[Federal Register Volume 85, Number 55 (Friday, March 20, 2020)]
[Rules and Regulations]
[Pages 15926-15930]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-05891]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0195; Product Identifier 2019-CE-052-AD; Amendment
39-21031; AD 2020-04-14]
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: The FAA is adopting a new airworthiness directive (AD) for
certain Honda Aircraft Company LLC (Honda) Model HA-420 airplanes. This
AD requires inspecting the wheel speed transducer (WST) wiring harness,
replacing the wiring harness if necessary, installing wiring hardware,
and rerouting the WST wiring harness on both the left and right brake
assemblies. This AD also requires revising the Abnormal Procedures
section of the airplane flight manual (AFM) and quick reference
handbook (QRH). This AD was prompted by reports of damage to the wiring
harness due to excessive slack in the wiring harness assembly that
allows contact with the main landing gear tire and by the determination
that the AFMs and QRHs contain incorrect procedures for anti-skid
braking system failures. The FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective April 6, 2020.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 6,
2020.
The FAA must receive comments on this AD by May 4, 2020.
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.
[[Page 15927]]
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: 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.
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: https://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 https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0195.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0195; 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 Docket Operations 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
The FAA received a report of a Honda Model HA-420 airplane losing
normal braking during ground operations. Inspections revealed damage to
a brake wiring harness for the WST, which was most likely caused by
contact with the main landing gear tire. A review of manufacturer type
design data and production line assembly instructions revealed that the
wiring harness is installed with excessive slack that allows contact
with the tire when pulled. Thus, the damage found may occur on all in
service Honda Model HA-420 airplanes.
Further investigation revealed that damage to the wiring harness
results in loss of the WST signal, which is interpreted by the digital
antiskid control unit (DACU) as either a WST failure or locked wheel
condition. The DACU provides locked wheel protection, which commands a
full release of normal brakes at speeds greater than 25 knots until the
right and left wheel speeds are within 70 percent of each other. Thus,
when a WST signal is lost, the DACU commands a full normal brake
release until the airplane speed falls below 25 knots. In this
scenario, unavailability of the normal brakes is not annunciated to the
pilot, because WST signal loss does not trigger the NORMAL BRAKE FAIL
red crew alerting system (CAS) message. The pilot is notified via an
ANTI-SKID FAIL amber CAS message. Existing AFM procedures for ANTI-SKID
FAIL instruct the pilot to apply normal brakes gradually to stop the
airplane when the anti-skid system has failed. The current AFM
procedures are incorrect and do not caution the pilot that normal
braking may be unavailable when the ANTI-SKID FAIL amber CAS message
posts or instruct the pilot to use emergency braking.
This condition, if not addressed, could result in unannunciated
loss of normal brakes, reduced directional control during landing
deceleration and ground operations, and loss of control of the airplane
when applying the brakes. The FAA is issuing this AD to address the
unsafe condition on these products.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Pages 3A-178 through 3A-180 from Section 3A--
Abnormal Procedures in Honda Aircraft Company Airplane Flight Manual,
HondaJet, Effectivity: 42000012 through 42000125, Model HA-420, Part
No.: HJ1-29000-003-001, Revision D, dated December 12, 2019; and Pages
3A-178 through 3A-180 from Section 3A--Abnormal Procedures in Honda
Aircraft Company Airplane Flight Manual, HondaJet ELITE, Effectivity:
42000011, 42000126 and after, HondaJet APMG, Effectivity: 42000012
through 42000125 with SB-420-55-001, Model HA-420, Part No.: HJ1-29001-
003-001, Revision B1, dated December 12, 2019. For the specific
airplane serial numbers specified on each document, these pages are
revised pages to the AFMs that provide procedures for the flight crew
when the braking anti-skid system fails.
The FAA also reviewed Page A-126 and Page A-127 from HondaJet,
Model HA-420, HJ1-29000-007-001, Volume 1 of 2, Effectivity 42000012
through 42000125, Quick Reference Handbook, Normal Procedures, Revision
D, dated December 12, 2019; Page A-124 and Page A-125 from HondaJet,
Model HA-420, HJ1-29001-007-001, HondaJet ELITE, Effectivity: 42000011,
42000126 and after, HondaJet APMG, Effectivity: 42000012 through
42000125 with SB-420-55-001, Quick Reference Handbook, Revision B,
dated December 12, 2019. For the specific airplane serial numbers
specified on each document, these pages are revised pages to the QRHs
that provide procedures for the flight crew when the braking anti-skid
system fails.
The FAA also reviewed Honda Aircraft Company Service Bulletin Alert
SB-420-32-008, Revision B, dated November 16, 2019 (Honda SB-420-32-
008, Revision B). This service document contains procedures for
inspecting the condition of the WST wiring harness, replacing the
wiring harness if necessary, installing wiring hardware, and rerouting
the WST wiring harness on both the left and right brake assemblies.
