This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

102016 

Vol. 89, No. 242 

Tuesday, December 17, 2024 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2661; Project 

Identifier MCAI–2024–00269–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) 

2015–02–14, which applies to all Airbus 

SAS Model A318 series airplanes; 

A319–111, –112, –113, –114, –115, 

–131, –132, and –133 airplanes; A320– 

211, –212, –214, –231, –232, and –233 

airplanes; and A321–111, –112, –131, 

–211, –212, –213, –231, and –232 

airplanes. AD 2015–02–14 requires 

repetitive inspections for cracking, 

damage, correct installation, and correct 

adjustment of the main landing gear 

(MLG) door hinge and actuator fittings 

on the keel beam, corrective actions if 

necessary, and revision of the existing 

maintenance or inspection program, as 

applicable. Since the FAA issued AD 

2015–02–14, a new design of the MLG 

door keel beam hinge and actuator 

fitting was developed. This proposed 

AD would continue to require the 

actions specified in AD 2015–02–14, 

add an optional terminating action, and 

revise the applicability, 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 January 31, 

2025. 

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–2024–2661; 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 EASA material identified in this 

proposed AD, 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. 

• 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: Tim 

Dowling, Aviation Safety Engineer, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone 206– 

231–3667; 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 the ADDRESSES section. Include 

‘‘Docket No. FAA–2024–2661; Project 

Identifier MCAI–2024–00269–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 the 

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 Tim Dowling, 

Aviation Safety Engineer, FAA, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 206–231–3667; 

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 2015–02–14, 

Amendment 39–18081 (80 FR 11096, 

March 2, 2015) (AD 2015–02–14), for all 

Airbus SAS Model A318 series 

airplanes; A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes; 

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

–233 airplanes; and A321–111, –112, 

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

series airplanes. AD 2015–02–14 was 

prompted by MCAI originated by the 

European Union Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union. EASA issued AD 2012–0118, 

dated July 4, 2012 (EASA AD 2012– 

0118) (which corresponds to FAA AD 


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2015–02–14), to correct an unsafe 

condition. 

AD 2015–02–14 requires repetitive 

inspections for cracking, damage, 

correct installation, and correct 

adjustment of the main landing gear 

(MLG) door hinge and actuator fittings 

on the keel beam; corrective actions if 

necessary; and revision of the existing 

maintenance or inspection program, as 

applicable. The FAA issued AD 2015– 

02–14 to detect and correct cracking on 

the MLG door hinge fitting and actuator 

fitting on the keel beam, which could 

lead to in-flight detachment of an MLG 

door, possibly resulting in injury to 

persons on the ground and/or damage to 

the airplane. 

Actions Since AD 2015–02–14 Was 

Issued 

Since the FAA issued AD 2015–02– 

14, EASA superseded AD 2012–0118, 

dated July 4, 2012, and issued EASA AD 

2024–0097R2, dated July 12, 2024 

(EASA AD 2024–0097R2) (referred to 

after this as the MCAI) to correct an 

unsafe condition on certain Airbus SAS 

Model A318–111, –112, –121, –122 

airplanes; Model A319–111, –112, –113, 

–114, –115, –131, –132, –133, –151N, 

–153N, and –171N airplanes; Model 

A320–211, –212, –214, –215, –216, 

–231, –232, –233, –251N, –252N, 

–253N, –271N, –272N, and –273N 

airplanes; and Model A321–111, –112, 

–131, –211, –212, –213, –231, –232, 

–251N, –251NX, –252N, –252NX, 

–253N, –253NX, –271N, –271NX, 

–272N, and –272NX airplanes. 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 Airbus SAS 

Model A318–111, A318–112, A318–121, 

A318–122; Model A319–111, A319–112, 

A319–113, A319–114, A319–115, A319– 

131, A319–132, A319–133; Model 

A320–211, A320–212, A320–214, A320– 

215, A320–216, A320–231, A320–232, 

A320–233; Model A321–111, A321–112, 

A321–131, A321–211, A321–212, A321– 

213, A321–231, and A321–232 airplanes 

are commercially known as current 

engine option (CEO) airplanes. 

