93152 Federal Register / Vol. 89, No. 228 / Tuesday, November 26, 2024 / Rules and Regulations 

11Bipartisan Campaign Reform Act of 2002, 

Public Law 107–155, sec. 502, 116 Stat. 115 (2002); 

52 U.S.C. 30112(a). 

12See, e.g., 52 U.S.C. 30104(i)(4) (requiring 

Commission to ensure, ‘‘to the greatest extent 

practicable,’’ that certain information is publicly 

available on its website ‘‘in a manner that is 

searchable, sortable, and downloadable’’). 

13Requirement to File FEC Form 3–Z, 89 FR 

62672 (Aug. 1, 2024), https://www.govinfo.gov/ 

content/pkg/FR-2024-08-01/pdf/2024-16843.pdf. 

the Act.11 The posted reports and 

related information can be searched, 

sorted, and downloaded.12

C. Notice of Proposed Rulemaking 

On August 1, 2024, the Commission 

published in the Federal Register a 

notice of proposed rulemaking 

(‘‘NPRM’’) soliciting comments on 

whether it should remove the 

requirement that principal campaign 

committees file Form 3–Z in light of 

statutory changes and technological 

advances.13 The NPRM comment period 

ended on September 3, 2024. The 

Commission received two substantive 

comments in response to the NPRM, 

both in favor of the Commission’s 

proposal. 

II. Revised Changes to 11 CFR 104.3 

After reviewing the public comments 

received in response to the NPRM, the 

Commission is amending § 104.3(f) by 

eliminating the requirement that 

principal campaign committees file FEC 

Form 3–Z. Although FEC Form 3–Z 

served a useful purpose when it was 

introduced more than 40 years ago, the 

information that it provides essentially 

duplicates information that is now filed 

directly with the Commission and 

readily available to the public in a 

searchable, sortable, and downloadable 

format. Accordingly, FEC Form 3–Z has 

been rendered obsolete. 

Certification of No Effect Pursuant to 5 

U.S.C. 605(b) (Regulatory Flexibility 

Act) 

The Commission certifies that the 

amendment will not have a significant 

economic impact on a substantial 

number of small entities. The 

amendment will simplify the reporting 

requirements for a principal campaign 

committee of a candidate with multiple 

authorized committees. The change will 

not impose new recordkeeping, 

reporting, or financial obligations on 

any political committees. The 

Commission therefore certifies that the 

amendment will not have a significant 

economic impact on a substantial 

number of small entities. 

List of Subjects in 11 CFR Part 104 

Campaign funds, Political committees 

and parties, Reporting and 

recordkeeping requirements. 

For the reasons set out in the 

preamble, the Federal Election 

Commission amends 11 CFR part 104 as 

follows: 

PART 104—REPORTS BY POLITICAL 

COMMITTEES AND OTHER PERSONS 

(52 U.S.C. 30104) 

■ 1. The authority citation for part 104 

is revised to read as follows: 

Authority: 52 U.S.C. 30101(1), 30101(8), 

30101(9), 30102(f), (g), and (i), 30104, 

30111(a)(8) and (b), 30114, and 30116 and 36 

U.S.C. 510. 

■ 2. Amend § 104.3 by revising 

paragraph (f) to read as follows: 

§ 104.3 Contents of reports (52 U.S.C. 

30104(b), 30114). 

* * * * * 

(f) Consolidated reports. Each 

principal campaign committee shall 

consolidate in each report those reports 

required to be filed with it. Such 

consolidated reports shall include: 

(1) Reports submitted to it by any 

authorized committees; and 

(2) The principal campaign 

committee’s own reports. 

* * * * * 

Dated: November 19, 2024. 

On behalf of the Commission. 

Sean J. Cooksey, 

Chairman, Federal Election Commission. 

[FR Doc. 2024–27395 Filed 11–25–24; 8:45 am] 

BILLING CODE 6715–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–1888; Project 

Identifier MCAI–2024–00190–T; Amendment 

39–22879; AD 2024–22–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus SAS Model Airbus A350–941 

and –1041 airplanes. This AD was 

prompted by a determination that the 

lower attachment studs on the aft galley 

complex may be installed incorrectly 

due to a missing instruction in the 

maintenance procedure task. This AD 

requires a one-time inspection of the 

lower attachment studs on the aft galley 

complex, and depending on findings, 

accomplishment of applicable corrective 

actions, as specified in a European 

Union Aviation Safety Agency (EASA) 

AD, which is incorporated by reference. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective December 

31, 2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 31, 2024. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–1888; 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, the mandatory 

continuing airworthiness information 

(MCAI), 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. 

Material Incorporated by Reference: 

• For EASA material identified in this 

AD, contact EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; 

telephone +49 221 8999 000; email 

ADs@easa.europa.eu; website 

easa.europa.eu. You may find this 

material on the EASA website at 

ad.easa.europa.eu. 

• You may view this material 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. 

It is also available at regulations.gov 

under Docket No. FAA–2024–1888. 

FOR FURTHER INFORMATION CONTACT: Dat 

Le, Aviation Safety Engineer, FAA, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7300; 

email 9-avs-nyaco-cos@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 Airbus SAS Model 

Airbus A350–941 and –1041 airplanes. 

The NPRM published in the Federal 

Register on July 17, 2024 (89 FR 58081). 

The NPRM was prompted by AD 2024– 

0073, dated March 18, 2024, issued by 

EASA, which is the Technical Agent for 


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Federal Register / Vol. 89, No. 228 / Tuesday, November 26, 2024 / Rules and Regulations 93153 

the Member States of the European 

Union (EASA AD 2024–0073) (also 

referred to as the MCAI). The MCAI 

states that the maintenance procedure 

task of the galley lower attachment stud 

installation did not provide the required 

maximum distance between the top of 

the threaded sleeve and the top of the 

threaded stud, which could lead to a 

wrong installation of the lower 

attachment stud having part number (P/ 

N) XP14–070–007800, P/N XP14–070– 

019100, P/N XP14–070–005400, P/N 

XP14–070–008400, and P/N XP14–070– 

001100 on the aft galley complex. The 

MCAI also states that the affected parts 

are the lower attachment stud having P/ 

N XP14–070–007800, P/N XP14–070– 

019100, P/N XP14–070–005400, P/N 

XP14–070–008400, and P/N XP14–070– 

001100, for which the incomplete 

maintenance procedure task has been 

accomplished after the airplane date of 

manufacture and before January 2024; 

and the lower attachment stud having P/ 

N XP14–070–019100, which has been 

installed after the airplane date of 

manufacture and before January 2024, in 

accordance with the instructions of 

Airbus Alert Operators Transmission 

A25P023–22, Revision 01, dated 

September 27, 2022. 

In the NPRM, the FAA proposed to 

require a one-time inspection of the 

affected lower attachment studs on the 

aft galley complex, and depending on 

findings, accomplishment of applicable 

corrective actions, as specified in EASA 

AD 2024–0073. The FAA is issuing this 

AD to address possible wrong 

installation for the lower attachment 

stud having P/N XP14–070–007800, P/ 

N XP14–070–019100, P/N XP14–070– 

005400, P/N XP14–070–008400, and P/ 

N XP14–070–001100 on the aft galley 

complex. This condition, if not detected 

and corrected, could lead to galley 

module detachment, with possible 

consequent injury to cabin crew and 

passengers, and reduced evacuation 

capacity from the airplane in case of an 

emergency. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2024–1888. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received a comment from an 

individual who supported the NPRM 

without change. 

Conclusion 

This product has been approved by 

the aviation authority of another 

country and is approved for operation in 

the United States. Pursuant to the FAA’s 

bilateral agreement with this State of 

Design Authority, it has notified the 

FAA of the unsafe condition described 

in the MCAI referenced above. The FAA 

reviewed the relevant data, considered 

the comment 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 this product. Except for 

minor editorial changes, this AD is 

adopted as proposed in the NPRM. 

None of the changes will increase the 

economic burden on any operator. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

EASA AD 2024–0073 specifies 

procedures for a one-time installation 

inspection of the lower attachment stud 

having P/N XP14–070–007800, P/N 

XP14–070–019100, P/N XP14–070– 

005400, P/N XP14–070–008400, and P/ 

N XP14–070–001100 on the aft galley 

complex; and depending on findings 

(the distance between the top of the 

threaded sleeves and the top of the 

threaded studs exceeds specified limits), 

accomplishment of applicable corrective 

actions (tightening the applicable 

threaded stud(s)). This material is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

Costs of Compliance 

The FAA estimates that this AD 

affects 32 airplanes of U.S. registry. The 

FAA estimates the following costs to 

comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

Cost on 

U.S. operators 

Up to 3 work-hours × $85 per hour = $255 ..................................................................... $0 Up to $255 .......... Up to $8,160. 

