Federal Register / Vol. 89, No. 230 / Friday, November 29, 2024 / Proposed Rules 94623 

Requirements Specific to the Stairway 

(h) The stairway must have essentially 

straight route segments with a landing at 

each significant change in segment 

direction. 

(i) The stairway must have essentially 

rectangular treads. 

(j) The stairway must accommodate 

the carriage of an incapacitated 

occupant from the lower deck to the 

main deck. The crewmember 

procedures for such carriage must be 

established and included in the AFM. 

(k) In normal operation, the general 

illumination level must not be less than 

0.05 foot-candles when measured along 

the center lines of each tread and 

landing. 

(l) The stairway must have a handrail 

on at least one side to allow occupants 

to steady themselves during moderate 

turbulence in flight. The handrail(s) 

must be constructed so there is no 

obstruction on them that will cause the 

user to release his/her grip or hinder the 

continuous movement of the hands 

along the handrail. The design must 

accommodate the stature of a 5th 

percentile female and a 95th percentile 

male. 

(m) The public address system must 

be intelligible in the stairway during all 

flight phases. 

(n) ‘‘Return to seat’’ signs must be 

installed and visible in the stairway 

both going up and down and at the 

stairway entrances. 

(o) Appropriate placards must be 

located outside each main deck entrance 

to the lower lobe access stairs to 

indicate: 

(1) The maximum number of 

occupants allowed in flight. 

(2) Occupancy during flight is 

restricted to crewmembers that are 

trained in the procedures for the lower 

lobe compartments. 

(3) Occupancy is prohibited during 

taxi, take-off, and landing. 

(4) The stowage of cargo or passenger 

baggage is not allowed in the stair 

enclosure. This placard is also required 

at each stair landing. 

(p) Passengers must be prevented 

from entering the stairway in the event 

of an emergency or when no flight 

attendant is present. 

(q) The means required by condition 

(p) must be capable of being quickly 

opened from inside the stairway, even 

when crowding occurs at the passenger 

cabin side of the stair entrance. 

(r) A means must be in place to 

preclude anyone from being trapped 

inside the stairway. If a locking 

mechanism is installed, it must be 

capable of being unlocked from either 

side without the aid of tools. 

(s) There must be appropriate 

placards conspicuously located as 

follows: 

(1) Inside the stairs on or near each 

exit to the main deck defining the 

operating instructions for the door. 

(2) On the cabin side, when the door 

is closed, no higher than 4 feet from the 

floor, indicating that the door is not an 

emergency exit. For the placards 

required by condition (s) the following 

applies: 

(3) Placards must be readable from a 

distance of 30 inches under emergency 

lighting conditions. 

(4) Placards must be illuminated to at 

least 160 micro-lamberts under 

emergency lighting conditions. 

(t) There shall be a means (visible and 

audible) to notify an occupant of the 

stairway of the need to don 

supplemental oxygen equipment in the 

event of a decompression. The aural and 

visual alerts must activate before the 

cabin pressure altitude exceeds 15,000 

feet. 

(u) A means must be available, in the 

event of failure of the airplane’s main 

power system, or of the normal stairway 

lighting system, for emergency 

illumination to be automatically 

provided in the stairway. 

(1) This emergency illumination must 

be independent of the main lighting 

system. 

(2) The sources of general 

illumination may be common to both 

the emergency and the main lighting 

systems if the power supply to the 

emergency lighting system is 

independent of the power supply to the 

main lighting system. 

(3) Emergency illumination must be 

provided so that, when measured along 

the centerlines of each tread and 

landing, the illumination is not less 

than 0.05 foot-candles. 

Issued in Kansas City, Missouri, on 

signature November 18, 2024. 

Patrick R. Mullen, 

Manager, Technical Policy Branch, Policy and 

Standards Division, Aircraft Certification 

Service. 

[FR Doc. 2024–27786 Filed 11–27–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2542; Project 

Identifier MCAI–2023–00611–R] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Type Certificate 

Previously Held by Eurocopter France) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2008–10–01 and AD 2010–05–51, which 

apply to certain Eurocopter France (now 

Airbus Helicopters) Model EC120B 

helicopters. AD 2008–10–01 requires 

replacing certain part-numbered and 

serial-numbered spherical thrust 

bearings. AD 2010–05–51 requires 

repetitively inspecting the main rotor 

(M/R) head rotor hub (rotor hub) and, 

depending on the results, taking 

corrective action. Since the FAA issued 

those ADs, the manufacturer revised the 

airworthiness limitations section (ALS) 

to incorporate various airworthiness 

limitations, tasks, and associated 

thresholds and intervals that were 

previously contained in service 

bulletins, as well as incorporate a new 

task. This proposed AD would require 

revising the ALS of the existing 

maintenance manual (MM) or 

instructions for continued airworthiness 

(ICAs) and the existing approved 

maintenance or inspection program, as 

applicable, as specified in a European 

Union Aviation Safety Agency (EASA) 

AD, which is proposed for incorporation 

by reference. The FAA is proposing this 

AD to address the unsafe condition on 

these products. 