The MCAI states that Airbus SAS 

Model A319–151N, A319–153N, A319– 

171N; Model A320–251N, A320–252N, 

A320–253N, A320–271N, A320–272N, 

A320–273N; Model A321–251N, A321– 

251NX, A321–252N, A321–252NX, 

A321–253N, A321–253NX, A321–271N, 

A321–271NX, A321–272N, and A321– 

272NX airplanes are commercially 

known as new engine option (NEO) 

airplanes. 

The MCAI states that after EASA AD 

2012–0118 was issued, a new design of 

the MLG door keel beam hinge and 

actuator fitting was certified for inservice embodiment through Airbus 

mod 165315 for CEO airplanes. The 

MCAI states that the applicability is 

expanded to include the NEO airplanes, 

which are subject to the same unsafe 

condition. 

The FAA is proposing this AD to 

detect and correct cracking on the MLG 

door hinge fitting and actuator fitting on 

the keel beam, which could lead to inflight detachment of an MLG door, 

possibly resulting in injury to persons 

on the ground and/or damage to the 

airplane. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2024–2661. 

Explanation of Retained Requirements 

Although this proposed AD does not 

explicitly restate the requirements of AD 

2015–02–14, this proposed AD would 

retain all the requirements of AD 2015– 

02–14. Those requirements are 

referenced in EASA AD 2024–0097R2, 

which, in turn, is referenced in 

paragraph (g) of this proposed AD. 

Paragraph (i) of this proposed AD does 

restate the requirement of paragraph (k) 

of AD 2015–02–14, as EASA AD 2024– 

0097R2 only cancels Task 533154–02–1 

of the Airbus A318/A319/A320/A321 

ALS Part 2-Damage Tolerant 

Airworthiness Limitations Items (DT 

ALI), Revision 01, dated April 4, 2012; 

Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/96, 

Issue 10, dated October 2009; or Airbus 

A318/A319/A320/A321 Airworthiness 

Limitation Items, Document AI/SE–M4/ 

95A.0252/96, Issue 11, dated September 

2010. However, it does not require 

removal from the maintenance or 

inspection program for certain 

airplanes. This proposed AD would 

require removal of this task. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

EASA AD 2024–0097R2 specifies 

procedures for repetitive detailed visual, 

high frequency eddy current (HFEC), 

and ultrasonic inspections of the MLG 

door actuator fittings on the keel beam. 

Corrective actions include replacement 

of the affected MLG door actuator 

fitting, and repair of the bush migration, 

the wear marks underneath bolt head, 

and other damages on left and right 

sides of the airplane. 

EASA AD 2024–0097R2 specifies 

procedures for repetitive detailed visual 

and HFEC inspections of the MLG door 

hinge fittings on the keel beam. 

Corrective actions include replacement 

of the MLG door hinge fitting, and 

repair of the bush migration, wear marks 

underneath bolt head, and other 

damages left and right sides of the 

airplane. 

EASA AD 2024–0097R2 also specifies 

procedures for modifying the actuator 

and hinge fittings at the MLG door for 

the following parts: MLG actuator 

fittings, hinge fittings, and connecting 

plates between Frame (FR) 42 and FR 

43; accomplishment of this modification 

terminates the repetitive inspections. 

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 and material referenced 

above. The FAA is issuing this NPRM 

after determining that the unsafe 

condition described previously is likely 

to exist or develop on other products of 

the same type design. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would retain all 

requirements of AD 2015–02–14, add an 

optional terminating action, and revise 

the applicability by adding NEO 

airplanes and removing airplanes with a 

certain modification. This proposed AD 

would also require accomplishing the 

actions specified in the material 

described previously. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 1,766 

airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this proposed AD: 


ddrumheller on DSK120RN23PROD with PROPOSALS1
102018 Federal Register / Vol. 89, No. 242 / Tuesday, December 17, 2024 / Proposed Rules 

ESTIMATED COSTS FOR REQUIRED ACTIONS

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

Inspections .................... 20 work-hours × $85 per hour = $1,700, per inspection cycle.$0 $1,700, per inspection 

cycle.

$3,002,200, per inspection cycle. 

ESTIMATED COSTS FOR OPTIONAL ACTIONS

Action Labor cost Parts cost Cost per 

product 

Modify the actuator and hinge fittings at MLG door .... 82 work-hours × $85 per hour = $6,970 ...................... $52,000 $58,970 

The FAA estimates the following 

costs to do any fitting replacement that 

would be required based on the results 

of any required actions. The FAA has no 

way of determining the number of 

aircraft that might need a fitting 

replacement: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per 

product 

38 work-hours × $85 per hour = $3,230 ................................................................................................................. $6,742 $9,972 

The FAA has received no definitive 

data on which to base the cost estimates 

for the repairs specified in this proposed 

AD. 

According to the manufacturer, some 

or all of the costs of this proposed AD 

may be covered under warranty, thereby 

reducing the cost impact on affected 

individuals. The FAA does not control 

warranty coverage for affected 

individuals. As a result, the FAA has 

included all known costs in the cost 

estimate. 

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) 2015–02–14, Amendment 39– 

18081 (80 FR 11096, March 2, 2015); 

and 

■ b. Adding the following new AD: 

Airbus SAS: Docket No. FAA–2024–2661; 

Project Identifier MCAI–2024–00269–T. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by January 31, 

2025. 

(b) Affected ADs 

This AD replaces AD 2015–02–14, 

Amendment 39–18081 (80 FR 11096, March 

2, 2015) (AD 2015–02–14). 

(c) Applicability 

This AD applies to the Airbus SAS 

airplanes identified in paragraphs (c)(1) 

through (4) of this AD, certificated in any 

category, as identified in European Union 

Aviation Safety Agency (EASA) AD 2024– 

0097R2, dated July 12, 2024 (EASA AD 

2024–0097R2). 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A319–151N, –153N, and –171N 

airplanes. 

(4) Model A320–211, –212, –214, –216, 

–231, –232, and –233 airplanes. 

(5) Model A320–251N, –252N, –253N, 

–271N, –272N, and –273N airplanes. 

(6) Model A321–111, –112, –131, –211, 

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

(7) Model A321–251N, –251NX, –252N, 

–252NX, –253N, –253NX, –271N, –271NX, 

–272N, and –272NX airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

on the main landing gear (MLG) door hinge 


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Federal Register / Vol. 89, No. 242 / Tuesday, December 17, 2024 / Proposed Rules 102019 

fitting and actuator fitting on the keel beam. 

The FAA is issuing this AD to detect and 

correct cracking on the MLG door hinge 

fitting and actuator fitting on the keel beam. 

The unsafe condition, if not addressed, could 

lead to in-flight detachment of an MLG door, 

possibly resulting in injury to persons on the 

ground and/or damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraphs (h) and 

(j) of this AD: Comply with all required 

actions and compliance times specified in, 

and in accordance with, EASA AD 2024– 

0097R2. 

(h) Exceptions to EASA AD 2024–0097R2 

(1) Where EASA AD 2024–0097R2 refers to 

‘‘16 May 2024 [the effective date of the 

original issue of this AD],’’ this AD requires 

using the effective date of this AD. 

(2) Where EASA AD 2024–0097R2 refers to 

‘‘18 July 2012 [the effective date of EASA AD 

2012–0118],’’ this AD requires using April 6, 

2015 (the effective date of AD 2015–02–14). 

(3) Where EASA AD 2024–0097R2 

specifies to ‘‘contact Airbus for approved 

repair instructions and, within the 

compliance time specified therein, 

accomplish those instructions accordingly,’’ 

replace that text with ‘‘all repairs must be 

done before further flight using a method 

approved by the Manager, International 

Validation Branch, FAA; or the European 

Union Aviation Safety Agency (EASA); or 

SAS’s EASA Design Organization Approval 

(DOA). If approved by the DOA, the approval 

must include the DOA-authorized signature.’’ 

