85040 Federal Register / Vol. 89, No. 207 / Friday, October 25, 2024 / Rules and Regulations 

intervals not to exceed 110 hours TIS, 

perform the actions required by paragraphs 

(h)(1)(i) through (v) of this AD: 

(i) Prepare the airplane for inspection of 

the pivot axle of the affected part in 

accordance with Section III, Paragraphs 1 

through 4, of the Work Instruction of the 

applicable MSB for your airplane. 

(ii) Clean the pivot axle of the affected part 

ensuring that any visible dye inspection 

residue is removed. 

Note 1 to paragraph (h)(1)(ii): Paragraph 5– 

63, Cleaners and Applicators, of Chapter 5, 

Nondestructive Inspection (NDI), Section 5, 

Penetrant Inspection, of FAA Advisory 

Circular 43.13–1B, ‘‘Acceptable Methods, 

Techniques, and Practices—Aircraft 

Inspection and Repair,’’ Change 1, dated 

September 8, 1998, provides guidance 

regarding an approved cleaning method. 

(iii) Perform a detailed inspection of the 

pivot axle of the affected part using a bright 

light (minimum of 100 foot-candles) and 10X 

magnifying glass to detect cracking, paying 

special attention to the radius at the top of 

the pivot axle as shown in Figure 1 of the 

Work Instruction of the applicable MSB for 

your airplane, except where Figure 1 refers 

to a ‘‘dye penetrant inspection’’ this AD does 

not require that type of inspection. 

(iv) If any cracking is found during any 

inspection required by paragraph (h)(1)(iii) of 

this AD, before further flight, replace the 

affected part with a serviceable part, and 

reinstall the nose wheel fork in accordance 

with Section III, Paragraphs 8 through 12 of 

the Work Instruction of the applicable MSB 

for your airplane. 

(v) If no cracking is found during any 

inspection required by paragraph (h)(1)(iii) of 

this AD and the compliance time specified in 

paragraph (h)(2) of this AD has not been 

exceeded, the affected part can remain 

installed until the compliance time specified 

in paragraph (h)(2) of this AD is reached. 

Reinstall the nose wheel fork in accordance 

with Section III, Paragraphs 8 through 12, of 

the Work Instruction of the applicable MSB 

for your airplane. 

(2) Within 2,500 hours TIS or 24 months 

after the effective date of this AD, whichever 

occurs first, replace an affected part with a 

serviceable part. This part replacement is 

terminating action for the repetitive 

inspections required by paragraph (h)(1) of 

this AD. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, do not 

install an affected part on any airplane. 

(j) 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 local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, mail it to the address identified in 

paragraph (k)(1) of this AD or email to: 

AMOC@faa.gov. If mailing information, also 

submit information by email. 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 

(1) For more information about this AD, 

contact Gabriel Kim, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; phone: (516) 228– 

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

(2) FAA Advisory Circular 43.13–1B, 

‘‘Acceptable Methods, Techniques, and 

Practices—Aircraft Inspection and Repair,’’ 

Change 1, dated September 8, 1998, may be 

found at drs.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) Diamond Aircraft Industries Mandatory 

Service Bulletin MSB 40–091, Rev. 0, dated 

January 18, 2021, published with Diamond 

Aircraft Industries Work Instruction WI–MSB 

40–091, Rev. 0, dated January 18, 2021 

(issued as one document). 

(ii) Diamond Aircraft Industries Mandatory 

Service Bulletin MSB F4–038, Rev.0, dated 

January 18, 2021, published with Diamond 

Aircraft Industries Work Instruction WI–MSB 

F4–038, Rev. 0, dated January 18, 2021 

(issued as one document). 

(3) For Diamond Aircraft Industries 

material identified in this AD, contact 

Diamond Aircraft Industries Inc., 1560 

Crumlin Sideroad, London, ON, Canada, N5V 

1S2; phone: (519) 457–4041; email: supportcanada@diamondaircraft.com; website: 

diamondaircraft.com. 

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

Airworthiness Products Section, Operational 

Safety Branch, 901 Locust, Kansas City, MO 

64106. 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 October 21, 2024. 

Steven W. Thompson, 

Acting Deputy Director, Compliance & 

Airworthiness Division, Aircraft Certification 

Service. 

[FR Doc. 2024–24758 Filed 10–24–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2328; Project 

Identifier AD–2024–00282–Q,R; Amendment 

39–22863; AD 2024–20–04] 

RIN 2120–AA64 

Airworthiness Directives; Various 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2024–01– 

11, which applied to all helicopters 

with certain Pacific Scientific Company 

rotary buckle assemblies (buckles) 

installed. AD 2024–01–11 required 

inspecting the buckle screws and, 

depending on the results, reidentifying 

the buckle, replacing the screws and 

reidentifying the buckle, or replacing 

the buckle. AD 2024–01–11 also 

prohibited installing certain buckles. 

This AD retains the requirements of AD 

2024–01–11, expands the applicability, 

and updates the referenced material. As 

an option to the actions required by this 

AD, this AD allows removing the male 

side from the lap of the restraint system 

assembly and installing a placard stating 

that use of the seat is prohibited; use of 

that crewmember seat or passenger seat 

is then prohibited until the actions 

required by the AD are accomplished 

and the male side from the lap of the 

restraint system assembly is reinstalled. 

This AD was prompted by a 

manufacturing defect in the screws used 

inside the buckle. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective November 

12, 2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 12, 2024. 

The FAA must receive comments on 

this AD by December 9, 2024. 

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. 


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• 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–2024–2328; or in person at 

Docket Operations between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this final rule, any comments 

received, and other information. The 

street address for Docket Operations is 

listed above. 

Material Incorporated by Reference: 

• For Parker Meggitt material 

identified in this AD, contact Parker 

Meggitt Services, 1785 Voyager Avenue, 

Simi Valley, CA 93063; phone: 877– 

666–0712; email: TechSupport@

meggitt.com; website: meggitt.com/ 

services_and_support/customer_

experience/update-on-buckle-assemblyservice-bulletins. 

• 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. It is also available 

at regulations.gov under Docket No. 

FAA–2024–2328. 

FOR FURTHER INFORMATION CONTACT: 

David Kim, Aviation Safety Engineer, 

FAA, 3960 Paramount Boulevard, 

Lakewood, CA 90712; phone: (562) 627– 

5274; email: david.kim@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written data, views, or arguments about 

this final rule. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2024–2328; Project Identifier AD–2024– 

00282–Q,R’’ at the beginning of your 

comments. The most helpful comments 

reference a specific portion of the final 

rule, 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 final rule 

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 final rule. 