DATES: The FAA must receive comments 

on this NPRM by January 13, 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. 


khammond on DSK9W7S144PROD with PROPOSALS
94624 Federal Register / Vol. 89, No. 230 / Friday, November 29, 2024 / Proposed Rules 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–2542; 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 EASA AD, 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; phone: +49 221 8999 000; 

email: ADs@easa.europa.eu; website: 

easa.europa.eu. You may find the EASA 

material on the EASA website at 

ad.easa.europa.eu. 

• You may view this material at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Parkway, Room 6N–321, Fort Worth, TX 

76177. For information on the 

availability of this material at the FAA, 

call (817) 222–5110. The EASA material 

is also available at regulations.gov under 

Docket No. FAA–2024–2542. 

FOR FURTHER INFORMATION CONTACT: Hye 

Yoon Jang, Aviation Safety Engineer, 

1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone: (206) 231– 

3758; email: hye.yoon.jang@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–2024–2542; Project Identifier 

MCAI–2023–00611–R’’ 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 Hye Yoon Jang, 

Aviation Safety Engineer, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; phone: (206) 231–3758; email: 

hye.yoon.jang@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 2008–10–01, 

Amendment 39–15507 (73 FR 24856, 

May 6, 2008) (AD 2008–10–01), for 

Eurocopter France (now Airbus 

Helicopters) Model EC120B helicopters 

with spherical thrust bearings part 

number (P/N) 7050A3622036 having 

serial number LK0130, LK0142, LK0155, 

or LK0158, installed. AD 2008–10–01 

was prompted by Direction generale de 

l’aviation civile France (DGAC), which 

was the aviation authority for France 

before the European Aviation Safety 

Agency, AD F–2006–040, dated 

February 15, 2006 (DGAC France AD F– 

2006–040), to address a batch of nonconforming spherical thrust bearings. 

AD 2008–10–01 requires removing any 

identified spherical thrust bearing and 

installing an airworthy spherical thrust 

bearing. The FAA issued AD 2008–10– 

01 to prevent failure of a spherical 

thrust bearing during flight, which, if 

not addressed, could cause the M/R 

system to separate from the helicopter, 

which would be catastrophic. 

The FAA issued AD 2010–05–51, 

Amendment 39–16265 (75 FR 22510, 

April 29, 2010) (AD 2010–05–51), for 

Eurocopter France (now Airbus 

Helicopters) Model EC120B helicopters 

with a rotor hub P/N C622A1002103, 

C622A1002104, or C622A1002105, 

installed. AD 2010–05–51 was 

prompted by European Aviation Safety 

Agency, which was the aviation 

authority for France after the DGAC and 

before the European Union Aviation 

Safety Agency, Emergency AD 2010– 

0026–E, dated February 19, 2010 

(European Aviation Safety Agency 

Emergency AD 2010–0026–E), to 

address failure of a rotor hub attachment 

area in one of the three drag damper 

fittings. AD 2010–05–51 requires 

repetitively inspecting the rotor hub, 

and depending on the results, sanding 

the area to inspect for cracks, and 

replacing the rotor hub if cracks are 

found. The FAA issued AD 2010–05–51 

to prevent failure of a rotor hub, 

excessive vibrations, loss of an M/R 

blade, and subsequent loss of control of 

the helicopter. 

Actions Since AD 2008–10–01 and AD 

2010–05–51 Were Issued 

Since the FAA issued AD 2008–10–01 

and AD 2010–05–51, EASA, which is 

the Technical Agent for the Member 

States of the European Union (including 

France), has issued EASA AD 2023– 

0083, dated April 19, 2023 (EASA AD 

2023–0083), to supersede DGAC France 

AD F–2006–040 and European Aviation 

Safety Agency Emergency AD 2010– 

0026–E. EASA advises that 

airworthiness limitations instructions 

are identified as mandatory for 

continued airworthiness and that 

Revision 3 of AH [Airbus Helicopters] 

EC 120 B Chapter 4 ALS, dated July 18, 

2022, was issued to introduce new, or 

more restrictive tasks, or both, including 

incorporation of the requirements of 

DGAC France AD F–2006–040 and 

EASA Emergency AD 2010–0026–E. 

