Airworthiness Directives; Honda Aircraft Company LLC

[Federal Register Volume 83, Number 61 (Thursday, March 29, 2018)]
[Rules and Regulations]
[Pages 13401-13404]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-06091]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0223; Product Identifier 2018-CE-007-AD; Amendment 
39-19230; AD 2018-06-10]
RIN 2120-AA64


Airworthiness Directives; Honda Aircraft Company LLC

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Honda Aircraft Company LLC Model HA-420 airplanes. This AD requires 
incorporating a temporary revision into the airplane flight manual and 
replacing faulty power brake valves upon condition. This AD was 
prompted by reports of unannunciated asymmetric braking during ground 
operations and landing deceleration. We are issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective April 13, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 13, 
2018.
    We must receive comments on this AD by May 14, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.

[[Page 13402]]

    For service information identified in this final rule, contact 
Honda Aircraft Company LLC, 6430 Ballinger Road, Greensboro, North 
Carolina 27410; telephone (336) 662-0246; internet: http://www.hondajet.com. You may view this service information at the FAA, 
Policy and Innovation Division, 901 Locust, Kansas City, Missouri 
64106. For information on the availability of this material at the FAA, 
call (816) 329-4148. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0223.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0223; 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, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Operations (phone: 
800-647-5107) is listed above. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Samuel Kovitch, Aerospace Engineer, 
Atlanta ACO Branch, FAA, 1701 Columbia Avenue, College Park, Georgia 
30337; phone: (404) 474-5570; fax: (404) 474-5605; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We received reports of unannunciated asymmetric braking during 
landing deceleration on several Honda Aircraft Company LLC Model HA-420 
airplanes. Investigation revealed that the power brake valve (PBV) 
housing design drawing dimension for a bore diameter, which serves as 
an O-ring gland outer diameter, is oversized from Society of Automotive 
Engineers (SAE) specification guidelines for O-ring gland dimensions. 
The oversized bore allows back-up ring extrusion damage during normal 
operating hydraulic pressure in the valve, O-ring deformation/damage, 
and internal leakage of hydraulic pressure within the PBV from the 
master cylinder brake lines. The damage to the back-up ring and O-ring 
worsens during operation and causes the internal leakage rate of the 
PBV brake master cylinder lines to increase over time. This condition, 
if not addressed, could result in failure of the PBV, which could cause 
degraded braking performance and reduced directional control during 
ground operations and landing deceleration. We are issuing this AD to 
address the unsafe condition on these products.

Related Service Information Under 1 CFR Part 51

    We reviewed Honda Aircraft Company Temporary Revision TR 01.1, 
dated February 16, 2018, to the Honda Aircraft Company HA-420 Airplane 
Flight Manual and Service Bulletin SB-420-32-001, dated January 8, 
2018. Temporary Revision TR 01.1, dated February 16, 2018, to the HA-
420 Airplane Flight Manual (AFM) describes procedures for performing 
pilot checks of the braking system during ground operations before 
every flight and before every landing and includes instructions for 
corrective actions if any indication of a leaking PBV is found. Service 
Bulletin SB-420-32-001, dated January 8, 2018, describes procedures for 
replacing a defective PBV with an improved design PBV. 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 the ADDRESSES section.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires inserting a temporary revision into the AFM, which 
may be performed by the owner/operator (pilot) holding at least a 
private pilot certificate and must be entered into the airplane records 
showing compliance with this AD in accordance with 14 CFR 43.9 (a)(1)-
(4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as 
required by 14 CFR 91.417, 121.380, or 135.439. This AD also requires 
replacing the installed PBV, P/N HJ1-13243-101-005 or P/N HJ1-13243-
101-007, with an improved PBV, P/N HJ1-13243-101-009, if a defective 
PBV is detected during the required pilot checks as specified in the 
temporary revision. In addition, this AD provides an optional 
terminating action for the temporary revision into the AFM by replacing 
the installed PBV with the improved PBV, P/N HJ1-13243-101-009.

Interim Action

    We consider this AD interim action. We are currently considering 
requiring replacement of the installed PBV, P/N HJ1-13243-101-005 or P/
N HJ1-13243-101-007, with an improved part, which will constitute 
terminating action for the temporary revision to the AFM. However, the 
planned compliance time for the replacement of the PBV would allow 
enough time to provide notice and opportunity for prior comment on the 
merit of the replacement.

FAA's Justification and Determination of the Effective Date

    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 waiving notice and comment prior to adoption of this rule 
because failure of the PBV could cause degraded braking performance and 
reduced directional control during ground operations and landing 
deceleration. Therefore, we find good cause that notice and opportunity 
for prior public comment are impracticable. In addition, for the reason 
stated above, we find that good cause exists for making this amendment 
effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite 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 the docket number FAA-2018-
0223 and Product Identifier 2018-CE-007-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this final rule. We will 
consider all comments received by the closing date and may amend this 
final rule because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this final rule.