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 AD 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 AD, 

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 AD. Submissions containing CBI 

should be sent to David Kim, Aviation 

Safety Engineer, FAA, 3960 Paramount 

Boulevard, Lakewood, CA 90712; 

phone: (562) 627–5274; email: 

david.kim@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 2024–01–11, 

Amendment 39–22662 (89 FR 6008, 

January 31, 2024) (AD 2024–01–11), for 

all helicopters with a Pacific Scientific 

Company buckle part number (P/N) 

1111475 (all dash numbers) or P/N 

1111548–01 installed, if the buckle was 

manufactured between January 2012 

and September 2012 inclusive or has an 

unknown date of manufacture (DOM). 

These same part-numbered buckles may 

also be installed in airplanes; the FAA 

published a separate notice of proposed 

rulemaking on February 29, 2024 (89 FR 

14783) to address all airplanes with a 

Pacific Scientific Company buckle P/N 

1111475 (all dash numbers) or P/N 

1111548–01 installed. 

For helicopters with the identified 

buckles, AD 2024–01–11 required 

inspecting each buckle screw for 

cracked, loose, and missing screw heads 

and, depending on the results, replacing 

the buckle or inspecting each screw to 

determine if any screw has a Torx head. 

Depending on the results of that 

inspection, AD 2024–01–11 required 

reassembling the buckle (if necessary) 

and reidentifying it with ‘‘INS. A’’ or 

replacing each Torx head screw with a 

hex head screw, reassembling the 

buckle, and reidentifying the buckle 

with ‘‘MOD. A.’’ If a screw head broke 

off during disassembly, AD 2024–01–11 

required replacing the buckle with an 

airworthy buckle. Lastly, AD 2024–01– 

11 prohibited installing an identified 

buckle unless it was marked with 

‘‘MOD. A’’ or ‘‘INS. A.’’ 

AD 2024–01–11 resulted from a report 

of a 2012 manufacturing defect in the 

screws used inside Pacific Scientific 

Company buckles P/N 1111475 (all dash 

numbers) and P/N 1111548–01. The 

screws used to fasten the load plate to 

the body of the buckle were found to be 

susceptible to hydrogen embrittlement 

due to improper baking during the 

electroplating process. This condition 

leads the screwhead to separate from the 

body of the screw when under load, 

which could result in the buckle failing 

to restrain the occupant to the seat. This 

condition was identified in screw Lots 

348601–A and 348994–A, which were 

manufactured between January 2012 

and September 2012, and were the first 

two lots of screws received by Pacific 

Scientific Company from a new 

supplier. The FAA issued AD 2024–01– 

11 to prevent cracking and missing 

screw heads when under load, which, if 

not addressed, could result in a failure 

of the buckle to restrain the occupant. 

Actions Since AD 2024–01–11 Was 

Issued 

Since the FAA issued AD 2024–01– 

11, additional review by the 

manufacturer revealed that an 

additional lot of screws, Lot 358764–A, 

is also affected by the same unsafe 

condition, which expands the DOM to 

April 2013 inclusive. 

Parker Meggitt also revised Service 

Bulletin (SB) 1111475–25–001–2023 

and SB 1111548–25–001–2023, each 

Revision 001 and dated December 1, 

2023 (SB 1111475–25–001–2023 Rev 

001 and SB 1111548–25–001–2023 Rev 

001), to SB 1111475–25–001–2023 and 

SB 1111548–25–001–2023, each 

Revision 002 and dated April 1, 2024 

(SB 1111475–25–001–2023 Rev 002 and 

SB 1111548–25–001–2023 Rev 002). SB 

1111475–25–001–2023 Rev 002 and SB 

1111548–25–001–2023 Rev 002 specify 

the same procedures as SB 1111475–25– 

001–2023 Rev 001 and SB 1111548–25– 

001–2023 Rev 001, except SB 1111475– 

25–001–2023 Rev 002 and SB 1111548– 

25–001–2023 Rev 002 expand the 

applicability, update material and 

tooling information, add and clarify 

certain Accomplishment Instructions 

procedures, and update figures. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

Comments to AD 2024–01–11 

After AD 2024–01–11 was published, 

the FAA received comments from 26 

commenters. The commenters included 

Airbus, Airbus Atlantic, Airbus 

Helicopters, Airbus India Private 

Limited, AS Aerospace, Ltd., ASL 


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Airlines Australia, Avionord, Castle Air, 

the Civil Aviation Safety Authority of 

Australia, Emirates Airlines, Etihad 

Airways, East West Helicopter-Panterra 

Heli Support, Elifriulia S.p.A., 

Elitellina—Pegasus Aero Group, Jordan 

Aviation, NASA Glenn Research Center 

Aircraft Operation (NASA), Parker 

Meggitt, Qatar Airways, Sabena 

Technics, San Antonio Police 

Helicopter Unit, SAS Airlines, SkyUP 

Ukraine, Starlux Airlines, Summit 

Helicopters, Inc., and two anonymous 

commenters. The following presents the 

comments received on AD 2024–01–11 

and the FAA’s response to each 

comment. 

Comment Regarding State of Design 

The Civil Aviation Safety Authority of 

Australia asked if the FAA or Parker 

Meggitt in the United Kingdom is the 

state of design for Pacific Scientific 

Company for the specified buckles. 

The United States is the state of 

design for the restraints and granted the 

technical standard order authorizations 

for those restraints; the oversight is the 

responsibility of the FAA. 

Comments Regarding Buckles Installed 

in Airplanes 

Airbus India Private Limited, 

Emirates Airlines, Jordan Aviation, 

Qatar Airlines, SAS Airlines, SkyUP 

Ukraine, and Starlux Airlines asked if 

AD 2024–01–11 applies to airplanes and 

Airbus, ASL Airlines Australia, 

Emirates Airlines, Etihad Airways, 

Jordan Aviation, NASA, Qatar Airlines, 

and SkyUP Ukraine explained that the 

affected buckles may be installed in 

aircraft other than helicopters. 

This AD applies to all helicopters 

with the affected buckles installed. The 

FAA published a separate notice of 

proposed rulemaking (89 FR 14783, 

February 29, 2024) to address all 

airplanes with an affected buckle 

installed because the FAA determined 

that a longer compliance time to 

accomplish the required actions is 

allowable for buckles installed in 

airplanes. The separate AD rulemaking 

for buckles installed in airplanes is 

available at federalregister.gov and 

regulations.gov under Docket No. FAA– 

2024–2328. 

