Rule2026-00454
Airworthiness Directives; Honda Aircraft Company LLC Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
January 13, 2026
Effective
February 17, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for certain Honda Aircraft Company LLC (Honda) Model HA-420 airplanes. This AD was prompted by the discovery of a gap between the trailing edge wing nut plates and leading edge aileron balance weights being less than the minimum required clearance. This AD requires replacing the affected left and right aileron fixed balance weights with reduced geometry fixed balance weights. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 91 Issue 8 (Tuesday, January 13, 2026)</title>
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[Federal Register Volume 91, Number 8 (Tuesday, January 13, 2026)]
[Rules and Regulations]
[Pages 1241-1243]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-00454]
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Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
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Federal Register / Vol. 91, No. 8 / Tuesday, January 13, 2026 / Rules
and Regulations
[[Page 1241]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-1355; Project Identifier AD-2025-00016-A;
Amendment 39-23229; AD 2026-01-01]
RIN 2120-AA64
Airworthiness Directives; Honda Aircraft Company LLC Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Honda Aircraft Company LLC (Honda) Model HA-420 airplanes. This
AD was prompted by the discovery of a gap between the trailing edge
wing nut plates and leading edge aileron balance weights being less
than the minimum required clearance. This AD requires replacing the
affected left and right aileron fixed balance weights with reduced
geometry fixed balance weights. The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective February 17, 2026.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of February 17,
2026.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-1355; or in person at Docket Operations between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this final rule, any comments received, and other
information. The address for Docket Operations is U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
Material Incorporated by Reference:
<bullet> For Honda Aircraft Company material identified in this AD,
contact Honda, 6430 Ballinger Road, Greensboro, NC 27410; phone: (336)
662-0246; website: <a href="http://hondajet.com">hondajet.com</a>.
<bullet> 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. It is also available at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-1355.
FOR FURTHER INFORMATION CONTACT: Tuan Tran, Aviation Safety Engineer,
FAA, 1701 Columbia Avenue, College Park, GA 30337; phone: (404) 474-
5522; email: <a href="/cdn-cgi/l/email-protection#e0a5a3a2cda3afb3a0868181ce878f96"><span class="__cf_email__" data-cfemail="632620214e202c30230502024d040c15">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain Honda Model HA-
420 airplanes. The NPRM was published in the Federal Register on July
7, 2025 (90 FR 29804). The NPRM was prompted by a production quality
assurance inspection that revealed a gap between the trailing edge wing
nut plates and leading edge aileron balance weights with less than the
minimum required clearance. This reduction could result in jamming or
contact between the balance weights and the nut plates and could
negatively affect flight and cause damage to the airplane. The unsafe
condition, if not addressed, could result in loss of control of the
airplane. In the NPRM, the FAA proposed to require replacing the
affected left and right aileron fixed balance weights with reduced
geometry fixed balance weights. The FAA is issuing this AD to address
the unsafe condition on these products.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from one commenter. The commenter was
Honda. The following presents the comments received on the NPRM and the
FAA's response to each comment.
Request To Revise the Background Paragraph and Unsafe Condition
Honda requested that the FAA remove the mention of potential
jamming between the wing trailing edge nut plates and aileron leading
edge balance weights from the Background paragraph of the proposed AD
and revise the paragraph to read; ``This reduction could result in
contact between the balance weights and nut plates, if not addressed
causing damage to the airplane.'' Honda also requested that the FAA
remove mention of potential jamming and loss of control of the airplane
from paragraph (e) of the proposed AD, and revise the unsafe condition
to read; ``The FAA is issuing this AD to prevent contact between the
balance weights and the nut plates. The unsafe condition, if not
addressed, could result in damage to the airplane.'' Honda noted that
prior to every flight in service, the pilot verifies that all flight
controls are ``free and correct,'' and if ailerons have the potential
to bind, the condition would be caught during these flight control
checks. Honda also noted that multiple aileron travel checks did not
result in reports of interference or jamming on numerous potentially
affected airplanes and the risk of jamming is not substantiated by
operational data.
