Federal Register / Vol. 88, No. 213 / Monday, November 6, 2023 / Proposed Rules 76147 

(4) You may view this service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 2200 South 216th 

Street, 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 30, 2023. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2023–24305 Filed 11–3–23; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–2144; Project 

Identifier MCAI–2023–00898–T] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2018–14–09, which applies to certain 

Airbus SAS Model A318 series 

airplanes; Model A319 series airplanes; 

Model A320–211, –212, –214, –216, 

–231, –232, and –233 airplanes; and 

Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

AD 2018–14–09 requires repetitive 

inspections for cracking of the fastener 

holes in certain fuselage frames, and 

depending on airplane configuration, 

provides an optional terminating action 

to the repetitive inspections. Since the 

FAA issued AD 2018–14–09, it was 

determined that additional actions are 

necessary beyond those required by AD 

2018–14–09. This proposed AD would 

continue to require the actions in AD 

2018–14–09 and would require 

modified compliance times, as well as 

further inspections and optional 

terminating actions for certain airplanes, 

as specified in a European Union 

Aviation Safety Agency (EASA) AD, 

which is proposed for incorporation by 

reference (IBR). The FAA is proposing 

this AD to address the unsafe condition 

on these products. 

DATES: The FAA must receive comments 

on this proposed AD by December 21, 

2023. 

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–2023–2144; 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 NPRM, the mandatory 

continuing airworthiness information 

(MCAI), any comments received, and 

other information. The street address for 

Docket Operations is listed above. 

Material Incorporated by Reference: 

• For the EASA AD identified in this 

NPRM, contact EASA, KonradAdenauer-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. It is also available at 

regulations.gov under Docket No. FAA– 

2023–2144. 

• 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. 

FOR FURTHER INFORMATION CONTACT: 

Timothy Dowling, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; 

telephone 817–222–5102; email 

timothy.p.dowling@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include ‘‘Docket No. 

FAA–2023–2144; Project Identifier 

MCAI–2023–00898–T’’ at the beginning 

of your comments. The most helpful 

comments reference a specific portion of 

the proposal, explain the reason for any 

recommended change, and include 

supporting data. The FAA will consider 

all comments received by the closing 

date and may amend this proposal 

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 NPRM. 

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 NPRM 

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 NPRM, 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 

NPRM. Submissions containing CBI 

should be sent to Timothy Dowling, 

Aviation Safety Engineer, FAA, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 817–222–5102; 

email timothy.p.dowling@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 

The FAA issued AD 2018–14–09, 

Amendment 39–19329 (83 FR 34034, 

July 19, 2018) (AD 2018–14–09), for 

certain Airbus SAS Model A318 series 

airplanes; Model A319 series airplanes; 

Model A320–211, –212, –214, –216, 

–231, –232, and –233 airplanes; and 

Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

AD 2018–14–09 was prompted by an 

MCAI originated by EASA, which is the 

Technical Agent for the Member States 

of the European Union. EASA issued 

AD 2016–0139, dated July 14, 2016, to 

correct an unsafe condition. 

AD 2018–14–09 requires repetitive 

inspections for cracking of the fastener 

holes in certain fuselage frames, and 

depending on airplane configuration, 

provides an optional terminating action 

to the repetitive inspections. The FAA 


ddrumheller on DSK120RN23PROD with PROPOSALS1
76148 Federal Register / Vol. 88, No. 213 / Monday, November 6, 2023 / Proposed Rules 

issued AD 2018–14–09 to address 

cracking at two upper rows of fasteners 

of the crossbeam splicing at frame 

(FR)16 and FR20, on both the left-hand 

(LH) and right-hand (RH) sides, which 

can result in reduced structural integrity 

of the airplane due to the failure of 

structural components. 