Requests for Clarification of the 

Applicability Product Type 

Airbus India Private Limited 

requested clarification regarding 

whether AD 2024–01–11 is a rotorcraft 

or appliance AD and provided images 

from the FAA’s Dynamic Regulatory 

System website (DRS), which is the 

website that stores ADs and other 

regulatory and guidance material, that 

show the product type as appliance and 

the product subtype as rotorcraft. An 

anonymous commenter suggested the 

FAA specify in the SUMMARY section in 

the preamble and the Applicability 

paragraph of the rule portion that the 

AD is an appliance AD. 

AD 2024–01–11 applied to rotorcraft 

with a specific appliance installed. 

Regarding the information in DRS 

listing the product type as appliance 

and the product subtype as rotorcraft, 

the FAA has since updated the listing in 

DRS to show the product type as both 

aircraft and appliance, and the subtype 

as rotorcraft. The FAA disagrees with 

explicitly stating that the AD is an 

appliance AD in the SUMMARY section 

and the Applicability paragraph because 

the AD is, in fact, a rotorcraft AD that 

affects all helicopters with the affected 

buckles installed. Additionally, the 

purpose of the SUMMARY section is to 

briefly explain the AD action, which 

may include, but is not limited to, 

providing the following types of 

information: affected products or 

articles, required actions, and the unsafe 

condition. And the purpose of the 

Applicability paragraph is to clearly 

identify the affected products or articles. 

Requests for the Referenced Material 

and a Direct Link in the Background 

Section 

Avionord, Castle Air, Elifriulia S.p.A, 

and Sabena Technics requested a copy 

of the service bulletins referenced in AD 

2024–01–11. Parker Meggitt requested 

the FAA add a hyperlink in the 

Background section to 

www.meggitt.com/services_and_

support/customer_experience/updateonbuckle-assembly-service-bulletins, 

which provides a direct link to the 

service bulletins. 

The service bulletins referenced in 

AD 2024–01–11 are available in the AD 

docket at www.regulations.gov/ 

document/FAA–2024–0034–0002. The 

ADDRESSES section, as well as the 

Material Incorporated by Reference 

paragraph, provide availability 

information for the service bulletins, 

including the direct link requested by 

Parker Meggitt. Regarding the request to 

add the direct link in the Background 

section, the purpose of the Background 

section is to explain the unsafe 

condition and the FAA’s justification for 

issuing the AD action. It may include, 

but is not limited to, providing the 

following types of information: the 

circumstances that created the need to 

correct the unsafe condition, historical 

information, consequences if the unsafe 

condition is not corrected, and any 

other information that supports the AD 

action. Additionally, the service 

bulletins referenced in AD 2024–01–11 

are no longer available at that direct 

link. Since this request does not correct 

information, it has not been 

incorporated into this new AD. 

Comments Regarding Parker Meggitt 

Services’ Email Address 

East West Helicopter-Panterra Heli 

Support, Elifriulia S.p.A., Parker 

Meggitt, Pegasus Aero-Group, Sabena 

Technics, and Summit Helicopters, Inc., 

stated that the email address identified 

in AD 2024–01–11 for contacting Parker 

Meggitt Services was incorrect. 

The FAA has corrected the email 

address for contacting Parker Meggitt 

Services in this AD to TechSupport@

meggitt.com. 

Request To Clarify the Received Report 

in the Background Section 

Parker Meggitt requested the FAA 

revise the Background section by 

clarifying that the report received by the 

FAA is for a ‘‘2012’’ manufacturing 

defect in the screws used inside Pacific 

Scientific Company buckle P/N 1111475 

(all dash numbers) and P/N 1111548–01 

to prevent operator confusion. 

The FAA agrees and has revised the 

Background section in this new AD 

accordingly. 

Comments Regarding Illegible Dates of 

Manufacture or Lack of DOM Marking 

East West Helicopter-Panterra Heli 

Support commented that the DOM on 

the plastic tag on the back of the buckle 

is easily erased and the AD requires 

replacing any Torx head screws before 

further flight if the date tag is 

unreadable on the buckle. Airbus 

Atlantic commented that some buckles 

may not have been marked with a DOM 

and asked when the DOM marking was 

implemented. 

The FAA acknowledges these 

comments and infers concern that some 

buckles may be repaired or replaced 

unnecessarily due to the date of 

manufacture not being legible. 

Applicable part-numbered buckles with 

an illegible or missing DOM, including 

those that may have never been marked, 

are considered as having an unknown 

DOM for the purposes of this AD and 

must comply with the requirements of 

this AD. Additionally, the compliance 

time to accomplish the inspections is 

within 3 months after the AD’s effective 

date; only if, as a result of the 

inspections, it is determined that a Torx 

head screw is installed, is replacing 

each Torx head screw required before 

further flight. The DOM marking was 

added to buckle P/N 1111475 (all dash 

numbers) after the initial 2012 

investigation while buckle P/N 


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1111548–01 has always been marked 

with the DOM. Additionally, part 

marking preservation and 

reidentification is the responsibility of 

operators. 

Comment Regarding Availability of 

Replacement Screws, Grounding 

Helicopters, and Requesting Alternative 

Methods of Compliance (AMOCs) 

East West Helicopter-Panterra Heli 

Support commented that the supplier of 

the affected screws has no screws 

available, and none are on order. East 

West Helicopter-Panterra Heli Support 

further commented that the lack of 

screws could ground helicopters and the 

alternate option to replace the entire 

seat belt harness with a parts cost of 

$8,135 is not stated in the Costs of 

Compliance section. East West 

Helicopter-Panterra Heli Support 

requested the FAA revise the AD to 

allow a daily inspection to ensure that 

no screw heads are broken off until the 

AD is due in May (2024), which could 

also provide time for screws to become 

available over the next couple of months 

and avoid grounding helicopters. An 

anonymous commenter referenced East 

West Helicopter-Panterra Heli Support’s 

comment and inquired whether an 

AMOC could be requested for repetitive 

inspections until parts become available 

or for an extension to accomplish a 

repair. 

To the extent spare parts may not 

exist to replace parts that fail the 

inspection requirements of this AD, the 

FAA cannot base its AD action on 

whether spare parts are available or can 

be produced. While every effort is made 

to avoid grounding aircraft, the FAA 

must address the unsafe condition. 

While operators may choose to replace 

the entire seat belt harness assembly, it 

is not necessary to do so as the buckle 

can be replaced, which may include 

repairing the buckle, as a component 

independently from the assembly. 

Regarding the request to allow a daily 

inspection to ensure that no screw 

heads are broken off, operators may 

request approval of any specific 

alternative actions as an AMOC under 

the provisions of paragraph (i) of this 

AD. 

