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2021-22-12 HONDA AIRCRAFT COMPANY LLC:
Amendment 39-21785; Docket No. FAA-2021-0884; Project Identifier AD-2021-00998-A.

(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective November 19, 2021.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies to Honda Aircraft Company LLC Model HA-420  airplanes,
    serial  numbers  42000153   through  42000158  and   42000160  through
    42000206, certificated in any category.

(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.  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 al-
    ready done.

(g) REQUIRED ACTIONS

(1) Within 90 days after the effective date of this AD  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 pushrod
    assemblies  by   following  steps   3.0(3)  through   3.0(6)  of   the
    Accomplishment Instructions in Honda Aircraft Company 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
    3.0(5)(a)  through (c)  of  the  Accomplishment Instructions  in Honda
    Aircraft Company Service Bulletin No. SB-420-27-008,  dated August 31,
    2021.

(i) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The  Manager,  Atlanta ACO 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
    certification  office,  send  it  to  the  attention  of  the   person
    identified in paragraph (j) of this AD.

(2) Before using any approved AMOC,  notify your appropriate principal in-
    spector, or lacking  a principal inspector,  the manager of  the local
    flight standards district office/certificate holding district office.

(3) For service information  that  contains  steps that are labeled as Re-
    quired for Compliance (RC), the following provisions 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.

(j) RELATED INFORMATION

    For more information about this AD,  contact Samuel Kovitch,  Aviation
    Safety Engineer, Atlanta ACO Branch FAA, 1701 Columbia Avenue, College
    Park, GA 30337; phone: (404) 474-5570; email: samuel.kovitch@faa.gov.

(k) MATERIAL INCORPORATED BY REFERENCE

(1) The Director of the Federal Register  approved  the  incorporation  by
    reference of the service information listed in this paragraph under  5
    U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable  to do the actions
    required by this AD, unless the AD specifies otherwise.

(i) Honda Aircraft Company Service Bulletin No. SB-420-27-008 dated August
    31, 2021.

(ii) [Reserved]

(3) For Honda Aircraft Company LLC service information  identified in this
    AD, contact Honda Aircraft Company LLC,  6430 Ballinger Road,  Greens-
    boro, NC 27410;  phone: (336) 662-0246; website: https://www.hondajet.
    com.

(4) You may view this service information at the FAA,  Airworthiness Prod-
    ucts Section, Operational Safety Branch,  901 Locust,  Kansas City, MO
    64106. For information on the availability of this material at the FAA
    call 816-329-4148.

(5) You may view this service information  that is incorporated  by refer-
    ence at the National Archives and Records Administration  (NARA).  For
    information on the availability of this material  at NARA,  email: fr.
    inspection@nara.gov,   or   go  to:  https://www.archives.gov/federal-
    register/cfr/ibr-locations.html.

Issued on October 15, 2021. Lance T Gant, Director, Compliance & Airworth-
iness Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Samuel Kovitch, Aviation Safety Engineer,
Atlanta ACO Branch,  FAA,  1701 Columbia Avenue,  College Park, GA  30337;
phone: (404) 474-5570; email: samuel.kovitch@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39


[Docket No. FAA-2021-0884; Project Identifier AD-2021-00998-A;
Amendment 39-21785; AD 2021-22-12]
RIN 2120-AA64

Airworthiness Directives; Honda Aircraft Company LLC Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

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 a report that the flap pushrod assemblies are
susceptible to corrosion. This AD requires removing and cleaning the
inner diameter of the flap control pushrods and repetitively applying
corrosion inhibiting compound (CIC) to this area. The FAA is issuing
this AD to address the unsafe condition on these products.

DATES: This AD is effective November 19, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 19,
2021.
The FAA must receive comments on this AD by December 20, 2021.

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 https://www.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.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this final rule, contact
Honda Aircraft Company LLC, 6430 Ballinger Road, Greensboro, NC 27410;
phone: (336) 662-0246; website: https://www.hondajet.com. You may view
this service information 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 (816)
329-4148. It is also available at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0884.

Examining the AD Docket

You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0884; 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 the
Docket Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Samuel Kovitch, Aviation Safety
Engineer, Atlanta ACO Branch, FAA, 1701 Columbia Avenue, College Park,
GA 30337; phone: (404) 474-5570; email: samuel.kovitch@faa.gov.