Costs of Compliance

    We estimate that this AD affects 72 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 13403]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
              Action                      Labor cost             Parts cost           product        operators
----------------------------------------------------------------------------------------------------------------
Insert temporary revision into the  1 work-hour x $85 per  Not applicable.......             $85          $6,120
 airplane flight manual.             hour = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the pilot check of the 
braking system during ground operations before every flight and before 
every landing. We have no way of determining the number of airplanes 
that might need these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace the power brake valve.................  20 work-hours x $85 per hour =           $21,878         $23,578
                                                 $1,700.
----------------------------------------------------------------------------------------------------------------

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.
    We are 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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to small airplanes, gliders, 
balloons, airships, domestic business jet transport airplanes, and 
associated appliances to the Director of the Policy and Innovation 
Division.

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) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

Adoption of 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 (AD):

2018-06-10 Honda Aircraft Company LLC: Amendment 39-19230; Docket 
No. FAA-2018-0223; Product Identifier 2018-CE-007-AD.

(a) Effective Date

    This AD is effective April 13, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Honda Aircraft Company LLC Model HA-420 
airplanes, serial numbers 42000011 through 4200089, that:
    (1) have power brake valve, part number (P/N) HJ1-13243-101-005 
or HJ1-13243-101-007, installed; and
    (2) are certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 32, Landing Gear.

(e) Unsafe Condition

    This AD was prompted by reports of unannunciated asymmetric 
braking during ground operations and landing deceleration. We are 
issuing this AD to detect failure of the power brake valve. The 
unsafe condition, if not addressed, could result in degraded braking 
performance and reduced directional control during ground operations 
and landing deceleration.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Insert Temporary Revision into the Airplane Flight Manual (AFM)

    Before further flight after April 13, 2018 (the effective date 
of this AD) insert Honda Aircraft Company Temporary Revision TR 
01.1, dated February 16, 2018, into the Honda Aircraft Company 
(Honda) HA-420 Airplane Flight Manual (AFM) (the temporary 
revision). This insertion and the steps therein may be performed by 
the owner/operator (pilot) holding at least a private pilot 
certificate and must be entered into the airplane records showing 
compliance with this AD in accordance with 14 CFR 43.9 (a)(1)-(4) 
and 14 CFR 91.417(a)(2)(v). The record must be maintained as 
required by 14 CFR 91.417, 121.380, or 135.439.

(h) Replace the Power Brake Valve (PBV)

    As of and any time after the effective date of this AD, if the 
PBV fails any of the pilot checks specified in the temporary 
revision,

[[Page 13404]]

before further flight, replace the PBV, P/N HJ1-13243-101-005 or P/N 
HJ1-13243-101-007, with the improved design PBV, P/N HJ1-13243-101-
009. Do the replacement using the Accomplishment Instructions in 
Honda Service Bulletin SB-420-32-001, dated January 8, 2018. Before 
further flight after installing P/N HJ1-13243-101-009, remove the 
temporary revision from the Honda HA-420 AFM.

(i) Optional Terminating Action for Inserting the AFM Temporary 
Revision/Pilot Checks

    (1) Instead of inserting the temporary revision or at any time 
after inserting the temporary revision required by paragraph (g) of 
this AD, you may replace the installed PBV, P/N HJ1-13243-101-005 or 
P/N HJ1-13243-101-007, with the improved design PBV, P/N HJ1-13243-
101-009. The replacement must be done using the Accomplishment 
Instructions in Honda Service Bulletin SB-420-32-001, dated January 
8, 2018. Before further flight after installing P/N HJ1-13243-101-
009, remove the temporary revision from the Honda HA-420 AFM.
    (2) If you choose to follow the temporary revision required by 
paragraph (g) of this AD instead of the optional replacement in 
paragraph (i)(1) of this AD, the on-condition replacement required 
by paragraph (h) of this AD is still required before further flight.

(j) No Reporting Requirement

    Although Honda Service Bulletin SB-420-32-001, dated January 8, 
2018, specifies to submit certain information to the manufacturer, 
this AD does not require that action.

(k) Special Flight Permit

    Special flight permits for this AD are prohibited.

(l) 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 (m) 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 provisions of paragraphs (h) 
and (i) 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 this 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.

(m) Related Information

    For more information about this AD, contact Samuel Kovitch, 
Aerospace Engineer, Atlanta ACO Branch, FAA, 1701 Columbia Avenue, 
College Park, Georgia 30337; phone: (404) 474-5570; fax: (404) 474-
5605; email: [email protected].

(n) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 510(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Honda Aircraft Company Temporary Revision TR 01.1, dated 
February 16, 2018, to the Honda Aircraft Company HA-420 Airplane 
Flight Manual.
    (ii) Honda Aircraft Company Service Bulletin SB-420-32-001, 
dated January 8, 2018.
    (3) For Honda Aircraft Company LLC service information 
identified in this AD, contact Honda Aircraft Company LLC, 6430 
Ballinger Road, Greensboro, North Carolina 27410; telephone (336) 
662-0246; internet: http://www.hondajet.com.
    (4) You may view this service information at the FAA, Policy and 
Innovation Division, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
(816) 329-4148.
    (5) You may view the 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, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri, on March 19, 2018.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division, Aircraft Certification 
Service.
[FR Doc. 2018-06091 Filed 3-28-18; 8:45 am]
 BILLING CODE 4910-13-P

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