Requests Regarding Deactivating a Seat 

An anonymous commenter requested 

the FAA revise its AD to allow 

deactivating and placarding as 

‘‘Inoperative’’ an identified discrepant 

buckle on a seat, other than the one(s) 

which must be occupied by the 

minimum crew required to operate the 

affected rotorcraft, per 14 CFR 91.213(b) 

and MMEL [Master Minimum 

Equipment List] PL–34. The commenter 

also requested clarification of the FAA’s 

position regarding deactivating nonoperational seats. 

The FAA agrees with the commenter’s 

request and has added an optional 

action for the AD requirements. This AD 

allows, for a crewmember seat or 

passenger seat with a restraint system 

with an affected buckle installed, 

removing the male side from the lap of 

the restraint system assembly and 

fabricating and installing a placard on 

the seat stating that use of the seat is 

prohibited. Use of that crewmember seat 

or passenger seat is then prohibited 

until the actions required by the AD are 

accomplished and the male side from 

the lap of the restraint system assembly 

is reinstalled. 

Request To Change Citations of 

Referenced Material 

AS Aerospace Ltd requested the FAA 

change the paragraph citations to 

referenced service bulletins in the 

Required Actions paragraph to begin 

with a number instead of a letter, e.g., 

state ‘‘paragraph 4.B.(4)(a)’’ instead of 

‘‘paragraph B.(4)(a)’’ because the service 

bulletins identify a number before each 

section title. 

The FAA disagrees. The paragraph 

citations to the service bulletins suffice 

since they identify the section of the 

service bulletins by title instead, e.g., 

‘‘Accomplishment Instructions, 

paragraph B.(4)(a).’’ 

Request To Correct the Flow Chart in 

Referenced Material 

Airbus Atlantic commented that an 

error in the flowchart in the Parker 

Meggitt service bulletin results in 

buckles being incorrectly reidentified. 

The flowcharts in Parker Meggitt SB 

1111475–25–001–2023 and SB 

1111548–25–001–2023, each original 

issue and dated September 1, 2023, 

specify only the reidentification of 

‘‘MOD. A.’’ One of the changes 

incorporated in SB 1111475–25–001– 

2023 Rev 001 and in SB 1111548–25– 

001–2023 Rev 002 was a change in the 

flowcharts to reidentify the buckle with 

‘‘INS. A’’ or ‘‘MOD. A’’ depending on 

the inspection results. 

Request To Revise a Service Bulletin 

Figure 

Airbus Atlantic requested revision of 

the ‘‘Torx Head Screws vs. Hex Head 

Screws’’ figure (Figure 7 of SB 1111475– 

25–001–2023 Rev 001 and Figure 5 of 

SB 1111548–25–001–2023 Rev 001) in 

the service bulletins to add the dates 

when each screw was used. 

The FAA cannot require a 

manufacturer to revise its publications; 

however, the FAA does include 

exceptions in an AD to referenced 

material that is required for compliance 

to correct information within the 

referenced material. The proposed 

changes do not correct information in 

the referenced material and accordingly, 

have not been incorporated into this 

new AD. 

Requests for Clarification Regarding 

Returning Parts to Parker Meggitt 

An anonymous commenter requested 

clarification regarding whether a buckle 

needs to be scrapped when a screw head 

breaks off during disassembly because it 

cannot be sent to Parker Meggitt for 

repair. And, if so, the commenter 

requested the FAA revise the AD to state 

that such buckles must be scrapped and 

update the Costs of Compliance 

accordingly. The commenter also asked 

if the FAA intended to prevent 

operators from attempting to repair such 

buckles in the field by removing the 

threaded portion of the broken screw 

and installing a new screw and, if so, to 

consider deleting the paragraph in the 

Required Actions paragraph and let the 

service information stand as-is (i.e., 

return a buckle with broken screws to 

Parker Meggitt for repair or 

replacement). 

Since the AD does not require 

(permanently) removing a damaged 

buckle from service, the damaged 

buckle may be returned to an airworthy 

condition. The AD does not require 

returning a buckle to Parker Meggitt 

because the FAA does not have the 

authority to direct operators to return 

defective components to the 

manufacturer in this AD. Because the 

AD also does not specify any particular 

procedure to return a damaged buckle to 

an airworthy condition, a procedure that 

is acceptable to the FAA must be used, 

which includes operators choosing to 

return a damaged buckle to Parker 

Meggitt for repair as the AD does not 

prohibit an operator from doing so. 

Operators may also request approval of 

any specific corrective actions as an 

AMOC under the provisions of 

paragraph (i) of this AD. 

Requests Regarding the Magnet Used 

for the Magnet Test 

Airbus Helicopters commented 

regarding Meggitt Service Bulletin SB 

1111475–25–001–2023 and stated that 

the magnetism strength of the magnet is 

the representative physical quantity to 

determine if each screw has a Torx head 

or hex head in the magnet test. Airbus 

Helicopters asked if Meggitt would 

provide more precise information 

concerning the magnet (particularly its 

magnetism strength) and if Meggitt 

would provide this magnet as a specific 


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85044 Federal Register / Vol. 89, No. 207 / Friday, October 25, 2024 / Rules and Regulations 

tool to ensure proper application of the 

service bulletin. Airbus Atlantic also 

requested that the service bulletin 

specify precise/physical characteristics 

of the magnet to be used to perform the 

magnet test. Additionally, Airbus 

Atlantic requested that Meggitt specify 

the magnet as a special tool with a part 

number and provide that tool to 

operators. 

Since AD 2024–01–11 was issued, SB 

1111475–25–001–2023 Rev 001 has 

been revised to Rev 002, to incorporate 

various changes, including the addition 

of a website link to magnet P/N 

5862K104 under the Material 

Information, paragraph G.—Special 

Tooling. The website at this link 

provides various magnet specification 

information. SB 1111475–25–001–2023 

Rev 002 also recommends certain 

magnet dimensions and explains that a 

magnet that is strong enough to not slip 

off the buckle suffices for the purposes 

of the magnet test. Regarding the request 

for Meggitt to provide a magnet, the 

FAA does not have the authority to 

require a manufacturer to send any 

tooling to an operator. 

Requests Regarding the Magnet Test for 

a Buckle With Velcro Installed on Its 

Back Plate 

Airbus Helicopters commented 

regarding Meggitt Service Bulletin SB 

1111475–25–001–2023 that the magnet 

test is not applicable for all buckles 

because some buckles have Velcro on 

their back plate that attaches padding 

between the buckle and the occupant. 