SUPPLEMENTARY INFORMATION:

Background

The FAA was informed by Honda that the inner diameter of the flap
control pushrod assemblies for certain Honda Model HA-420 airplanes are
susceptible to corrosion, reducing the capability of the flap control
pushrod to withstand normal operating conditions and resulting in its
eventual failure. The corrosion was initially discovered during
scheduled maintenance when a visual inspection of the flap control
pushrod assemblies revealed signs of corrosion at the drain holes of
the welded tube center section of inboard and outboard assemblies. Later
borescope inspections of the same airplane inside the welded tube
section revealed pitting and discoloration of interior walls. On a
later scheduled inspection of another airplane, similar corrosion was
noted.
While the specific root cause of the corrosion is still under
investigation, the flap control pushrods on the affected airplanes are
susceptible to corrosion because the material of the pushrod is a low-
alloy steel that had incomplete coverage of primer and CIC in the inner
diameter. This incomplete coverage is potentially due to welding
process spillover material creating voids that the primer could not
reach and is exacerbated by general incomplete application. Drainage
holes in the flap pushrod allow the external environment direct access
to the inner diameter of the tube, exposing the improperly treated
surface to the elements. As a result, corrosion may begin to develop
immediately after the airplane enters service.
As a large majority of the fleet have been in service for longer
than 12 months, during which time corrosion has progressed, the FAA
finds the need for immediate action to preclude failure of the flap
control pushrod. The compliance time of this AD prioritizes the
affected fleet by risk and simultaneously requires all airplanes to be
serviced as soon as possible.
Failure of a flap control pushrod, if not prevented, could result
in uncontrolled and un-annunciated flap asymmetry, which could result
in loss of control of the airplane. The FAA is issuing this AD to
address the unsafe condition on these products.

FAA's Determination

The FAA is issuing this AD because the agency has determined the
unsafe condition described previously is likely to exist or develop in
other products of the same type design.

Related Service Information Under 1 CFR Part 51


The FAA reviewed Honda Aircraft Company Service Bulletin No. SB-
420-27-008, dated August 31, 2021. This service information specifies
procedures for removing and cleaning the inner diameter of the flap
control pushrods and repetitively applying CIC to this area. This
service information is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in ADDRESSES.

AD Requirements

This AD requires accomplishing the actions specified in the service
information already described.

Interim Action

The FAA considers this AD to be an interim action. Honda is
currently considering implementing design changes to preclude the need
for repetitively applying CIC and more permanently address the unsafe
condition identified in this AD. Once these design changes are
developed, approved, and available, the FAA may consider additional
rulemaking.

Justification for Immediate Adoption and Determination of the Effective
Date


Section 553(b)(3)(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 foregoing notice and comment prior to adoption of this rule
because the corrosion reduces the fatigue life and potentially
initiates cracks in the pushrod. Crack propagation in a steel part
could lead to immediate failure, resulting in un-annunciated,
uncontrolled, and unrecoverable flap asymmetry. Because there is no
primer or CIC on the affected part to prevent the corrosion from
developing and worsening, the corrosion may appear immediately in
service. As a large majority of the fleet has been in service for 12 to
24 months, during which time the corrosion has progressed, it is
necessary to mitigate this unsafe condition by requiring the corroded
pushrods to be serviced immediately. Also essential to correct the
unsafe condition in the interim while a long term solution is developed
is a requirement to reapply the CIC every 90 days to prevent the
corrosion from developing further. Accordingly, notice and opportunity
for prior public comment are impracticable and contrary to the public
interest pursuant to 5 U.S.C. 553(b)(3)(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 forego notice and
comment.

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
ADDRESSES. Include ``Docket No. FAA-2021-0884 and Project Identifier
AD-2021-00998-A'' 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
https://www.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 Samuel
Kovitch, Aviation Safety Engineer, Atlanta ACO Branch, FAA, 1701
Columbia Avenue, College Park, GA 30337. Any commentary that the FAA
receives which is not specifically designated as CBI will be placed in
the public docket for this rulemaking.

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 44 airplanes of U.S.
registry.
The FAA estimates the following costs to comply with this AD:

Estimated Costs

Action
Labor cost
Parts cost
Cost per product
Cost on U.S. operators
Remove, clean, and apply CIC to the flap control pushrods 22 work-hours x $85 per hour = $1,870
$70
$1,940
$85,360
Reapply CIC every 90 days (cost for each time) 1 work-hour x $85 per hour = $85
70
155
6,820

The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected operators.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.

Regulatory Findings


This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866, and
(2) Will not affect intrastate aviation in Alaska.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

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

Sec. 39.13 [Amended]


2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive: