Federal Register / Vol. 90, No. 29 / Thursday, February 13, 2025 / Proposed Rules 9523 

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, AIR–520, Continued 

Operational Safety Branch, FAA; or EASA; or 

Airbus SAS’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (i)(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. 

(j) Additional Information 

For more information about this AD, 

contact Dan Rodina, Aviation Safety 

Engineer, FAA, 2200 South 216th St., Des 

Moines, WA 98198; telephone 206–231– 

3225; email dan.rodina@faa.gov. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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 2024–0200, dated October 21, 

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 February 6, 2025. 

John P. Piccola, Jr., 

Director, Integrated Certificate Management 

Division, Aircraft Certification Service. 

[FR Doc. 2025–02506 Filed 2–12–25; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–1702; Project 

Identifier MCAI–2024–00067–T] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (SNPRM). 

SUMMARY: The FAA is revising a notice 

of proposed rulemaking (NPRM) to 

supersede Airworthiness Directive (AD) 

2021–25–14, which applies to all Airbus 

SAS 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. 

This action revises the NPRM by adding 

a prohibition against accomplishing a 

repair using certain structural repair 

manual (SRM) tasks. The FAA is 

proposing this AD to address the unsafe 

condition on these products. Since these 

actions would impose an additional 

burden over those in the NPRM, the 

FAA is requesting comments on this 

SNPRM. 

DATES: The FAA must receive comments 

on this SNPRM by March 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–2024–1702; or in person at 

Docket Operations between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains the NPRM, this SNPRM, 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 European Union Aviation 

Safety Agency (EASA) material 

identified in this SNPRM, 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. It is also available at 

regulations.gov under Docket No. FAA– 

2024–1702. 

• 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, 2200 South 216th St., 

Des Moines, WA 98198; phone: 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 the ADDRESSES section. Include 

‘‘Docket No. FAA–2024–1702; Project 

Identifier MCAI–2024–00067–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 SNPRM. 

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 SNPRM 

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 SNPRM, it is 

important that you clearly designate the 


ddrumheller on DSK120RN23PROD with PROPOSALS1
9524 Federal Register / Vol. 90, No. 29 / Thursday, February 13, 2025 / Proposed Rules 

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 SNPRM. Submissions containing 

CBI should be sent to Timothy Dowling, 

Aviation Safety Engineer, FAA, 2200 

South 216th St., Des Moines, WA 98198; 

phone: 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 an NPRM to amend 

14 CFR part 39 by adding an AD to 

supersede AD 2021–25–14, Amendment 

39–21858 (86 FR 72171, December 21, 

2021) (AD 2021–25–14), that would 

apply to all Airbus SAS Model A319– 

111, –112, –113, –114, –115, –131, –132, 

–133, 151N, –153N, and –171N 

airplanes; Model A320–211, –212, –214, 

–216, –231, –232, –233, –251N, –252N, 

–253N, –271N, –272N, and –273N 

airplanes; and Model A321–211, –212, 

–213, –231, –232, –251N, –251NX, 

–252N, –252NX, –253N, –253NX, 

–271N, –271NX, –272N, and –272NX 

airplanes. The NPRM published in the 

Federal Register on July 3, 2024 (89 FR 

55123). The NPRM was prompted by 

AD 2024–0027, dated January 25, 2024 

(EASA AD 2024–0027), issued by 

EASA, which is the Technical Agent for 

the Member States of the European 

Union. EASA AD 2024–0027 stated new 

investigation results highlighted that 

inspections must be applied to all 

models of A319, A320 and A321 

airplanes in an affected configuration, 

and the associated compliance time 

must be adapted to these configurations. 

It was determined that fatigue cracking 

may occur in affected areas on airplanes 

having Sharklets installed during 

production or in service. This condition, 

if not detected and corrected, could lead 

to crack initiation and propagation, 

possibly resulting in reduced structural 

integrity of the wings. 

In the NPRM, the FAA proposed to 

continue to require the actions in AD 

2021–25–14 and to require expanding 

the applicability to include new engine 

option (NEO) airplanes and 

accomplishment of the required actions 

within updated compliance times, as 

applicable to airplane configuration. 

Actions Since the NPRM Was Issued 

Since the FAA issued the NPRM, 

EASA superseded EASA AD 2024–0027 

and issued EASA AD 2024–0230, dated 

December 2, 2024 (EASA AD 2024– 

0230) (also referred to as the MCAI), to 

correct an unsafe condition for all 

Airbus SAS 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 A321–211, –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 

since AD 2024–0027 was issued, it was 

identified that Airbus published certain 

SRM tasks at revision dated May 2024, 

removing instructions linked to steps 2 

to 9 and aligning the compliance time 

with the EASA AD 2024–0027 for all the 

related SRM tasks. In addition, SRM 

tasks 57–21–11–300–010, 57–21–11– 

300–021 and 57–21–11–300–025 were 

deactivated at revision dated August 

2023, and should no longer be used. 

The FAA is proposing this AD to 

address the unsafe condition on these 

products. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2024–1702. 

Comments 

The FAA received a comment from 

Air Line Pilots Association, 

International (ALPA) who supported the 

NPRM without change. 

The FAA received additional 

comments from Delta Air Lines (Delta). 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Add Exceptions 

Delta requested the inclusion of an 

exception in paragraph (h) of the final 

rule to correct the meaning of ‘‘Steps 2 

to 9’’ as stated in paragraph (5) of EASA 

AD 2024–0027. Delta stated the meaning 

of ‘‘Steps 2 to 9’’ in paragraph (5) is not 

readily evident due to a conflict 

between the note included in paragraph 

(5) of EASA AD 2024–0027 and later 

revisions of Airbus A319–A320–A321 

SRM, which has had the bushing 

oversize step numbering deleted from 

the referenced SRM repair. 

Delta also requested the inclusion of 

an exception paragraph in the final rule 

of allowing operators with A321–200 

(CEO [current engine option]) aircraft 

and A321–200 (NEO ACF [advanced 

cabin flex]) aircraft, as defined in 

Appendix 1, Table 1 and Table 2 of 

EASA AD 2024–0027, to omit the 

requirements to accomplish certain 

post-repair inspections at the 

compliance times specified in paragraph 

(6) of EASA AD 2024–0027, rather than 

those in the SRM. Delta stated Airbus 

adjusted the thresholds and intervals for 

post-repair inspections to match the 

compliance times specified in paragraph 

(6) of EASA AD 2024–0027 in the recent 

SRM Revision 27, SRM Task 57–21–11– 

300–009. 

Delta also requested the inclusion of 

an exception in paragraph (h) of the 

final rule to clarify and correct the 

meaning of ‘‘Step 1’’ in paragraph (7) of 

EASA AD 2024–0027. Delta stated that 

the meaning of ‘‘Step 1’’ is unclear due 

to a conflict between the note after 

paragraph (5) of EASA AD 2024–0027, 

and later revisions of the SRM, which 

have the bushing oversize step 

numbering deleted from the applicable 

figure. 

The FAA disagrees with the request to 

add exceptions because EASA AD 

2024–0230 supersedes EASA AD 2024– 

0027 and addresses Delta’s concerns by 

clarifying the requirements that were 

specified in paragraphs (5), (6), and (7) 

of EASA AD 2024–0027. EASA AD 

2024–0230 adds Note 1 to paragraph (5) 

of EASA AD 2024–0230 to clarify which 

SRMs included steps 2 to 9 for bushing 

installation. EASA AD 2024–0230 also 

clarifies the affected airplanes for 

paragraph (6) of EASA AD 2024–0230 

and removes reference to ‘‘Step 1’’ from 

paragraph (7) of EASA AD 2024–0230. 

The FAA has not changed this AD in 

this regard. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

EASA AD 2024–0230 specifies 

procedures for repetitive detailed 

inspections (DET) for cracks of the 

affected areas (left-hand and right-hand 

wing manhole access panel attachment 

holes in the bottom wing skin panels 2, 

between rib 13 and rib 23), and 

applicable corrective actions (i.e., 

repair). EASA AD 2024–0230 also 

prohibits accomplishing a repair using 

certain SRM tasks. 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 


ddrumheller on DSK120RN23PROD with PROPOSALS1
Federal Register / Vol. 90, No. 29 / Thursday, February 13, 2025 / Proposed Rules 9525 

is issuing this SNPRM after determining 

that the unsafe condition described 

previously is likely to exist or develop 

in other products of the same type 

design. 

Certain changes described above 

expand the scope of the NPRM. As a 

result, it is necessary to reopen the 

comment period to provide additional 

opportunity for the public to comment 

on this SNPRM. 

Proposed AD Requirements in This 

SNPRM 

This proposed AD would require 

accomplishing the actions specified in 

EASA AD 2024–0230 described 

previously, except for any differences 

identified as exceptions in the 

regulatory text of this proposed AD. 

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 2024–0230 by 

reference in the FAA final rule. This 

proposed AD would, therefore, require 

compliance with EASA AD 2024–0230 

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 2024–0230 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 2024–0230. 

Material required by EASA AD 2024– 

0230 for compliance will be available at 

regulations.gov under Docket No. FAA– 

2024–1702 after the FAA final rule is 

published. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 1,650 

airplanes of U.S. registry. The FAA 

estimates the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

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

14 work-hours × $85 per hour = $1,190 ............................................................. $0 $1,190 $1,963,500 

The FAA has received no definitive 

data on which to base the cost estimates 

for the on-condition actions 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 (AD) 

2021–25–14, Amendment 39–21858 (86 

FR 72171, December 21, 2021); and 

■ b. Adding the following new AD: 

Airbus SAS: Docket No. FAA–2024–1702; 

Project Identifier MCAI–2024–00067–T. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by March 31, 

2025. 