Airbus Helicopters requested that 

Meggitt provide an alternate method for 

buckles with this Velcro installed. 

Airbus Atlantic also expressed concern 

about inaccurate results from the 

magnet test when Velcro is attached to 

the buckle back plate. 

Since AD 2024–01–11 was issued, SB 

1111475–25–001–2023 Rev 001, as well 

as SB 1111548–25–001–2023 Rev 001, 

were revised to Rev 002 to incorporate 

various changes, including the addition 

of procedures to accomplish the magnet 

test for a buckle that has Velcro 

installed on its back plate. Therefore, 

this AD provides two other methods for 

determining if any screw has a Torx 

head as an alternative to the magnet test. 

Requests for Clarification of ‘‘Thin 

Metal Stock’’ and Removing a Buckle 

Airbus Helicopters commented 

regarding Meggitt Service Bulletin SB 

1111475–25–001–2023 and requested 

that Meggitt provide more details about 

the ‘‘thin metal stock’’ to be used to 

remove a buckle, the way to proceed, 

and a reference to a well-known 

procedure of CMM [Component 

Maintenance Manual]. 

Since AD 2024–01–11 was issued, SB 

1111475–25–001–2023 Rev 001 was 

revised to Rev 002 to incorporate 

various changes, including the addition 

of dimensions and specification of a 

shim or feeler gauge (metal stock) under 

the Material Information, paragraph 

G.—Special Tooling. This AD requires 

using Revision 2 of the referenced 

material to accomplish its requirements. 

AD 2024–01–11 does not refer to a 

component maintenance manual and 

the FAA cannot require a manufacturer 

to revise its publications. 

Requests for Torque Values 

Airbus Helicopters commented 

regarding Meggitt Service Bulletin SB 

1111475–25–001–2023 and requested 

that Meggitt provide the precise torque 

values to reassemble the two parts of the 

buckle because the values are missing. 

Since AD 2024–01–11 was issued, SB 

1111475–25–001–2023 Rev 001 was 

revised to Rev 002 to incorporate 

various changes, including the addition 

of the torque values. Further, this AD 

requires using Revision 2 of the 

referenced material to accomplish its 

requirements. 

Request Regarding Service Bulletin 

Accomplishment Traceability 

Airbus Helicopters commented 

regarding Meggitt Service Bulletin SB 

1111475–25–001–2023 and requested 

that Meggitt provide a proposal for 

buckle (re)identification that indicates 

the completion of its service bulletin to 

ensure the traceability of affected 

buckles. 

Parker Meggitt SB 1111475–25–001– 

2023 Rev 002, which is incorporated by 

reference in this AD, specifies 

procedures for marking affected buckles 

that have passed the inspections with 

‘‘INS. A’’ and marking affected buckles 

that have successfully been modified 

with ‘‘MOD. A.’’ 

FAA’s Determination 

The FAA is issuing this AD because 

the agency determined the unsafe 

condition described previously is likely 

to exist or develop in other products of 

the same type design. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

The FAA reviewed SB 1111475–25– 

001–2023 Rev 002 for buckle P/N 

1111475 and SB 1111548–25–001–2023 

Rev 002 for buckle P/N 1111548–01. 

This material specifies procedures for 

inspecting the buckle for any missing or 

loose screw heads and depending on the 

results, replacing the buckle and 

sending the removed buckle to Parker 

Meggitt for repair or replacement. If 

after that first inspection, all of the 

screw heads are intact, this material 

specifies procedures for inspecting the 

buckle for any Torx head screws (alloy 

steel) and, depending on the results, 

allowing the buckle assembly to remain 

in-service temporarily, replacing any 

Torx head screws (alloy steel) with new 

hex head screws (stainless steel), and 

checking the functionality of the buckle. 

This material also specifies procedures 

for removing a buckle from a restraint 

system, installing a buckle on a restraint 

system, and returning buckles to Parker 

Meggitt. If the buckle passes the 

specified inspections or is modified by 

replacing Torx head screws (alloy steel) 

with new hex head screws (stainless 

steel) screws, this material specifies 

procedures for reidentifying the back of 

the buckle. 

The buckle may be included as a 

component of a different part-numbered 

restraint system assembly. This material 

identifies known affected restraint 

system assembly P/Ns. 

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. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the referenced 

material described previously, except as 

discussed under ‘‘Differences Between 

this AD and the Referenced Material.’’ 

Differences Between This AD and the 

Referenced Material 

The material incorporated by 

reference does not specify any 

compliance times, whereas this AD 

requires accomplishing the required 

actions within three months. This AD 

also prohibits installing an affected 

buckle on any helicopter unless the 

buckle includes ‘‘MOD A’’ or ‘‘INS A’’ 

on the buckle as of the effective date of 

this AD. 

The material incorporated by 

reference specifies sending any 

damaged buckles to Parker Meggitt for 

repair or replacement, and this AD does 

not. Instead, this AD requires replacing 

the buckle with an airworthy buckle. 

The material incorporated by 

reference allows buckles with a Torx 

head (alloy steel) screw to remain in 

service temporarily and be replaced at a 

time convenient to the operator, and 

this AD does not. If a buckle has any 

number of Torx head (alloy steel) screws 

installed, this AD requires replacing all 

four screws with hex head screws before 

further flight. 


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If a screw head breaks off during 

disassembly of a buckle or if reassembly 

of a buckle is not possible, the material 

incorporated by reference specifies 

returning the buckle to Parker Meggitt, 

whereas this AD does not. If a screw 

head breaks off during disassembly, this 

AD requires replacing the buckle with 

an airworthy buckle. If reassembly of a 

buckle is not possible, then the buckle 

is not airworthy. 

This AD has the optional action, for 

a crewmember seat or passenger seat 

with a restraint system with an affected 

buckle installed, within 3 months after 

the effective date, of removing the male 

side from the lap of the restraint system 

assembly and fabricating and installing 

a placard on the seat stating that use of 

the seat is prohibited. Use of that 

crewmember seat or passenger seat is 

then prohibited until the actions 

required by the AD are accomplished 

and the male side from the lap of the 

restraint system assembly is reinstalled. 

The material incorporated by reference 

does not include this optional action. 

Justification for Immediate Adoption 

and Determination of the Effective Date 

Section 553(b) of the Administrative 

Procedure Act (APA) (5 U.S.C. 551 et 

seq.) authorizes agencies to dispense 

with notice and comment procedures 

for rules when the agency, for ‘‘good 

cause,’’ finds that those procedures are 

‘‘impracticable, unnecessary, or contrary 

to the public interest.’’ Under this 

section, an agency, upon finding good 

cause, may issue a final rule without 

providing notice and seeking comment 

prior to issuance. Further, section 

553(d) of the APA authorizes agencies to 

make rules effective in less than thirty 

days, upon a finding of good cause. 