Consequently, EASA AD 2023–0083 

retains the requirements of DGAC 

France AD F–2006–040 and European 

Aviation Safety Agency Emergency AD 

2010–0026–E and requires 

accomplishing the actions specified in, 

and the incorporation into the Aircraft 

Maintenance Programme (AMP) of, AH 

[Airbus Helicopters] EC 120 B Chapter 

4 ALS, Revision 3, dated July 18, 2022. 

According to EASA, failure to 

accomplish these instructions could 

result in an unsafe condition. You may 

examine EASA AD 2023–0083 in the 

AD docket at regulations.gov under 

Docket No. FAA–2024–2542. 

Lastly, since the FAA issued AD 

2008–10–01 and AD 2010–05–51, 

Eurocopter France changed its name to 

Airbus Helicopters; this NPRM reflects 

that change. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

The FAA reviewed EASA AD 2023– 

0083, which requires replacing 

components before exceeding their life 

limits and accomplishing all applicable 

maintenance tasks within thresholds 

and intervals specified in the ALS as 

defined within. Depending on the 

results of the maintenance tasks, EASA 

AD 2023–0083 requires accomplishing 

corrective action(s) or contacting AH 


khammond on DSK9W7S144PROD with PROPOSALS
Federal Register / Vol. 89, No. 230 / Friday, November 29, 2024 / Proposed Rules 94625 

[Airbus Helicopters] for approved 

instructions and accomplishing those 

instructions. 

Additionally, EASA AD 2023–0083 

requires revising the AMP by 

incorporating the limitations, tasks, and 

associated thresholds and intervals 

described in the specified ALS, as 

applicable. Revising the AMP 

constitutes terminating action for the 

requirement to record accomplishment 

of the actions of replacing components 

before exceeding their life limits and 

accomplishing maintenance tasks 

within thresholds and intervals 

specified in the applicable ALS as 

required by EASA AD 2023–0083 for 

demonstration of AD compliance on a 

continued basis. 

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 

These products have been approved 

by the aviation authority of another 

country and are 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 its AD 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 require 

revising the ALS of the existing MM or 

ICAs and the existing approved 

maintenance or inspection program, as 

applicable, by incorporating new or 

more restrictive actions and associated 

thresholds and intervals, including any 

life limits, specified in EASA AD 2023– 

0083, described previously, as 

incorporated by reference, 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 EASA 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 2023–0083 by 

reference in the FAA final rule. Using 

common terms that are the same as the 

heading of a particular section in EASA 

AD 2023–0083 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 2023–0083. 

Material referenced in EASA AD 2023– 

0083 for compliance will be available at 

regulations.gov under Docket No. FAA– 

2024–2542 after the FAA final rule is 

published. 

Differences Between This Proposed AD 

and the EASA AD 

EASA AD 2023–0083 requires, as 

individual tasks, replacing certain 

components before exceeding applicable 

life limits, accomplishing certain 

maintenance tasks within thresholds 

and intervals as specified in the ALS, as 

defined within, and depending on the 

results, accomplishing corrective 

action(s), whereas this proposed AD 

would not. EASA AD 2023–0083 also 

requires revising the approved AMP to 

incorporate the limitations, tasks, and 

associated thresholds and intervals 

described in that ALS within 12 

months, whereas this proposed AD 

would require revising the ALS of the 

existing MM or ICAs and the existing 

approved maintenance or inspection 

program, as applicable, by incorporating 

the limitations, tasks, and associated 

thresholds and intervals described in 

that ALS within 30 days, and clarifies 

that if the initial instance of an 

incorporated limitation or threshold 

therein is reached before 30 days after 

the effective date of the final rule of this 

proposed AD, you still have up to 30 

days after the effective date of the final 

rule of this proposed AD to accomplish 

the corresponding task. 

Lastly, the material referenced in ‘‘the 

ALS,’’ as defined in EASA AD 2023– 

0083, specifies contacting Airbus 

[Helicopters] if there is a crack in the 

rotor hub, whereas this proposed AD 

would not require contacting Airbus 

Helicopters. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 65 

helicopters of U.S. registry. Labor rates 

are estimated at $85 per work-hour. 

Based on these numbers, the FAA 

estimates the following costs to comply 

with this proposed AD. 

Revising the ALS of the existing MM 

or ICAs and the existing approved 

maintenance or inspection program, as 

applicable, would take 1 work-hour, at 

an estimated cost of $85 per helicopter 

and $5,525 for the U.S. fleet. 

