required action is shorter than 

the time necessary for the public to 

comment and for publication of the final 

rule. 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. 

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 notice 

and comment, RFA analysis is not 

required. 

Costs of Compliance 

The FAA estimates that this AD 

affects 41 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 

Inspections ...................................................... 10 work-hours × $85 per hour = $850 ........... $0 $850 $34,850 

The FAA has received no definitive 

data on which to base the cost estimates 

for the on-condition actions specified in 

this AD. 

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 is not a ‘‘significant 

regulatory action’’ under Executive 

Order 12866. 

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) AD 96–12–20, Amendment 39– 

9663 (61 FR 29279, June 10, 1996; 

corrected August 16, 1996 (61 FR 

42549)); and 

b. Adding the following new AD: 

2023–22–06 Lockheed Martin Corporation/ 

Lockheed Martin Aeronautics Company: 

Amendment 39–22590; Docket No. 

FAA–2023–2140; Project Identifier AD– 

2023–01071–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective November 21, 2023. 

(b) Affected ADs 

This AD replaces AD 96–12–20, 

Amendment 39–9663 (61 FR 29279, June 10, 

1996; corrected August 16, 1996 (61 FR 

42549)) (AD 96–12–20). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (2) of this AD. 

(1) All Lockheed Martin Corporation/ 

Lockheed Martin Aeronautics Company 

Model 382, 382B, 382E, 382F, and 382G 

airplanes, certificated in any category. 


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Federal Register / Vol. 88, No. 223 / Tuesday, November 21, 2023 / Rules and Regulations 80955 

(2) All airplanes specified in paragraphs 

(c)(2)(i) through (xi) of this AD, type 

certificated in the restricted category. 

(i) LeSEA Model C–130A airplanes 

(transferred from Central Air Services, Inc.), 

Type Certificate Data Sheet (TCDS) A34SO, 

Revision 1. 

(ii) T.B.M., Inc., Model C–130A airplanes, 

TCDS A39CE, Revision 3. 

(iii) Western International Aviation, Inc., 

Model C–130A airplanes, TCDS A33NM. 

(iv) USDA Forest Service Model C–130A 

airplanes, TCDS A15NM, Revision 4. 

(v) Snow Aviation International, Inc., 

Model C–130A airplanes, TCDS TQ3CH, 

Revision 1. 

(vi) International Air Response (transferred 

from Rogers Helicopters, Inc., and Heavylift 

Helicopters Inc.) Model C–130A airplanes, 

TCDS A31NM, Revision 3. 

(vii) Heavylift Helicopters, Inc., Model C– 

130B airplanes, TCDS A35NM, Revision 1. 

(viii) Hawkins & Powers Aviation, Inc., 

Model HP–C–130A airplanes, TCDS A30NM, 

Revision 1. 

(ix) Coulson Aviation (USA), Inc., Model 

EC–130Q and C–130H airplanes, TCDS 

T00019LA, Revision 4. 

(x) Lockheed-Georgia Company Model 

282–44A–05 (C–130B) airplanes, TCDS 

A5SO. 

(xi) Surplus Model C–130A airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fatigue cracking of an upper lug of the engine 

truss mount, and by reports of cracks found 

prior to the initial inspection times required 

by AD 96–12–20. The FAA is issuing this AD 

to address such fatigue cracking. Fatigue 

cracking of a single engine truss mount upper 

lug could reduce the static strength of an 

engine mount to limit load, while cracking of 

both lugs can lead to separation of the 

engine, catastrophic structural damage, and 

loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Within 35 days after the effective date of 

this AD, do the inspections specified in 

paragraphs (g)(1) and (2) of this AD, using a 

method approved in accordance with the 

procedures specified in paragraph (i) of this 

AD. If any cracked or severed engine truss 

mount upper lug is found, the engine truss 

mount must be replaced before further flight, 

using a method approved in accordance with 

the procedures specified in paragraph (i) of 

this AD. 

(1) Do a one-time detailed visual 

inspection for cracking of the No. 1 and No. 