(4) Where paragraph (6) of EASA AD 2024– 

0097R2 describes an airplane that has been 

inspected per ‘‘ALI task 533154–03–2, 

533154–04–2 or 533154–10–1, or in 

accordance with the instructions of 

inspection SB 1 (at any Revision) or 

inspection SB 2 (at any Revision),’’ replace 

that text with ‘‘ALI task 533154–03–2, 

533154–04–2 or 533154–10–1, or in 

accordance with the instructions of Airbus 

SB A320–53–1195 or SB A320–53–1325 at 

any Revision, as applicable, or Airbus SB 

A320–53–1196 or SB A320–53–1326 at any 

Revision, as applicable.’’ 

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

section of EASA AD 2024–0097R2. 

(i) Retained Maintenance or Inspection 

Program Revision, With Added Airplanes 

and Compliance Time 

This paragraph restates the requirements of 

paragraph (k) of AD 2015–02–14 with added 

airplanes and compliance time. At the 

applicable time specified in paragraph (i)(1) 

or (2) of this AD: Revise the maintenance or 

inspection program, as applicable, to remove 

Task 533154–02–1 of the Airbus A318/A319/ 

A320/A321 ALS Part 2-Damage Tolerant 

Airworthiness Limitations Items (DT ALI), 

Revision 01, dated April 4, 2012; Airbus 

A318/A319/A320/A321 Airworthiness 

Limitation Items, Document AI/SE–M4/ 

95A.0252/96, Issue 10, dated October 2009; 

or Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 11, dated 

September 2010. The actions required by this 

AD take precedence over Task 533154–02–1 

of the Airbus A318/A319/A320/A321 ALS 

Part 2-Damage Tolerant Airworthiness 

Limitation Items (DT ALI), Revision 01, dated 

April 4, 2012; Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 10, dated 

October 2009; and Airbus A318/A319/A320/ 

A321 Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/96, Issue 11, 

dated September 2010. 

(1) For airplanes identified in paragraphs 

(c)(1), (2), (4), and (6) of this AD: After the 

effective date of AD 2015–02–14 and before 

further flight after doing the initial 

inspections required by paragraph (g) of this 

AD. 

(2) For airplanes identified in paragraphs 

(c)(3), (5), and (7) of this AD: After the 

effective date of this AD and before further 

flight after doing the initial inspections 

required by paragraph (g) of this AD. 

(j) No Reporting Requirement 

Although the material referenced in EASA 

AD 2024–0097R2 specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

(k) Additional AD Provisions 

(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 attention of the person 

identified in paragraph (l) of this AD and 

email to: AMOC@faa.gov. 

(i) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(ii) AMOCs approved previously for AD 

2015–02–14 are approved as AMOCs for the 

corresponding provisions of EASA AD 2012– 

0118 that are required by paragraph (g) of this 

AD. 

(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 the European Union 

Aviation Safety Agency (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 (k)(2) of this AD, if 

any material 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. 

(l) Additional Information 

For more information about this AD, 

contact Tim Dowling, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone 206– 

231–3667; email: timothy.p.dowling@faa.gov. 

(m) 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. 

(3) The following material was approved 

for IBR on [DATE 35 DAYS AFTER 

PUBLICATION OF THE FINAL RULE]. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2024–0097R2, dated July 12, 

2024. 

(ii) [Reserved] 

(4) For EASA AD 2024–0097R2 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. 

(5) 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. 

(6) 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 December 11, 2024. 

Suzanne Masterson, 

Deputy Director, Integrated Certificate 

Management Division, Aircraft Certification 

Service. 

[FR Doc. 2024–29620 Filed 12–16–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2662; Project 

Identifier MCAI–2024–00448–T] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 


ddrumheller on DSK120RN23PROD with PROPOSALS1