Airworthiness Directives; Various Helicopters, 85040-85047 [2024-24756]
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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.
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(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
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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.
DEPARTMENT OF TRANSPORTATION
(k) Additional Information
[Docket No. FAA–2024–2328; Project
Identifier AD–2024–00282–Q,R; Amendment
39–22863; AD 2024–20–04]
(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]
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Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; Various
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
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.
SUMMARY:
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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:
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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.
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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
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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.
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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
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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
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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.
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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
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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
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85043
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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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
ddrumheller on DSK120RN23PROD with RULES1
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
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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
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Sfmt 4700
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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ddrumheller on DSK120RN23PROD with RULES1
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)
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15:46 Oct 24, 2024
Jkt 265001
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
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
85045
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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Federal Register / Vol. 89, No. 207 / Friday, October 25, 2024 / Rules and Regulations
(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.
ddrumheller on DSK120RN23PROD with RULES1
(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
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15:46 Oct 24, 2024
Jkt 265001
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
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Fmt 4700
Sfmt 4700
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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(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
Drug Enforcement
Administration, Department of Justice.
ACTION: Final rule.
AGENCY:
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.
ddrumheller on DSK120RN23PROD with RULES1
SUMMARY:
DATES:
Effective October 25, 2024.
Dr.
Terrence L. Boos, Drug and Chemical
Evaluation Section, Diversion Control
FOR FURTHER INFORMATION CONTACT:
VerDate Sep<11>2014
15:46 Oct 24, 2024
Jkt 265001
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-(4butoxybenzyl)-5-nitro-1H-benzimidazol1-yl)-N,N-diethylethan-1-amine),
• Flunitazene (N,N-diethyl-2-(2-(4fluorobenzyl)-5-nitro-1H-benzimidazol1-yl)ethan-1-amine),
• Metodesnitazene (N,N-diethyl-2-(2(4-methoxybenzyl)-1H-benzimidazol-1yl)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
1 21
U.S.C. 811(a).
Schedules of Controlled Substances:
Temporary Placement of Butonitazene,
Etodesnitazene, Flunitazene, Metodesnitazene,
2 See
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
85047
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
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.
3 See 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).
4 See 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).
E:\FR\FM\25OCR1.SGM
25OCR1
Agencies
[Federal Register Volume 89, Number 207 (Friday, October 25, 2024)]
[Rules and Regulations]
[Pages 85040-85047]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-24756]
-----------------------------------------------------------------------
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.
[[Page 85041]]
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: [email protected]; website:
meggitt.com/services_and_support/customer_experience/update-on-buckle-assembly-service-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: [email protected].
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: [email protected]. 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
[[Page 85042]]
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/update-onbuckle-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 [email protected].
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
[[Page 85043]]
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 non-operational 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
[[Page 85044]]
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.
[[Page 85045]]
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
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:
0
a. Removing Airworthiness Directive 2024-01-11, Amendment 39-22662 (89
FR 6008, January 31, 2024); and
0
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.
[[Page 85046]]
(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: [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.
(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: [email protected].
(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.
[[Page 85047]]
(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: [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, 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 [email protected].
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