An unsafe condition exists that 

requires the immediate adoption of this 

AD without providing an opportunity 

for public comments prior to adoption. 

The FAA has found that the risk to the 

flying public justifies forgoing notice 

and comment prior to adoption of this 

rule because in an otherwise survivable 

accident, hard landing, or severe 

turbulence, the buckle may fail to 

restrain the occupant. Based on the 

rotorcraft accident rate, coupled with 

not knowing the propagation rate of this 

unsafe condition into failure, the FAA 

determined that the compliance time to 

inspect affected buckles installed in 

helicopters must be within three 

months. Accordingly, notice and 

opportunity for prior public comment 

are impracticable and contrary to the 

public interest pursuant to 5 U.S.C. 

553(b). 

In addition, the FAA finds that good 

cause exists pursuant to 5 U.S.C. 553(d) 

for making this amendment effective in 

less than 30 days, for the same reasons 

the FAA found good cause to forgo 

notice and comment. 

Regulatory Flexibility Act 

The requirements of the Regulatory 

Flexibility Act (RFA) do not apply when 

an agency finds good cause pursuant to 

5 U.S.C. 553 to adopt a rule without 

prior notice and comment. Because FAA 

has determined that it has good cause to 

adopt this rule without prior notice and 

comment, RFA analysis is not required. 

Costs of Compliance 

The FAA estimates that this AD 

affects approximately 21,313 buckles 

installed on restraint systems in aircraft 

worldwide. The FAA has no way of 

knowing the number of helicopters of 

U.S. Registry that may have a restraint 

system with an affected buckle 

installed. The estimated costs on U.S. 

operators reflects the maximum possible 

costs based on affected buckles installed 

on restraint systems in aircraft 

worldwide. Labor rates are estimated at 

$85 per work-hour. Based on these 

numbers, the FAA estimates that 

operators may incur the following costs 

in order to comply with this AD. 

Inspecting a buckle will take 

approximately 0.1 work-hour for an 

estimated cost of $9 per buckle and up 

to $191,817. for the U.S. fleet. If 

required, replacing a set of screws (four) 

will take approximately 0.5 work-hour 

and parts will cost a nominal amount 

for an estimated cost of $43 per buckle. 

Replacing a buckle will take 

approximately 0.5 work-hour and parts 

will cost approximately $740 for an 

estimated cost of $783 per buckle. The 

FAA estimates a nominal cost for 

reidentifying a buckle. 

The optional action of removing the 

male side from the lap of the restraint 

system assembly on the crewmember or 

passenger seat and fabricating and 

installing a placard will take 

approximately 1.5 work-hours and parts 

will cost a nominal amount for an 

estimated cost of $128 per seat. 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, some of the 

costs of this AD may be covered under 

warranty, thereby reducing the cost 

impact on affected operators. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs describes in more 

detail the scope of the Agency’s 

authority. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701: General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

and 

(2) Will not affect intrastate aviation 

in Alaska. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by: 

■ a. Removing Airworthiness Directive 

2024–01–11, Amendment 39–22662 (89 

FR 6008, January 31, 2024); and 

■ b. Adding the following new 

airworthiness directive: 

2024–20–04 Various Helicopters: 

Amendment 39–22863; Docket No. 

FAA–2024–2328; Project Identifier AD– 

2024–00282–Q,R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective November 12, 2024. 


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(b) Affected ADs 

This AD replaces AD 2024–01–11, 

Amendment 39–22662 (89 FR 6008, January 

31, 2024) (AD 2024–01–11). 

(c) Applicability 

This AD applies to all helicopters, 

certificated in any category, with a restraint 

system with a Pacific Scientific Company 

rotary buckle assembly (buckle) part number 

(P/N) 1111475 (all dash numbers) or P/N 

1111548–01 having a date of manufacture 

(DOM) between January 2012 and April 2013 

inclusive, or an unknown DOM. These 

buckles may be installed on, but not limited 

to, Airbus Helicopters model helicopters. 

Note 1 to paragraph (c): The buckle may 

be included as a component of a different 

part-numbered restraint system assembly. 

Note 2 to paragraph (c): These buckles 

may also be installed on airplanes; however, 

the FAA determined that a longer 

compliance time to accomplish the required 

actions is allowable for buckles installed on 

airplanes. Accordingly, the FAA plans to 

publish a separate AD rulemaking to address 

all airplanes with an affected buckle 

installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code: 2500, Cabin Equipment/Furnishing; 

and 2510, Flight Compartment Equipment. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

manufacturing defect in the screws used 

inside the buckle. The FAA is issuing this 

AD to prevent cracking and missing screw 

heads when under load. The unsafe 

condition, if not addressed, could result in a 

failure of the buckle to restrain the occupant. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For helicopters with buckle P/N 

1111475 (all dash numbers), within 3 months 

after the effective date of this AD, inspect 

each buckle screw for cracked, loose, and 

missing screw heads by following the 

Accomplishment Instructions, paragraphs 

B.(1) and (2), of Parker Meggitt Service 

Bulletin (SB) 1111475–25–001–2023, 

Revision 002, dated April 1, 2024 (SB 

1111475–25–001–2023 Rev 002). 

(i) If any screw has a cracked, loose, or 

missing screw head, before further flight, 

replace the buckle with an airworthy buckle. 

(ii) If none of the four screw heads are 

cracked, loose, or missing, before further 

flight, inspect each screw to determine if any 

screw has a Torx head by using one of the 

following methods in the Accomplishment 

Instructions of SB 1111475–25–001–2023 

Rev 002: paragraph B.(4)(a) (Magnet Test); 

paragraph B.(4)(b) (Inspection); or paragraphs 

C.(2) through (4) (removing the buckle from 

the restraint system) and paragraphs D.(1)(a) 

through (d) (disassembling the buckle). 

(A) If none of the four screws have a Torx 

head, before further flight, reassemble the 

buckle (if necessary) by following the 

Accomplishment Instructions, paragraphs 

D.(1)(f) through (l), of SB 1111475–25–001– 

2023 Rev 002, and reidentify the buckle with 

‘‘INS. A’’ by following the Accomplishment 

Instructions, paragraph B.(6), of SB 1111475– 

25–001–2023 Rev 002. 