The FAA estimates the following 

costs to do any necessary on-condition 

action that would be required based on 

the results of any required actions. The 

FAA has no way of determining the 

number of airplanes that might need 

this on-condition action: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per 

product 

1 work-hour × $85 per hour = $85 per stud adjustment ......................................................................................... $10 $95 

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 


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93154 Federal Register / Vol. 89, No. 228 / Tuesday, November 26, 2024 / Rules and Regulations 

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: 

2024–22–08 Airbus SAS: Amendment 39– 

22879; Docket No. FAA–2024–1888; 

Project Identifier MCAI–2024–00190–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective December 31, 2024. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus SAS Model 

Airbus A350–941 and –1041 airplanes, 

certificated in any category, as identified in 

European Union Aviation Safety Agency 

(EASA) AD 2024–0073, dated March 18, 2024 

(EASA AD 2024–0073). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/furnishings. 

(e) Unsafe Condition 

This AD was prompted by a determination 

that the lower attachment studs on aft galley 

complex may be installed incorrectly due to 

a missing instruction in the maintenance 

procedure task. The FAA is issuing this AD 

to address a possible wrong installation for 

the lower attachment stud having part 

number (P/N) XP14–070–007800, P/N XP14– 

070–019100, P/N XP14–070–005400, P/N 

XP14–070–008400, and P/N XP14–070– 

001100 on the aft galley complex. This 

condition, if not detected and corrected, 

could lead to galley module detachment, 

with possible consequent injury to cabin 

crew and passengers, and reduced evacuation 

capacity from the airplane in case of an 

emergency. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, EASA AD 2024–0073. 

(h) Exceptions to EASA AD 2024–0073 

(1) Where EASA AD 2024–0073 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) This AD does not adopt the ‘‘Remarks’’ 

section of EASA AD 2024–0073. 

(i) Additional AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Validation Branch, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or 

responsible Flight Standards Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, send it to the person identified in 

paragraph (j) of this AD and email to: 

AMOC@faa.gov. Before using any approved 

AMOC, notify your appropriate principal 

inspector, or lacking a principal inspector, 

the manager of the responsible Flight 

Standards Office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, International Validation 

Branch, FAA; or EASA; or Airbus SAS’s 

EASA Design Organization Approval (DOA). 

If approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (i)(2) of this AD, if 

any material referenced in EASA AD 2024– 

0073 contains paragraphs that are labeled as 

RC, the instructions in RC paragraphs, 

including subparagraphs under an RC 

paragraph, must be done to comply with this 

AD; any paragraphs, including subparagraphs 

under those paragraphs, that are not 

identified as RC are recommended. The 

instructions in paragraphs, including 

subparagraphs under those paragraphs, not 

identified 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 instructions identified 

as RC can be done and the airplane can be 

put back in an airworthy condition. Any 

substitutions or changes to instructions 

identified as RC require approval of an 

AMOC. 

(j) Additional Information 

For more information about this AD, 

contact Dat Le, Aviation Safety Engineer, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone 516–228– 

7300; email 9-avs-nyaco-cos@faa.gov. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the material listed in this paragraph 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use this material as 

applicable to do the actions required by this 

AD, unless this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2024–0073, dated March 18, 

2024. 

(ii) [Reserved] 

(3) For EASA material identified in this 

AD, contact EASA, Konrad-Adenauer-Ufer 3, 

50668 Cologne, Germany; telephone +49 221 

8999 000; email ADs@easa.europa.eu; 

website easa.europa.eu. You may find this 

material on the EASA website at 

ad.easa.europa.eu. 

(4) You may view this material 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. 

(5) You may view this material at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

visit www.archives.gov/federal-register/cfr/ 

ibr-locations or email fr.inspection@nara.gov. 

Issued on October 29, 2024. 

Peter A. White, 

Deputy Director, Integrated Certificate 

Management Division, Aircraft Certification 

Service. 

[FR Doc. 2024–27589 Filed 11–25–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2008; Project 

Identifier AD–2024–00122–T; Amendment 

39–22876; AD 2024–22–05] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 787–8, 787–9, 

and 787–10 airplanes. This AD was 

prompted by a report that during 

manufacture of drag brace lower lock 

link assemblies for the main landing 

gear (MLG), a certain required 


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