Actions Since AD 2018–14–09 Was 

Issued 

Since the FAA issued AD 2018–14– 

09, EASA superseded AD 2016–0139, 

dated July 14, 2016, and issued EASA 

AD 2023–0150, dated July 20, 2023 

(EASA AD 2023–0150) (also referred to 

as the MCAI), to correct an unsafe 

condition for Airbus SAS A318–111, 

A318–112, A318–121, A318–122, A319– 

111, A319–112, A319–113, A319–114, 

A319–115, A319–131, A319–132, A319– 

133, A320–211, A320–212, A320–214, 

A320–215, A320–216, A320–231, A320– 

232, A320–233, A321–111, A321–112, 

A321–131, A321–211, A321–212, A321– 

213, A321–231 and A321–232 airplanes, 

all manufacturer serial numbers, except 

airplanes on which Airbus modification 

(mod) 161255 was embodied in 

production, Model A318 airplanes on 

which Airbus mod 39195 was embodied 

in production, or Airbus Service 

Bulletin A320–00–1219 was embodied 

in service; and Model A319 airplanes on 

which Airbus mod 28238, mod 28162, 

and mod 28342 were embodied in 

production. Model A320–215 airplanes 

are not certificated by the FAA and are 

not included on the U.S. type certificate 

data sheet; this proposed AD therefore 

does not include those airplanes in the 

applicability. The MCAI states that 

repetitive inspections were instituted 

due to reports of cracks on the four 

holes of the crossbeam splicing at FR16 

and FR20 on both LH and RH sides. 

Following further assessments, the need 

was determined for additional 

inspections, reduced compliance times, 

and an additional terminating action 

option. 

For the reasons described above, this 

proposed AD retains the requirements of 

AD 2018–14–09 (which corresponds to 

EASA AD 2016–0139), introduces new 

compliance times for airplanes that 

embody Airbus mod 20416 or mod 

21999, expands the inspection area for 

airplanes that embody neither Airbus 

mod 20416 nor mod 21999, and adds a 

terminating action option. 

The FAA is proposing this AD to 

address cracking at two upper rows of 

fasteners of the crossbeam splicing at 

FR16 and FR20, on both the LH and RH 

sides, which can result in reduced 

structural integrity of the airplane due 

to the failure of structural components. 

You may examine the MCAI in the AD 

docket at regulations.gov under Docket 

No. FAA–2023–2144. 

Explanation of Retained Requirements 

Although this proposed AD does not 

explicitly restate the requirements of AD 

2018–14–09, this proposed AD would 

retain all of the requirements of AD 

2018–14–09. Those requirements are 

referenced in EASA AD 2023–0150, 

which, in turn, is referenced in 

paragraph (g) of this proposed AD. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2023–0150 specifies 

procedures for repetitive rototest 

inspections for cracking of the holes in 

certain fuselage frames and crossbeams 

and applicable corrective actions 

(including repairing cracking and 

replacing fasteners); and, for certain 

airplanes, procedures for modifying the 

airplane, including cold working 

instructions in certain fuselage frames 

and crossbeams, which would terminate 

the inspections (optional terminating 

action). 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. 

FAA’s Determination 

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 

is issuing this NPRM after determining 

that the unsafe condition described 

previously is likely to exist or develop 

in other products of the same type 

design. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would retain all 

requirements of AD 2018–14–09. This 

proposed AD would require 

accomplishing the actions specified in 

EASA AD 2023–0150 described 

previously, except for any differences 

identified as exceptions in the 

regulatory text of this proposed AD and 

except as discussed under ‘‘Differences 

Between this Proposed AD and the 

MCAI.’’ 

Explanation of Required Compliance 

Information 

In the FAA’s ongoing efforts to 

improve the efficiency of the AD 

process, the FAA developed a process to 

use some civil aviation authority (CAA) 

ADs as the primary source of 

information for compliance with 

requirements for corresponding FAA 

ADs. The FAA has been coordinating 

this process with manufacturers and 

CAAs. As a result, the FAA proposes to 

incorporate EASA AD 2023–0150 by 

reference in the FAA final rule. This 

proposed AD would, therefore, require 

compliance with EASA AD 2023–0150 

in its entirety through that 

incorporation, except for any differences 

identified as exceptions in the 

regulatory text of this proposed AD. 

Using common terms that are the same 

as the heading of a particular section in 

EASA AD 2023–0150 does not mean 

that operators need comply only with 

that section. For example, where the AD 

requirement refers to ‘‘all required 

actions and compliance times,’’ 

compliance with this AD requirement is 

not limited to the section titled 

‘‘Required Action(s) and Compliance 

Time(s)’’ in EASA AD 2023–0150. 

Service information required by EASA 

AD 2023–0150 for compliance will be 

available at regulations.gov under 

Docket No. FAA–2023–2144 after the 

FAA final rule is published. 

Differences Between This Proposed AD 

and the MCAI 

Although the applicability of EASA 

AD 2023–0150 references Airbus 

Service Bulletin A320–00–1219, the 

FAA contacted Airbus and learned that 

the referenced service information has 

not been published. Therefore, this 

proposed AD does not include that 

service information in the applicability. 

