Rule2026-06527
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
April 3, 2026
Effective
May 8, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2021-22-12 for certain Honda Aircraft Company LLC (Honda) Model HA-420 airplanes. AD 2021-22-12 required removing and cleaning the inner diameter of the flap control pushrod assemblies and repetitively applying corrosion inhibiting compound (CIC) to this area. Since the FAA issued AD 2021- 22-12, new flap control pushrods have been approved that are more corrosion resistant and do not require repetitive CIC applications. In addition, referenced service material has been updated to a new revision that includes redesigned replacement flap control pushrod assemblies that have been modified to prevent interference with adjacent parts. This AD retains the requirements of AD 2021-22-12 and requires replacing the flap control pushrod assemblies with improved design pushrod assemblies for all airplanes affected by AD 2021-22-12, as well as for other airplanes not affected by AD 2021-22-12. 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 64 (Friday, April 3, 2026)</title>
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[Federal Register Volume 91, Number 64 (Friday, April 3, 2026)]
[Rules and Regulations]
[Pages 16821-16824]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-06527]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0485; Project Identifier AD-2024-00670-A;
Amendment 39-23293; AD 2026-06-71]
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 superseding Airworthiness Directive (AD) 2021-22-12
for certain Honda Aircraft Company LLC (Honda) Model HA-420 airplanes.
AD 2021-22-12 required removing and cleaning the inner diameter of the
flap control pushrod assemblies and repetitively applying corrosion
inhibiting compound (CIC) to this area. Since the FAA issued AD 2021-
22-12, new flap control pushrods have been approved that are more
corrosion resistant and do not require repetitive CIC applications. In
addition, referenced service material has been updated to a new
revision that includes redesigned replacement flap control pushrod
assemblies that have been modified to prevent interference with
adjacent parts. This AD retains the requirements of AD 2021-22-12 and
requires replacing the flap control pushrod assemblies with improved
design pushrod assemblies for all airplanes affected by AD 2021-22-12,
as well as for other airplanes not affected by AD 2021-22-12. The FAA
is issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective May 8, 2026.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 8, 2026.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 19,
2021 (86 FR 60753, November 4, 2021).
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-0485; or in person at
[[Page 16822]]
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, 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-2025-0485.
FOR FURTHER INFORMATION CONTACT: Kelly Fichter, Aviation Safety
Engineer, FAA, 1701 Columbia Avenue, College Park, GA 30337: (404) 474-
5544; email: <a href="/cdn-cgi/l/email-protection#f7929495da949884b7919696d9909881"><span class="__cf_email__" data-cfemail="197c7a7b347a766a597f7878377e766f">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2021-22-12, Amendment 39-21785 (86 FR
60753, November 4, 2021) (AD 2021-22-12). AD 2021-22-12 applied to
certain Honda Model HA-420 airplanes. AD 2021-22-12 required removing
and cleaning the inner diameter of the flap control pushrods and
repetitively applying CIC to this area to prevent corrosion. The NPRM
was published in the Federal Register on April 11, 2025 (90 FR 15426).
The NPRM was prompted by the manufacturer developing improved flap
control pushrods that are more corrosion resistant and do not require
repetitive CIC applications. The manufacturer also determined that the
applicability should be expanded to include airplanes with serial
number 42000211, 42000212, and 42000215 through 42000287, as these
airplanes also have an affected flap pushrod assembly installed.
The FAA issued a supplemental notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 to supersede AD 2021-22-12. The SNPRM was
published in the Federal Register on December 23, 2025 (90 FR 60029).
The SNPRM was prompted by the discovery that the updated outboard
corrosion resistant pushrods could interfere with the mid flap drive
arms when fully deployed. As a result of this finding, the manufacturer
published updated service material that includes a modified design of
the flap control pushrod assembly to prevent interference with adjacent
parts. In the SNPRM, the FAA proposed to require retaining all of the
requirements of AD 2021-22-12. The SNPRM also proposed to require
expanding the applicability to include additional airplanes, and
replacing the flap control pushrod assemblies with new corrosion-
resistant flap control pushrod assemblies as terminating action for the
repetitive CIC applications required by AD 2021-22-12. The FAA is
issuing this AD to address the unsafe condition on these products.
Discussion of Final Airworthiness Directive
Comments
The FAA received no comments on the SNPRM or on the determination
of the costs.
Conclusion
The FAA reviewed the relevant data and determined that air safety
requires adopting the AD as proposed. Accordingly, the FAA is issuing
this AD to address the unsafe condition on these products. This AD is
adopted as proposed in the SNPRM.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed Honda Aircraft Company Alert Service Bulletin No.
SB-420-27-009, Revision B, dated August 5, 2025. This material
specifies procedures for replacing the flap control pushrod assemblies
with improved design flap control pushrod assemblies.
This AD also requires Honda Aircraft Company Alert Service Bulletin
No. SB-420-27-008, dated August 31, 2021, which the Director of the
Federal Register approved for incorporation by reference as of November
19, 2021 (86 FR 60753, November 4, 2021).
This material is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD affects 107 airplanes of U.S.
registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
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Cost per
Action Labor cost Parts cost product Cost on U.S. operators
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Remove, clean, and apply CIC to the 22 work-hours x $85 per $70 $1,940 $85,360 (44 airplanes).
flap control pushrod assembly hour = $1,870.
(retained from AD 2021-22-12).
Reapply CIC every 90 days (cost for 1 work-hour x $85 per 70 155 $6,820 (44 airplanes).
each time) (retained from AD 2021- hour = $85.