4 engine truss mount upper lugs, lower 

surfaces, at outer wing station (OWS) 162 and 

OWS 197; and for severed engine truss 

mount upper lugs; at a total of four locations: 

two locations per engine mount, one mount 

assembly at each OWS. 

(2) Do a one-time borescope inspection for 

cracking of the No. 1 and No. 4 engine truss 

mount upper lug side surfaces, inboard and 

outboard, at OWS 162 and OWS 197; and for 

severed engine truss mount upper lugs; at a 

total of eight locations: two locations per 

engine truss mount lug, two lugs per engine, 

one mount assembly at each OWS. 

Note 1 to paragraph (g): Guidance for 

accomplishing the inspections and 

replacement can be found in Lockheed 

Martin Aeronautics Company Alert Service 

Bulletin A382–57–103, dated October 19, 

2023. 

(h) Special Flight Permit 

Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199 

to operate the airplane to a location where 

the inspections required by this AD can be 

performed, but special flight permits may not 

be issued to operate the airplane after a 

visual or borescope inspection has identified 

a cracked or severed lug, unless the operator 

contacts the Manager, East Certification 

Branch, FAA, for specific limitations that 

must be followed and complies with those 

limitations. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, East 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 responsible Flight 

Standards 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 (j) of this 

AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(j) Related Information 

(1) For more information about this AD, 

contact Fred Caplan, Aviation Safety 

Engineer, FAA, 1701 Columbia Avenue, 

College Park, GA 30337; phone: 404–474– 

5507; email: 9-ASO-ATLACO-ADs@faa.gov. 

(2) For Lockheed Martin Aeronautics 

Company service information identified in 

this AD that is not incorporated by reference, 

contact Lockheed Martin Corporation/ 

Lockheed Martin Aeronautics Company, 

Airworthiness Office, Dept. 6A0M, Zone 

0252, Column P–58, 86 S Cobb Drive, 

Marietta, GA 30063; telephone 770–494– 

5444; fax 770–494–5445; email ams.portal@

lmco.com. You may view this service 

information at the FAA, Airworthiness 

Products Section, Operational Safety Branch, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

(k) Material Incorporated by Reference 

None. 

Issued on November 16, 2023. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2023–25762 Filed 11–17–23; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Bureau of Industry and Security 

15 CFR Part 744 

[Docket No. 231115–0270] 

RIN 0694–AJ45 

Additions to the Entity List 

AGENCY: Bureau of Industry and 

Security, Department of Commerce. 

ACTION: Final rule. 

SUMMARY: In this rule, the Bureau of 

Industry and Security (BIS) amends the 

Export Administration Regulations 

(EAR) by adding four entities under 

nine entries to the Entity List. These 

entities are listed under the destinations 

of Costa Rica (1), Ecuador (1), India (1) 

Panama (2), Spain (1), Russia (1), and 

Venezuela (2). These entities have been 

determined by the U.S. Government to 

be acting contrary to the national 

security or foreign policy interests of the 

United States. Some entities are added 

under multiple entries, accounting for 

the difference in the totals. 

DATES: This rule is effective November 

17, 2023. 

FOR FURTHER INFORMATION CONTACT: 

Chair, End-User Review Committee, 

Office of the Assistant Secretary for 

Export Administration, Bureau of 

Industry and Security, Department of 

Commerce, Phone: (202) 482–5991, 

Email: ERC@bis.doc.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The Entity List (supplement no. 4 to 

part 744 of the EAR (15 CFR parts 730– 

774)) identifies entities for which there 

is reasonable cause to believe, based on 

specific and articulable facts, that the 

entities have been involved, are 

involved, or pose a significant risk of 

being or becoming involved in activities 

contrary to the national security or 

foreign policy interests of the United 

States, pursuant to § 744.11(b). The EAR 

impose additional license requirements 

on, and limit the availability of, most 

license exceptions for exports, 

reexports, and transfers (in-country) 

when a listed entity is a party to the 

transaction. The license review policy 

for each listed entity is identified in the 


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