(B) If at least one of the four screws has a 

Torx head, before further flight, with the 

buckle removed, replace each Torx head 

screw with a hex head screw, reassemble the 

buckle, and reidentify the buckle with 

‘‘MOD. A’’ by following the Accomplishment 

Instructions, paragraphs D.(1)(e) through (m), 

of SB 1111475–25–001–2023 Rev 002, except 

you are not required to return any parts to 

Parker Meggitt. If a screw head breaks off 

during disassembly, before further flight, 

replace the buckle with an airworthy buckle. 

Note 3 to paragraph (g)(1): SB 1111475– 

25–001–2023 Rev 002 refers to a magnifying 

glass as an ‘‘eye loupe.’’ 

(2) For helicopters with buckle P/N 

1111548–01, within 3 months after the 

effective date of this AD, inspect each buckle 

screw for cracked, loose, and missing screw 

heads by following the Accomplishment 

Instructions, paragraph B.(1), of Parker 

Meggitt SB 1111548–25–001–2023, Revision 

002, dated April 1, 2024 (SB 1111548–25– 

001–2023 Rev 002). 

(i) If any screw has a cracked, loose, or 

missing screw head, before further flight, 

replace the buckle with an airworthy buckle. 

(ii) If none of the four screw heads are 

cracked, loose, or missing, before further 

flight, inspect each screw to determine which 

screws have a Torx head by using one of the 

following methods in the Accomplishment 

Instructions of SB 1111548–25–001–2023 

Rev 002: paragraph B.(3)(a) (Inspection); or 

paragraph C. (removing the buckle from the 

restraint system) and paragraphs D.(1)(a) 

through (c) (disassembling the buckle). 

(A) If none of the four screws have a Torx 

head, before further flight, reassemble the 

buckle (if necessary) by following the 

Accomplishment Instructions, paragraphs 

D.(1)(e) through (l), of SB 1111548–25–001– 

2023 Rev 002, and reidentify the buckle with 

‘‘INS. A’’ by following the Accomplishment 

Instructions, paragraph B.(5), of SB 1111548– 

25–001–2023 Rev 002. 

(B) If at least one of the four screws has a 

Torx head, before further flight, with the 

buckle removed, replace each Torx head 

screw with a hex head screw, reassemble the 

buckle, and reidentify the buckle with 

‘‘MOD. A’’ by following the Accomplishment 

Instructions, paragraphs D.(1)(d) through (m), 

of SB 1111548–25–001–2023 Rev 002, except 

you are not required to return any parts to 

Parker Meggitt. If a screw head breaks off 

during disassembly, before further flight, 

replace the buckle with an airworthy buckle. 

Note 4 to paragraph (g)(2): SB 1111548– 

25–001–2023 Rev 002 refers to a magnifying 

glass as an ‘‘eye loupe.’’ 

(3) As of the effective date of this AD, do 

not install a buckle identified in paragraph 

(c) of this AD on any helicopter unless the 

buckle is marked with ‘‘MOD. A’’ or ‘‘INS. 

A.’’ 

(4) For a crewmember seat or passenger 

seat with a restraint system with a buckle 

identified in paragraph (c) of this AD 

installed, as an option for the actions 

required by paragraph (g)(1) or (2) of this AD, 

as applicable, within 3 months after the 

effective date of this AD: 

(i) Remove the male side from the lap of 

the restraint system assembly. 

(ii) Fabricate a placard using at least 1⁄8

inch letters with the words ‘‘USE OF THIS 

SEAT IS PROHIBITED’’ on it and install the 

placard on the seat within the crewmember 

or passenger’s clear view. The seat is then 

inoperative until the actions required by 

paragraph (g)(1) or (2) of this AD, as 

applicable, are accomplished and the male 

side from the lap of the restraint system 

assembly is reinstalled. 

(h) Credit for Previous Actions 

(1) You may take credit for the actions 

required by paragraph (g)(1) or (2) of this AD, 

as applicable, if you accomplished AD 2024– 

01–11 before the effective date of this AD, 

provided torque of 15 to 25 in-lbs (1.69 to 

2.82 N-m) was applied on the four hex head 

screws (P/N 0901101–149) during any repair 

of the buckle. 

(2) You may take credit for actions required 

by paragraph (g)(1) or (2) of this AD, as 

applicable, if the corresponding actions were 

performed before the effective date of this AD 

using Parker Meggitt SB 1111475–25–001– 

2023, Revision 001, dated December 1, 2023, 

or Parker Meggitt SB 1111548–25–001–2023, 

Revision 001, dated December 1, 2023, as 

applicable, and provided torque of 15 to 25 

in-lbs (1.69 to 2.82 N-m) was applied on the 

four hex head screws (P/N 0901101–149) 

during any repair of the buckle. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, West Certification 

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 West Certification 

Branch, send it to the attention of the person 

identified in paragraph (j) of this AD. 

Information may be emailed to: AMOC@

faa.gov. 

(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. 

(j) Additional Information 

For more information about this AD, 

contact David Kim, Aviation Safety Engineer, 

FAA, 3960 Paramount Boulevard, Lakewood, 

CA 90712; phone: (562) 627–5274; email: 

david.kim@faa.gov. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the material listed in this paragraph 

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

(2) You must use this material as 

applicable to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Parker Meggitt Service Bulletin 

1111475–25–001–2023, Revision 002, dated 

April 1, 2024. 


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Federal Register / Vol. 89, No. 207 / Friday, October 25, 2024 / Rules and Regulations 85047 

1 21 U.S.C. 811(a). 

2See Schedules of Controlled Substances: 

Temporary Placement of Butonitazene, 

Etodesnitazene, Flunitazene, Metodesnitazene, 

Metonitazene, N-Pyrrolidino etonitazene, and 

Protonitazene in Schedule I, 87 FR 21556 (Apr. 12, 

2022). The four additional benzimidazole-opioids 

were etodesnitazene, metonitazene, N-pyrrolidino 

etonitazene, and protonitazene. DEA pursued 

separate scheduling actions for metonitazene, see 

88 FR 56466 (Aug. 18, 2023) and for etodesnitazene, 

N-pyrrolidino etonitazene, and protonitazene, see 

89 FR 25514 (Apr. 11, 2024) to remain as schedule 

I substances under the CSA in order to meet the 

United States’ obligations under the United Nations 

Single Convention on Narcotic Drugs, Mar. 30, 

1961, 18 U.S.T. 1407, 520 U.N.T.S. 151 (Single 

Convention), as amended by the 1972 Protocol. 

3See Schedules of Controlled Substances: 

Extension of Temporary Placement of Butonitazene, 

Flunitazene, and Metodesnitazene in Schedule I of 

the Controlled Substances Act, 89 FR 25517 (Apr. 

11, 2024). 

4See Schedules of Controlled Substances: 

Placement of Butonitazene, Flunitazene, and 

Metodesnitazene Substances in Schedule I, 89 FR 

25544 (Apr. 11, 2024). 

5 DEA published a final order to permanently 

place the three other benzimidazole-opioids 

(etodesnitazene, N-pyrrolidino etonitazene, and 

protonitazene) in schedule I of the CSA. See 

Schedules of Controlled Substances: Placement of 

Etodesnitazene, N-Pyrrolidino Etonitazene, and 

Protonitazene in Schedule I, 89 FR 25514 (Apr. 11, 

2024). 

(ii) Parker Meggitt Service Bulletin 

1111548–25–001–2023, Revision 002, dated 

April 1, 2024. 

(3) For Parker Meggitt material identified 

in this AD, contact Parker Meggitt Services, 

1785 Voyager Avenue, Simi Valley, CA 

93063; phone: 877–666–0712; email: 

TechSupport@meggitt.com; website: 

meggitt.com/services_and_support/ 

customer_experience/update-on-buckleassembly-service-bulletins. 

(4) 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. 

(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 21, 2024. 

Steven W. Thompson, 

Acting Deputy Director, Compliance & 

Airworthiness Division, Aircraft Certification 

Service. 

[FR Doc. 2024–24756 Filed 10–24–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF JUSTICE 

Drug Enforcement Administration 

21 CFR Part 1308 

[Docket No. DEA–900N] 

Schedules of Controlled Substances: 

Placement of Butonitazene, 

Flunitazene, and Metodesnitazene 

Substances in Schedule I 

AGENCY: Drug Enforcement 

Administration, Department of Justice. 

ACTION: Final rule. 

SUMMARY: The Drug Enforcement 

Administration places butonitazene, 

flunitazene, and metodesnitazene 

including their isomers, esters, ethers, 

salts and salts of isomers, esters and 

ethers in schedule I of the Controlled 

Substances Act. The regulatory controls 

and administrative, civil, and criminal 

sanctions applicable to schedule I 

controlled substances on persons who 

handle (manufacture, distribute, reverse 

distribute, import, export, engage in 

research, conduct instructional 

activities or chemical analysis with, or 

possess), or propose to handle these 

three specific controlled substances will 

continue to apply as a result of this 

action. 

DATES: Effective October 25, 2024. 

FOR FURTHER INFORMATION CONTACT: Dr. 

Terrence L. Boos, Drug and Chemical 

Evaluation Section, Diversion Control 

Division, Drug Enforcement 

Administration; Telephone: (571) 362– 

3249. 

SUPPLEMENTARY INFORMATION: In this 

final rule, the Drug Enforcement 

Administration (DEA) permanently 

schedules the following three controlled 

substances in schedule I of the 

Controlled Substances Act (CSA), 

including their isomers, esters, ethers, 

salts, and salts of isomers, esters, and 

ethers whenever the existence of such 

isomers, esters, ethers, and salts is 

possible within the specific chemical 

designation: 

• Butonitazene (2-(2-(4- 

butoxybenzyl)-5-nitro-1H-benzimidazol1-yl)-N,N-diethylethan-1-amine), 

• Flunitazene (N,N-diethyl-2-(2-(4- 

fluorobenzyl)-5-nitro-1H-benzimidazol1-yl)ethan-1-amine), 

• Metodesnitazene (N,N-diethyl-2-(2- 

(4-methoxybenzyl)-1H-benzimidazol-1- 

yl)ethan-1-amine). 

Legal Authority 

The CSA provides that proceedings 

for the issuance, amendment, or repeal 

of the scheduling of any drug or other 

substance may be initiated by the 

Attorney General (delegated to the 

Administrator of DEA pursuant to 28 

CFR 0.100) on his own motion, at the 

request of the Secretary of Health and 

Human Services (HHS), or on the 

petition of any interested party.1 This 

action is supported, inter alia, by a 

recommendation from the Assistant 

Secretary for Health of HHS (Assistant 

Secretary for HHS or Assistant 

Secretary) and an evaluation of all other 

relevant data by DEA. This action 

continues the imposition of the 

regulatory controls and administrative, 

civil, and criminal sanctions of schedule 

I controlled substances on any person 

who handles (manufactures, distributes, 

imports, exports, engages in research, or 

conducts instructional activities or 

chemical analysis with, or possesses) or 

proposes to handle butonitazene, 

flunitazene, and metodesnitazene. 

Background 

On April 12, 2022, pursuant to 21 

U.S.C. 811(h)(1), DEA published an 

order in the Federal Register 

temporarily placing butonitazene, 

flunitazene, metodesnitazene, and four 

additional benzimidazole-opioids in 

schedule I of the Controlled Substances 

Act (CSA) based upon a finding that 

these substances pose an imminent 

hazard to the public safety.2 That 

temporary order was effective upon the 

date of publication. Under 21 U.S.C. 

811(h)(2), the temporary scheduling of a 

substance expires at the end of two 

years from the date of issuance of the 

scheduling order, except that DEA may 

extend temporary scheduling of that 

substance for up to one year during the 

pendency of permanent scheduling 

proceedings under 21 U.S.C. 811(a)(1) 

with respect to the substance. Pursuant 

to 21 U.S.C. 811(h)(2), the temporary 

scheduling of butonitazene, flunitazene, 

and metodesnitazene was set to expire 

on April 12, 2024. However, on April 

11, 2024, the DEA Administrator 

extended the temporary order in a 

separate action.3 On the same day, the 

Administrator, on her own motion 

pursuant to 21 U.S.C. 811(a), initiated 

scheduling proceedings and published a 

notice of proposed rulemaking (NPRM) 

to permanently control butonitazene, 

flunitazene, and metodesnitazene in 

schedule I of the CSA.4 Specifically, 

DEA proposed to add these substances 

to the opiates list under 21 CFR 

1308.11(b). 

DEA and HHS Eight Factor Analyses 

On November 15, 2023, the Assistant 

Secretary submitted HHS’s scientific 

and medical evaluation and scheduling 

recommendation for butonitazene, 

flunitazene, metodesnitazene, and three 

other benzimidazole-opioids and their 

salts to the Administrator,5 which 

recommended placing butonitazene, 

flunitazene, and metodesnitazene and 

their salts in schedule I of the CSA. In 

accordance with 21 U.S.C. 811(c), upon 

receipt of the scientific and medical 

evaluation and scheduling 


ddrumheller on DSK120RN23PROD with RULES1