22-12).
Replace the left and right inboard 22 work-hours x $85 per 5,168 7,038 $753,066 (107
flap control pushrod assemblies. hour = $1,870. airplanes).
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The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some or all 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.
[[Page 16823]]
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:
0
a. Removing Airworthiness Directive 2021-22-12, Amendment 39-21785 (86
FR 60753, November 4, 2021); and
0
b. Adding the following new airworthiness directive:
2026-06-71 Honda Aircraft Company LLC: Amendment 39-23293; Docket
No. FAA-2025-0485; Project Identifier AD-2024-00670-A.
(a) Effective Date
This airworthiness directive (AD) is effective May 8, 2026.
(b) Affected ADs
This AD replaces AD 2021-22-12, Amendment 39-21785 (86 FR 60753,
November 4, 2021) (AD 2021-22-12).
(c) Applicability
This AD applies to the following Honda Aircraft Company LLC
Model HA-420 airplanes, certificated in any category:
(1) Group 1 airplanes: serial numbers 42000153 through 42000158
and 42000160 through 42000206; and
(2) Group 2 airplanes: serial numbers 42000211, 42000212, and
42000215 through 42000287.
(d) Subject
Joint Aircraft System Component (JASC) Code 2752, Trailing Edge
Flap Actuator.
(e) Unsafe Condition
This AD was prompted by a report that the flap pushrod
assemblies are susceptible to corrosion. The FAA is issuing this AD
to prevent failure of the flap control pushrod assembly. The unsafe
condition, if not addressed, could result in uncontrolled and un-
annunciated flap asymmetry with consequent loss of control of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Actions From AD 2021-22-12 for Group 1 Airplanes
(1) Within 90 days after November 19, 2021 (the effective date
of AD 2021-22-12), or 18 months after issuance of the first standard
certificate of airworthiness, whichever occurs later: Remove, clean,
apply corrosion inhibiting compound (CIC) to, and reinstall the left
and right inboard and outboard flap control pushrod assemblies by
following steps (3) through (6) of the Accomplishment Instructions
in Honda Aircraft Company Alert Service Bulletin No. SB-420-27-008,
dated August 31, 2021.
(2) Within 90 days or 300 hours time-in-service (TIS), whichever
occurs first after accomplishing the actions required by paragraph
(g)(1) of this AD, and thereafter at intervals not to exceed 90 days
or 300 hours TIS, whichever occurs first: Reapply CIC by following
step (5)(a) through (c) of the Accomplishment Instructions in Honda
Aircraft Company Alert Service Bulletin No. SB-420-27-008, dated
August 31, 2021.
(h) New Required Actions for Group 1 and Group 2 Airplanes
(1) Within 2 years after the effective date of this AD, replace
the flap control pushrod assemblies with redesigned (zero hours TIS)
flap control pushrod assemblies in accordance with steps (3) through
(5) of the Accomplishment Instructions in Honda Aircraft Company
Alert Service Bulletin No. SB-420-27-009 Revision B, dated August 5,
2025.
(2) For Group 1 airplanes, accomplishing the replacement
required by paragraph (h)(1) of this AD terminates the requirements
of paragraphs (g)(1) and (2) of this AD.
(i) Installation Prohibition
As of the effective date of this AD, do not install on any
airplane, an inboard or outboard flap control pushrod assembly part
number that is identified in the Effectivity section of Honda
Aircraft Company Alert Service Bulletin No. SB-420-27-009 Revision
B, dated August 5, 2025.
(j) No Reporting Requirement
Although Honda Aircraft Company Alert Service Bulletin No. SB-
420-27-008, dated August 31, 2021, and Alert Service Bulletin No.
SB-420-27-009, Revision B, dated August 5, 2025, specify to submit
certain information to the manufacturer, this AD does not include
those requirements.
(k) 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 (l) of this AD
and email to: <a href="/cdn-cgi/l/email-protection#81c0cccec2c1e7e0e0afe6eef7"><span class="__cf_email__" data-cfemail="a8e9e5e7ebe8cec9c986cfc7de">[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
Required for Compliance (RC), the provisions of paragraphs (k)(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.
(l) Additional Information
For more information about this AD, contact Kelly Fichter,
Aviation Safety Engineer, FAA, 1701 Columbia Avenue, College Park,
GA 30337; phone: (404) 474-5544; email: <a href="/cdn-cgi/l/email-protection#026761602f616d71426463632c656d74"><span class="__cf_email__" data-cfemail="2b4e4849064844586b4d4a4a054c445d">[email protected]</span></a>.
(m) 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.
(3) The following material was approved for IBR on May 8, 2026.
(i) Honda Aircraft Company Alert Service Bulletin No. SB-420-27-
009, Revision B, dated August 5, 2025.
(ii) [Reserved]
(4) The following material was approved for IBR on November 19,
2021 (86 FR 60753, November 4, 2021).
(i) Honda Aircraft Company Alert Service Bulletin No. SB-420-27-
008, dated August 31, 2021.
(ii) [Reserved]
(5) 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>.
(6) 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.
[[Page 16824]]
(7) 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#a1c7d38fc8cfd2d1c4c2d5c8cecfe1cfc0d3c08fc6ced7"><span class="__cf_email__" data-cfemail="6006124e090e1310050314090f0e200e0112014e070f16">[email protected]</span></a>.
Issued on March 20, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2026-06527 Filed 4-2-26; 8:45 am]
BILLING CODE 4910-13-P
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