(b) Affected ADs 

This AD replaces AD 2021–25–14, 

Amendment 39–21858 86 FR 72171, 

December 21, 2021 (AD 2021–25–14). 

(c) Applicability 

This AD applies to all Airbus SAS 

airplanes identified in paragraphs (c)(1) 

through (3) of this AD and certificated in any 

category. 

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

–115, –131, –132, –133, –151N, –153N, and 

–171N airplanes. 

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

–231, –232, –233, –251N, –252N, –253N, 

–271N, –272N, and –273N airplanes. 

(3) Model A321–211, –212, –213, –231, 

–232, –251N, –251NX, –252N, –252NX, 

–253N, –253NX, –271N, –271NX, –272N, and 

–272NX airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a determination 

that fatigue cracking may occur at the lefthand and right-hand wing manhole access 

panel attachment holes in the bottom wing 

skin panels 2, between rib 13 and rib 23, on 

airplanes with Sharklets or their structural 

reinforcements installed. This AD was also 

prompted by a determination that additional 

airplanes are subject to the unsafe condition, 

and that certain structural repair manual 


ddrumheller on DSK120RN23PROD with PROPOSALS1
9526 Federal Register / Vol. 90, No. 29 / Thursday, February 13, 2025 / Proposed Rules 

(SRM) tasks should not be used to 

accomplish repairs. The FAA is issuing this 

AD to address fatigue cracking that may 

occur in affected areas on airplanes having 

Sharklets installed during production or in 

service. The unsafe condition, if not 

addressed, could result in crack initiation 

and propagation, possibly resulting in 

reduced structural integrity of the wings. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraphs (h) and 

(i) of this AD: Comply with all required 

actions and compliance times specified in, 

and in accordance with, EASA AD 2024– 

0230, dated December 2, 2024 (EASA AD 

2024–0230). 

(h) Exceptions to EASA AD 2024–0230 

(1) Where EASA AD 2024–0230 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where EASA AD 2024–0230 refers to 

February 8, 2024 (the effective date of EASA 

AD 2024–0027 dated January 25, 2024), this 

AD requires using the effective date of this 

AD. 

(3) Where paragraph (2) of EASA AD 2024– 

0230 specifies ‘‘any finding is detected as 

defined in the [Alert Operators Transmission] 

AOT, before next flight, contact Airbus for 

approved repair instructions and, within the 

compliance time specified therein, 

accomplish those instructions accordingly,’’ 

this AD requires replacing that text with ‘‘any 

cracking is detected, the cracking must be 

repaired before further flight using a method 

approved by the Manager, AIR–520, 

Continued Operational Safety 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.’’ 

(4) This AD does not adopt the 

requirements of paragraph (4) of EASA AD 

2024–0230. 

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

section of EASA AD 2024–0230. 

(i) No Reporting Requirement 

Although the material referenced in EASA 

AD 2024–0230 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, AIR–520, Continued 

Operational Safety 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, AIR–520, Continued 

Operational Safety Branch, FAA, send it to 

the attention of the person identified in 

paragraph (k) 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, AIR–520, Continued 

Operational Safety Branch, FAA; or EASA; or 

Airbus SAS’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraphs (i) and (j)(2) of this 

AD, if any material referenced in EASA AD 

2024–0230 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. 

(k) Additional Information 

For more information about this AD, 

contact Timothy Dowling, Aviation Safety 

Engineer, FAA, 2200 South 216th St., Des 

Moines, WA 98198; phone: 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 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 2024–0230, dated December 2, 

2024. 

(ii) [Reserved] 

(3) For the 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 February 7, 2025. 

John P. Piccola, Jr., 

Director, Integrated Certificate Management 

Division, Aircraft Certification Service. 

[FR Doc. 2025–02572 Filed 2–12–25; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2025–0199; Project 

Identifier MCAI–2024–00332–T] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Canada Limited Partnership (Type 

Certificate Previously Held by C Series 

Aircraft Limited Partnership (CSALP); 

Bombardier, Inc.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Airbus Canada Limited 

Partnership Model BD–500–1A10 and 

BD–500–1A11 airplanes. This proposed 

AD was prompted by certification 

testing that found that environmental 

control system (ECS) ducts 

manufactured using a certain material 

failed the flammability test 

requirements established for 

compliance. This proposed AD would 

require inspecting the affected ECS 

ducts and, as applicable, installing a 

fire-resistant sleeve assembly over any 

non-compliant ECS duct, and prohibit 

the installation of ECS ducts as 

replacement parts under certain 

conditions, as specified in a Transport 

Canada 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 March 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 


ddrumheller on DSK120RN23PROD with PROPOSALS1