[Federal Register Volume 90, Number 157 (Monday, August 18, 2025)]
[Rules and Regulations]
[Pages 40038-40041]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-15688]
[[Page 40038]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-0230; Project Identifier AD-2023-01064-A,Q,T;
Amendment 39-23107; AD 2025-16-09]
RIN 2120-AA64
Airworthiness Directives; Various Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
airplanes with certain Pacific Scientific Company rotary buckle
assemblies (buckles) installed. This AD was prompted by a report of a
manufacturing defect in the screws used inside the buckle. This AD
requires inspecting the buckle screws, and depending on the results,
reidentifying the buckle, replacing the screws and reidentifying the
buckle, or replacing the buckle. This AD also allows optionally
prohibiting use of the seat until the actions required by this AD are
accomplished. This AD also prohibits installing certain buckles on any
airplane. The FAA is issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective September 22, 2025.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 22,
2025.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2024-0230; 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 address for Docket Operations is U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
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: [email protected]; website:
Meggitt.com/services_and_support/customer_experience/update-on-buckle-assembly-service-bulletins.
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. It is also available at regulations.gov under
Docket No. FAA-2024-0230.
FOR FURTHER INFORMATION CONTACT: David Kim, Aviation Safety Engineer,
FAA, 3960 Paramount Boulevard, Lakewood, CA 90712; phone: 562-627-5274;
email: [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to all airplanes 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 installed having a date of manufacture (DOM) between January
2012 and September 2012 inclusive, or an unknown DOM. The NPRM was
published in the Federal Register on February 29, 2024 (89 FR 14783).
The NPRM was prompted by a report of a manufacturing defect in the
screws used inside the buckle. In the NPRM, for airplanes with the
identified buckle, the FAA proposed to require inspecting the buckle
screws, and depending on the results of that screw inspection,
replacing the screws and reidentifying the buckle, or replacing the
buckle.
The FAA issued a supplemental notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an AD that would apply to all
airplanes with a restraint system with a Pacific Scientific Company
rotary buckle assembly (buckle) P/N 1111475 (all dash numbers) or P/N
1111548-01 installed having a DOM between January 2012 and April 2013
inclusive, or an unknown DOM. The SNPRM was published in the Federal
Register on February 11, 2025 (90 FR 9293). The SNPRM was prompted by
discovery that an additional lot of screws are affected by the unsafe
condition. The SNPRM proposed to require the same actions as those
proposed in the NPRM, but with a broader applicability and updated
service information. As an alternative, the SNPRM also proposed to
allow 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 would then be
prohibited until the proposed actions are accomplished and the male
side from the lap of the restraint system assembly is reinstalled.
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.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from Boeing and United Airlines who
supported the SNPRM without change.
The FAA received additional comments from three commenters,
including Delta Air Lines (Delta) and American Airlines (American). The
following presents the comments received on the SNPRM and the FAA's
response to each comment.
Request To Apply Distinct P/N for Modified Buckles
An individual commenter requested the FAA revise the SNPRM to
require identifying the buckle with a distinct P/N and/or more durable
label. The commenter stated that the current labeling system wears off
over time, potentially increasing the risk of confusion regarding
compliance status. Further, the commenter contended that a unique
identifier for compliant buckles would prevent unnecessary reinspection
and improve long-term regulatory adherence.
The FAA disagrees. As the FAA stated in the SNPRM, the manufacturer
introducing a new P/N for newly-manufactured parts is ideal; however,
the FAA cannot mandate a company to change a P/N for an article.
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 would be required
to comply with the AD actions. The DOM marking was added to buckle P/N
1111475 (all dash numbers) starting in September 2012, while buckle P/N
1111548-01 has always been marked with the DOM. Additionally, part
marking preservation and reidentification is the responsibility of the
operators. No change has been made to this AD as a result of this
comment.
Request To Clarify Screw Replacement Requirement
American requested that the FAA clarify whether all four screws
must be replaced if at least one of the four screws has a Torx head.
American noted that the ``Differences Between This SNPRM and the
Referenced Material'' section of the SNPRM stated that all four screws
must be replaced with hex head screws if any number of Torx head
[[Page 40039]]
screws are found, but that the required actions specify replacement of
only Torx head screws. American stated it was not sure if a buckle
would have a mix of screws. Delta requested that the FAA revise
paragraphs (g)(1)(ii)(B) and (g)(2)(ii)(B) of the proposed AD to
require replacing all four screws if at least one of the fours screws
is found to have a Torx head. Delta explained that the current language
might lead operators to interpret that only Torx head screws found need
to be replaced, rather than all four, as stated in the referenced
material.
The FAA agrees to clarify the screw replacement requirement in this
AD and disagrees with the request to require replacement of all four
screws if at least one of the four screws has a Torx head. Although the
material referenced in this AD specifies replacing all four screws if
at least one screw is a Torx head, this AD only requires the
replacement of Torx head screws. Hex head screws are not subject to the
unsafe condition and therefore do not need to be replaced for the
buckle to be considered airworthy.
No change is necessary to this AD regarding these comments.
Request To Extend Compliance Time
An individual commenter requested that the FAA extend the proposed
12-month compliance time to a compliance time of 18 to 24 months, due
to constraints such as parts availability and fleet size. The commenter
stated that the FAA's assertion that replacement parts are readily
available may not fully account for global supply chain delays.
The FAA disagrees. The FAA determined the proposed 12-month
compliance time after factoring the time needed to process the proposed
AD before issuance of the final rule, as well as after evaluating the
associated safety risks. According to the manufacturer, an ample number
of spare parts and screws are in stock and will be available to modify
the U.S. fleet within the required compliance time. To the extent spare
parts may become unavailable, the FAA cannot base AD actions upon parts
availability. While every effort is made to avoid grounding airplanes,
the FAA must address the unsafe condition. The FAA did not make any
changes to this final rule as a result of this comment.
Conclusion
The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed Parker Meggitt Service Bulletin SB 1111475-25-001-
2023 and SB 1111548-25-001-2023, both Revision 002, both dated April 1,
2024. 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), 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. These documents are distinct since they
apply to different airplane configurations. 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.
Costs of Compliance
The FAA estimates that this AD affects 21,313 buckles installed on
restraint systems on airplanes worldwide. The FAA has no way of knowing
the number of airplanes 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 airplanes worldwide. Labor rates are
estimated at $85 per work-hour. Based on these numbers, the FAA
estimates the following costs to comply with this AD:
Estimated Costs
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Cost per
Action Labor cost Parts cost buckle Cost on U.S. operators
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Inspecting a buckle............... .1 work-hour x $85 $0 $9 Up to $191,817.
per hour = $9.
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Estimated Costs for Optional Actions
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Action Labor cost Parts cost Cost per product
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Removing male side of lap belt and placarding 1.5 work-hours x $85 per hour = nominal $128
seat inoperative. $128.
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The FAA estimates the following costs to do any necessary repairs
that would be required based on the results of the inspection. The
agency has no way of determining the number of buckles that might need
this repair:
On-Condition Costs
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Action Labor cost Parts cost Cost per buckle
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Replacing a set of screws (four).. .5 work-hour x $85 nominal................. $43.
per hour = $43.
Replacing a buckle................ .5 work-hour x $85 $740.................... 783.
per hour = $43.
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Reidentifying a buckle............ minimal.............. nominal................. nominal.
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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,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will 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 Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2025-16-09 Various Airplanes: Amendment 39-23107; Docket No. FAA-
2024-0230; Project Identifier AD-2023-01064-A,Q,T.
(a) Effective Date
This airworthiness directive (AD) is effective September 22,
2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all airplanes, 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 installed 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, The
Boeing Company model airplanes.
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
helicopters; however, the FAA determined that a shorter compliance
time to accomplish the required actions is required for buckles
installed on helicopters. Accordingly, the FAA published a separate
AD (AD 2024-20-04, Amendment 39-22863 (89 FR 85040, October 25,
2024)) to address all helicopters with an affected buckle installed.
(d) Subject
Air Transport Association (ATA) of America Code: 25, Equipment/
Furnishings, or Joint Aircraft System Component (JASC) Code 2500,
Cabin Equipment/Furnishings; 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 airplanes with buckle P/N 1111475 (all dash numbers),
within 12 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 airplanes with buckle P/N 1111548-01, within 12 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
[[Page 40041]]
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) 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 12 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) Parts Installation Prohibition
As of the effective date of this AD, do not install a buckle
identified in paragraph (c) of this AD on any airplane unless the
buckle is marked with ``MOD. A'' or ``INS. A.''
(i) Credit for Previous Actions
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.
(j) 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 (k) of this AD.
Information may be emailed to: [email protected].
(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 David Kim, Aviation
Safety Engineer, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712;
phone: 562-627-5274; email: [email protected].
(l) 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 the AD specifies otherwise.
(i) Parker Meggitt Service Bulletin SB 1111475-25-001-2023,
Revision 002, dated April 1, 2024.
(ii) Parker Meggitt Service Bulletin SB 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: [email protected]; website:
meggitt.com/services_and_support/customer_experience/update-on-
buckle-assembly-service-bulletins.
(4) You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th
Street, Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195.
(5) You may view this material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].
Issued on August 12, 2025.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2025-15688 Filed 8-15-25; 8:45 am]
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