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 that the 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: 


khammond on DSK9W7S144PROD with PROPOSALS
94626 Federal Register / Vol. 89, No. 230 / Friday, November 29, 2024 / Proposed Rules 

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 

2008–10–01, Amendment 39–15507 (73 

FR 24856, May 6, 2008), and AD 2010– 

05–51, Amendment 39–16265 (75 FR 

22510, April 29, 2010); and 

■ b. Adding the following new 

airworthiness directive: 

Airbus Helicopters (Type Certificate 

previously held by Eurocopter France): 

Docket No. FAA–2024–2542; Project 

Identifier MCAI–2023–00611–R. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by January 13, 

2025. 

(b) Affected ADs 

This AD replaces AD 2008–10–01, 

Amendment 39–15507 (73 FR 24856, May 6, 

2008), and AD 2010–05–51, Amendment 39– 

16265 (75 FR 22510, April 29, 2010). 

(c) Applicability 

This AD applies to Airbus Helicopters 

(type certificate previously held by 

Eurocopter France) Model EC120B 

helicopters, certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code: 6220, Main Rotor Head. 

(e) Unsafe Condition 

This AD was prompted by new and more 

restrictive airworthiness limitations. The 

FAA is issuing this AD to prevent failure of 

certain parts, which if not addressed, could 

result in subsequent loss of control of the 

helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

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, European Union 

Aviation Safety Agency AD 2023–0083, dated 

April 19, 2023 (EASA AD 2023–0083). 

(h) Exceptions to EASA AD 2023–0083 

(1) Where EASA AD 2023–0083 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) This AD does not adopt paragraphs (1), 

(2), (4), and (5) of EASA AD 2023–0083. 

(3) Where paragraph (3) of EASA AD 2023– 

0083 specifies ‘‘Within 12 months after the 

effective date of this AD, revise the approved 

AMP,’’ this AD requires replacing that text 

with ‘‘Within 30 days after the effective date 

of this AD, revise the airworthiness 

limitations section of the existing 

maintenance manual or instructions for 

continued airworthiness and the existing 

approved maintenance or inspection 

program, as applicable.’’ 

(4) Regarding ‘‘the ALS’’ as defined in 

EASA AD 2023–0083; where the material 

referenced in ‘‘the ALS’’ in paragraph (3) of 

EASA AD 2023–0083 specifies contacting 

Airbus [Helicopters] if there is a crack in the 

(main rotor head rotor) hub body, this AD 

does not require contacting Airbus 

Helicopters. 

(5) The initial compliance time for doing 

the tasks specified in paragraph (3) of EASA 

AD 2023–0083 is on or before the applicable 

‘‘limitations’’ and ‘‘associated thresholds’’ as 

incorporated by the requirements of 

paragraph (3) of EASA AD 2023–0083 or 

within 30 days after the effective date of this 

AD, whichever occurs later. 

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

section of EASA AD 2023–0083. 

(i) Provisions for Alternative Actions and 

Intervals 

After the action required by paragraph (g) 

of this AD has been done, no alternative 

actions and associated thresholds and 

intervals, including life limits, are allowed 

unless they are approved as specified in the 

provisions of the ‘‘Ref. Publications’’ section 

of EASA AD 2023–0083. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) 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 local 

Flight Standards District 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 (k) of this AD. If 

sending information directly to the manager 

of the International Validation Branch, mail 

it to the address identified in paragraph (k) 

of this AD or email to: AMOC@faa.gov. If 

mailing information, also submit information 

by email. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(k) Additional Information 

For more information about this AD, 

contact Hye Yoon Jang, Aviation Safety 

Engineer, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone: (206) 231–3758; 

email: hye.yoon.jang@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 the AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2023–0083, dated April 19, 2023. 

(ii) [Reserved] 

(3) For EASA material identified in this 

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

50668 Cologne, Germany; phone: +49 221 

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

website: easa.europa.eu. You may find the 

EASA material on the EASA website at 

ad.easa.europa.eu. 

(4) You may view this material at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 10101 Hillwood Pkwy., Room 6N– 

321, Fort Worth, TX 76177. For information 

on the availability of this material at the 

FAA, call (817) 222 5110. 

(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 November 21, 2024. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2024–27814 Filed 11–27–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2541; Project 

Identifier MCAI–2023–00006–R] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

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 Helicopters Model 

SA341G and SA342J helicopters. This 

proposed AD was prompted by a report 

of a pilot collective pitch stick handle 

grip that broke when pulled. This 

proposed AD would require replacing 

certain pilot collective pitch stick 

handle grips and prohibit installing 

those pilot collective pitch stick handle 

grips. These actions are specified in a 

European Union Aviation Safety Agency 

(EASA) AD, which is proposed for 

incorporation by reference. The FAA is 

proposing this AD to address the unsafe 

condition on these products. 

DATES: The FAA must receive comments 

on this NPRM by January 13, 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. 


khammond on DSK9W7S144PROD with PROPOSALS