Where the service information 

referenced in paragraphs (8) and (9) of 

EASA AD 2023–0150, i.e., ‘‘Airbus SB 

A320–53–1295,’’ refers to actions when 

an existing hole diameter is ‘‘more than 

or equal to the minimum starting hole 

diameter,’’ paragraph (h)(6) of this 

proposed AD specifies to replace those 

words with ‘‘more than or equal to the 

maximum starting hole diameter.’’ In 

Airbus Operators Information Telex 

(OIT) 15–0097, Revision 01, dated 

January 7, 2016, Airbus confirmed that 

the corrective action in Airbus Service 

Bulletin A320–53–1295 that refers to 

‘‘more than or equal to the minimum 

starting hole diameter’’ should be ‘‘more 

than or equal to the maximum starting 

hole diameter.’’ As explained in the 

‘‘Request to Include Corrections to 

Service Information’’ paragraph in AD 

2018–14–09, Airbus released OIT 15– 

0097, Revision 01, dated January 7, 

2016, to correct discrepancies in Airbus 

Service Bulletin A320–53–1295, which 

is referred to paragraphs (k) and (m) of 

AD 2018–14–09. The FAA added 

paragraph (r) to AD 2018–14–09 to 

address the diameter hole discrepancy. 


ddrumheller on DSK120RN23PROD with PROPOSALS1
Federal Register / Vol. 88, No. 213 / Monday, November 6, 2023 / Proposed Rules 76149 

Paragraphs (k) and (m) of AD 2018–14– 

09 correspond to paragraphs (8) and (9) 

of EASA AD 2023–0150. Paragraph (r) of 

AD 2018–14–09 corresponds to 

paragraph (h)(6) of this proposed AD. 

Where rows B and C of the 

‘‘Threshold’’ column in Table 1 of 

EASA AD 2023–0150 refer to ‘‘54 800 

FH,’’ for this proposed AD, those words 

should be replaced with ‘‘54 900 FH’’ 

because the existing flight-hour interval 

specified in Table 1 of AD 2018–14–09 

is 54,900 flight hours. Once the initial 

inspection is done within the 

‘‘Threshold’’ compliance times in Table 

1 of EASA AD 2023–0150, the new 

repetitive flight-hour interval will be 

54,800 flight hours (flight-hour 

component only; the complete new 

interval is 27,400 flight cycles or 54,800 

flight hours, whichever occurs first). 

The FAA has included this exception in 

paragraph (h)(3) of the proposed AD. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 1,680 

airplanes of U.S. registry. The FAA 

estimates the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Retained actions from AD 2018–14–09 31 work-hours × $85 per hour = $2,635 $0 $2,635 $4,426,800 

ESTIMATED COSTS FOR OPTIONAL ACTIONS

Labor cost Parts cost Cost per product 

28 work-hours × $85 per hour = $2,380 ..................................................................................................... $3,020 $5,400 

The FAA estimates the following 

costs to do any necessary on-condition 

actions that would be required based on 

the results of any required or optional 

actions. The FAA has no way of 

determining the number of aircraft that 

might need this on-condition action: 

ESTIMATED COSTS OF ON-CONDITION REPLACEMENTS

Labor cost Parts cost Cost per product 

14 work-hours × $85 per hour = $1,190 ..................................................................................................... $50 $1,240 

The FAA has received no definitive 

data that would enable us to provide 

cost estimates for the on-condition 

repairs specified in this proposed 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 

The FAA determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Would not affect intrastate 

aviation in Alaska, and 

(3) Would 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 Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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) 2018–14–09, Amendment 39– 

19329 (83 FR 34034, July 19, 2018); and 

■ b. Adding the following new AD: 

Airbus SAS: Docket No. FAA–2023–2144; 

Project Identifier MCAI–2023–00898–T. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by December 21, 

2023. 

(b) Affected ADs 

This AD replaces AD 2018–14–09, 

Amendment 39–19329 (83 FR 34034, July 19, 

2018) (AD 2018–14–09). 

(c) Applicability 

This AD applies to Airbus SAS Model 

A318–111, –112, –121, and –122 airplanes; 

Model A319–111, –112, –113, –114, –115, 

–131, –132, and –133 airplanes; Model 

A320–211, –212, –214, –216, –231, –232, and 

–233 airplanes; and Model A321–111, –112, 

–131, –211, –212, –213, –231, and –232 

airplanes; certificated in any category, all 


ddrumheller on DSK120RN23PROD with PROPOSALS1
76150 Federal Register / Vol. 88, No. 213 / Monday, November 6, 2023 / Proposed Rules 

manufacturer serial numbers, except the 

airplanes specified in paragraphs (c)(1) 

through (3) of this AD. 

(1) Airplanes on which Airbus 

modification 161255 has been embodied in 

production. 

(2) Model A319 series airplanes on which 

Airbus modifications 28238, 28162, and 

28342 have been concurrently embodied in 

production. 

(3) Model A318 series airplanes on which 

Airbus modification 39195 has been 

embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of early 

cracking on the four holes of the crossbeam 

splicing at certain fuselage frames (FR). The 

FAA is issuing this AD to address cracking 

at two upper rows of fasteners of the 

crossbeam splicing at FR16 and FR20, on 

both the left-hand (LH) and right-hand (RH) 

sides. The unsafe condition, if not addressed, 

could result in reduced structural integrity of 

the airplane due to the failure of structural 

components. 

(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, European Union Aviation 

Safety Agency (EASA) AD 2023–0150, dated 

July 20, 2023 (EASA AD 2023–0150). 

(h) Exceptions to EASA AD 2023–0150 

(1) Where EASA AD 2023–0150 refers to 

‘‘28 July 2016 [the effective date of EASA AD 

2016–0139],’’ this AD requires using August 

23, 2018 (the effective date of AD 2018–14– 

09). 

(2) Where EASA AD 2023–0150 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(3) Where rows B and C of the ‘‘Threshold’’ 

column in Table 1 of EASA AD 2023–0150 

refer to ‘‘54 800 FH,’’ for this AD, replace 

those words with ‘‘54 900 FH.’’ 

(4) Where paragraph (5) of EASA AD 2023– 

0150 refers to ‘‘valid within the EASA 

system,’’ for this AD, replace those words 

with ‘‘approved by the FAA, EASA, Airbus’s 

EASA Design Organization Approval (DOA), 

or an EASA DOA (other than Airbus’s EASA 

DOA).’’ 

(5) Where paragraph (5) of EASA AD 2023– 

0150 specifies ‘‘contact that design approval 

holder (DAH) for assessment and repair 

instructions, obtain EASA AMOC approval 

and accomplish those instructions 

accordingly, as applicable,’’ for this AD, 

replace those words with ‘‘modify the repair 

using a method approved by the Manager, 

International Validation Branch, FAA; or 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature.’’ 

(6) Where the service information 

referenced in paragraphs (8) and (9) of EASA 

AD 2023–0150 refers to actions when an 

existing hole diameter is ‘‘more than or equal 

to the minimum starting hole diameter,’’ for 

this AD, replace those words with ‘‘more 

than or equal to the maximum starting hole 

diameter.’’ 

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

section of EASA AD 2023–0150. 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2023–0150 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) 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 International Validation Branch, send 

it to the attention of the person identified in 

paragraph (k) of this AD. Information may be 

emailed to: 9-AVS-AIR-730-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 paragraphs (i) and (j)(2) of this 

AD, if any service information contains 

procedures or tests that are identified as RC, 

those procedures and tests must be done to 

comply with this AD; any procedures or tests 

that are not identified as RC are 

recommended. Those procedures and tests 

that are 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 

procedures and tests identified as RC can be 

done and the airplane can be put back in an 

airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(k) Additional Information 

For more information about this AD, 

contact Timothy Dowling, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone 817– 

222–5102; email timothy.p.dowling@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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2023–0150, dated July 20, 2023. 

(ii) [Reserved] 

(3) For EASA AD 2023–0150, 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 EASA AD 

on the EASA website at ad.easa.europa.eu. 

(4) 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. 

(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. 

Dated: Issued on October 30, 2023. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2023–24300 Filed 11–3–23; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2023–2115; Airspace 

Docket No. 23–ASO–40] 

RIN 2120–AA66 

Amendment of Class E Airspace; 

Natchez, MS 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

amend the Class E airspace at Natchez, 

MS. The FAA is proposing this action 

as the result of an airspace review 

conducted due to the decommissioning 

of the Natchez very high frequency 

omnidirectional range (VOR) as part of 

the VOR Minimum Operating Network 

(MON) Program. The name and 

geographic coordinates of the airport 

would also be updated to coincide with 

the FAA’s aeronautical database. This 

action will bring the airspace into 

compliance with FAA orders to support 

instrument flight rule (IFR) operations. 

DATES: Comments must be received on 

or before December 21, 2023. 

ADDRESSES: Send comments identified 

by FAA Docket No. FAA–2023–2115 


ddrumheller on DSK120RN23PROD with PROPOSALS1