[Federal Register Volume 86, Number 211 (Thursday, November 4, 2021)]
[Rules and Regulations]
[Pages 60753-60756]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-24097]


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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.

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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 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: [email protected].

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

[[Page 60754]]

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

[[Page 60755]]

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
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Remove, clean, and apply CIC to the  22 work-hours x $85 per                 $70          $1,940         $85,360
 flap control pushrods.               hour = $1,870.
Reapply CIC every 90 days (cost for  1 work-hour x $85 per hour               70             155           6,820
 each time).                          = $85.
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    The FAA has included all known costs in its cost estimate. 
According to the manufacturer, however, some of the costs of this AD 
may be covered under warranty, thereby reducing the cost impact on 
affected operators.

Authority for This Rulemaking

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

Regulatory Findings

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

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 already 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 inspector, 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 Required 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

[[Page 60756]]

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: 
[email protected].

(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, Greensboro, NC 27410; phone: (336) 662-0246; 
website: https://www.hondajet.com.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on October 15, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-24097 Filed 11-3-21; 8:45 am]
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