The FAA disagrees with the request to revise the Background
language because there is still a potential of jamming or interference
between the balance weights and nut plates at maximum aileron
deflection during landing or mid-flight. The FAA notes that the reduced
gap condition still existed in 10 affected airplanes, and there is not
enough substantiated data to show any mitigation effect to the jamming
or interference at maximum aileron deflection. The FAA has not changed
this AD based on this request.
Request To Revise Paragraph (g) ``Required Actions''
Honda requested that the FAA revise paragraph (g) of the proposed
AD, so that before further flight replacement of the balance weights
would only be necessary if interference is found during the clearance
check. The commenter stated that the use of ``before further flight''
is not warranted based on Honda's safety risk assessment since multiple
aileron travel checks did not result in reports of interference or
[[Page 1242]]
jamming on numerous potentially affected airplanes and the risk of
jamming is not substantiated by operational data. Honda also stated
that its requested approach would align with Honda's safety risk
assessment and operational experience, and allow for a targeted
response based on actual findings rather than a blanket requirement
that Honda said may not be necessary. Honda also argued that paragraph
(g)(3) of the proposed AD is not warranted and would only cause delays
for completion of this action because Honda has FAA-approved data that
allows use of the larger balance weights having part number (P/N) HJ1-
15751-137-005, but chose not to include the larger adjustable weight
part number in the parts list of the service bulletin in order to track
utilization of the longer weights. The instructions to install them are
in step (5) Accomplishment Instructions of the Service Bulletin.
Further, the FAA notes that the reduced gap condition still existed
in 10 out of 38 affected airplanes. Even if these 10 airplanes had the
aileron checks done on the issue date of Honda Aircraft Company Service
Bulletin No. SB-420-27-011, Revision B, dated December 12, 2024, they
still require replacement of the affected left and right aileron fixed
balance weights with reduced geometry fixed balance weights before
further flight after the effective date of this AD. Prolonging this
unsafe condition for another 60 days would introduce additional
unnecessary safety risk, and there is not substantiated data to show
any mitigation effect to the jamming or interference at maximum aileron
deflection. The FAA also notes that it is important to ensure that the
ailerons are properly balanced with the appropriate configuration under
an FAA-approved procedure, especially when a mixed combination and
order between different types of balance weight can introduce further
complications and complexity. The FAA has not changed this AD based on
this request.
Request To Remove ``Differences Between This Proposed AD and the
Reference Material'' Paragraph
Honda requested that the FAA remove the ``Differences Between This
Proposed AD and the Reference Material'' paragraph from the proposed
AD. The commenter noted that Honda already uses FAA-approved data that
allows for use of the larger balance weights having P/N HJ1-15751-137-
005, and the information currently in the Differences paragraph of the
proposed AD would cause unnecessary delays.
The FAA disagrees with the request. The FAA acknowledges that Honda
uses FAA-approved data allowing for use of larger balance weights
having P/N HJ1-15751-137-005, but the process for installation of the
balance weight is not appropriately highlighted and detailed in Honda
Aircraft Company Service Bulletin No. SB-420-27-011, Revision B, dated
December 12, 2024. The FAA also notes that it is important to ensure
that the ailerons are properly balanced with the appropriate
configuration under an FAA-approved procedure, especially when a mixed
combination and order between different types of balance weights can
introduce further complications and complexity. The FAA has not changed
this AD based on this request.
Conclusion
The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes, this
AD is adopted as proposed in the NPRM. None of the changes will
increase the economic burden on any operator.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed Honda Aircraft Company Service Bulletin No. SB-
420-27-011, Revision B, dated December 12, 2024. This material
specifies procedures for replacing the affected left and right aileron
fixed balance weights with reduced geometry fixed balance weights to
ensure the minimum required clearances are maintained with the adjacent
wing trailing edge panel fasteners.
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.
Differences Between This AD and the Referenced Material
Honda Aircraft Company Service Bulletin No. SB-420-27-011, Revision
B, dated December 12, 2024, specifies contacting Honda if proper
aileron balance cannot be attained using adjustable balance weights,
but this AD requires using a procedure approved by the Manager, East
Certification Branch, FAA.
Costs of Compliance
The FAA estimates that this AD affects 38 airplanes of U.S.
registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Replace the left and right inboard and 45 work-hours x $85 per $3,676 $7,501 $285,038
outboard fixed balance weights. hour = $3,825.
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The instructions for repair could vary significantly from airplane
to airplane if proper aileron balance cannot be attained using
adjustable balance weights. The FAA has no way of determining the cost
of this repair or the number of airplanes that may require repair.
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
[[Page 1243]]
unsafe condition that is likely to exist or develop on products
identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2026-01-01 Honda Aircraft Company LLC: Amendment 39-23229; Docket
No. FAA-2025-1355; Project Identifier AD-2025-00016-A.
(a) Effective Date
This airworthiness directive (AD) is effective February 17,
2026.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Honda Aircraft Company LLC (Honda) Model HA-
420 airplanes, serial numbers 42000172, 42000235 through 42000265,
and 42000267 through 42000272, certificated in any category, with
aileron balance weight part number HJ1-15751-152-003 or HJ1-15751-
157-003 installed.
(d) Subject
Joint Aircraft System Component (JASC) Code 2710, Aileron
Control System.
(e) Unsafe Condition
This AD was prompted by the discovery that the gap between the
trailing edge wing nut plates and leading edge aileron balance
weights may be less than the minimum required clearance. The FAA is
issuing this AD to prevent jamming or contact between the balance
weights and the nut plates. The unsafe condition, if not addressed,
could result in loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Before further flight after the effective date of this AD,
replace the left and right aileron fixed balance weights in
accordance with steps 3.0(3) through 3.0(8) of the Accomplishment
Instructions in Honda Aircraft Company Service Bulletin No. SB-420-
27-011, Revision B, dated December 12, 2024, except as provided in
paragraphs (g)(1) through (3) of this AD.
(1) Instead of discarding parts, you must remove those parts
from service.
(2) This AD does not require returning parts to the
manufacturer.
(3) Instead of contacting Honda if proper aileron balance cannot
be attained using adjustable balance weights, this AD requires
attaining proper aileron balance using a procedure approved by the
Manager, East Certification Branch, FAA.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, East 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 East Certification Branch, send it to
the attention of the person identified in paragraph (i) of this AD
and email to: <a href="/cdn-cgi/l/email-protection#a3e2eeece0e3c5c2c28dc4ccd5"><span class="__cf_email__" data-cfemail="82c3cfcdc1c2e4e3e3ace5edf4">[email protected]</span></a>.
(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.
(3) For material that contains steps that are labeled as RC the
provisions of paragraphs (h)(3)(i) and (ii) of this AD apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. An AMOC is required for any deviations to RC steps,
including substeps and identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(i) Additional Information
For more information about this AD, contact Tuan Tran, Aviation
Safety Engineer, FAA, 1701 Columbia Avenue, College Park, GA 30337;
phone: (404) 474-5522; email: <a href="/cdn-cgi/l/email-protection#bcf9fffe91fff3effcdadddd92dbd3ca"><span class="__cf_email__" data-cfemail="763335345b3539253610171758111900">[email protected]</span></a>.
(j) 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) Honda Aircraft Company Service Bulletin No. SB-420-27-011,
Revision B, dated December 12, 2024.
(ii) [Reserved]
(3) For Honda Aircraft Company material identified in this AD,
contact Honda Aircraft Company LLC, 6430 Ballinger Road, Greensboro,
NC 27410; phone: (336) 662-0246; website: <a href="http://hondajet.com">hondajet.com</a>.
(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 <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#187e6a3671766b687d7b6c7177765876796a79367f776e"><span class="__cf_email__" data-cfemail="caacb8e4a3a4b9baafa9bea3a5a48aa4abb8abe4ada5bc">[email protected]</span></a>.
Issued on January 8, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2026-00454 Filed 1-12-26; 8:45 am]
BILLING CODE 4910-13-P
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