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
The FAA is issuing this AD because the FAA 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 replacing the revised pages in the AFMs and QRHs
applicable to your airplane. This AD also requires accomplishing the
actions specified in Honda SB-420-32-008, Revision B described
previously.
Interim Action
The FAA considers this AD, which addresses anti-skid braking system
failures, an interim action. Honda is developing software changes to
revise the WST logic from the ANTI-SKID FAIL CAS to the NORMAL BRAKES
FAIL CAS. Once this action is developed, approved, and available, the
FAA may consider additional rulemaking.
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
[[Page 15928]]
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 the damage to WST wiring harness is
possible on all affected airplanes due to slack in the harness by type
design and may worsen rapidly after each landing cycle and result in
loss of normal braking if left uncorrected. Additionally, incorrect AFM
and QRH procedures instruct the pilot to use normal braking when it is
unavailable instead of using emergency braking. The FAA has determined
that certain corrective action is necessary before further flight to
address the wiring harness damage that results in loss of normal
braking and to provide pilot notification and guidance on what to
expect and how to react to the ANTI-SKID FAIL CAS message coupled with
the loss of normal brakes. Therefore, the FAA finds good cause that
notice and opportunity for prior public comment are impracticable. In
addition, for the reasons stated above, the FAA finds 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, the FAA invites 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-2020-
0195 and Product Identifier 2019-CE-052-AD at the beginning of your
comments. The FAA specifically invites comments on the overall
regulatory, economic, environmental, and energy aspects of this final
rule. The FAA will consider all comments received by the closing date
and may amend this final rule because of those comments.
The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact the FAA receives about this final rule.
Costs of Compliance
The FAA estimates that this AD affects 116 airplanes of U.S.
registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Revise the Abnormal Procedures 1 work-hour x $85 per Not applicable....... $85 $9,860
section of the AFM. hour = $85.
Revise the QRH.................... 1 work-hour x $85 per Not applicable....... 85 9,860
hour = $85.
Inspect WST wiring harness, 7.5 work-hours x $85 Not applicable....... 637.50 73,950
install hardware and reroute the per hour = $637.50.
WST wiring harness.
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The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
inspection. The FAA has no way of determining the number of aircraft
that might need these replacements:
On-Condition Costs
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Cost per
Action Labor cost Parts cost product
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Replace the WST wiring harness................ *See note below................. $389 $389
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* Note: Since all operators are required to install wiring hardware and reroute the WST wiring harness, there is
no additional labor cost associated with replacing the WST wiring harness.
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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.
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 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 notice and comment,
RFA analysis is not required.
[[Page 15929]]
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.
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):
2020-04-14 Honda Aircraft Company LLC: Amendment 39-21031; Docket
No. FAA-2020-0195; Product Identifier 2019-CE-052-AD.
(a) Effective Date
This AD is effective April 6, 2020.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Honda Aircraft Company LLC Model HA-420
airplanes, serial numbers (S/Ns) 42000011 through 42000184,
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 damage to the wheel speed
transducer wiring harness due to excessive slack in the wiring
harness assembly that allows contact with the main landing gear tire
and the determination that the airplane flight manuals (AFMs) and
quick reference handbooks (QRHs) contain incorrect procedures for
anti-skid braking system failures. The FAA is issuing this AD to
prevent un-annunciated loss of normal brakes and reduced directional
control during landing deceleration and ground operations, which
could lead to a runway excursion.
(f) Compliance
Comply with this AD within the compliance time specified, unless
already done.
(g) Revise the Airplane Flight Manuals and Quick Reference Handbooks
Before further flight after April 6, 2020 (the effective date of
this AD), revise your AFM and your QRH as specified below.
(1) For airplanes with S/Ns 42000012 through 42000125 without
SB-420-55-001: Remove the Abnormal Procedure pages for ANTI-SKID
Fail and replace with Pages 3A-178 through 3A-180 from Section 3A--
Abnormal Procedures in Honda Aircraft Company Airplane Flight
Manual, Model HA-420, Part No.: HJ1-29000-003-001, Revision D, dated
December 12, 2019.
(2) For airplanes with S/Ns 42000012 through 42000125 without
SB-420-55-001: Remove the Abnormal Procedure pages for ANTI-SKID
FAIL and replace with Page A-126 and Page A-127 from Model HA-420,
HJ1-29000-007-001, Volume 1 of 2, Quick Reference Handbook, Normal
Procedures, Revision D, dated December 12, 2019.
(3) For airplanes with S/Ns 42000011, 42000012 through 42000125
with SB-420-55-001, and 42000126 through 42000184: Remove the
Abnormal Procedure pages for ANTI-SKID FAIL and replace with Pages
3A-178 through 3A-180 from Section 3A--Abnormal Procedures in Honda
Aircraft Company Airplane Flight Manual, Model HA-420, Part No.:
HJ1-29001-003-001, Revision B1, dated December 12, 2019.
(4) For airplanes with S/Ns 42000011, 42000012 through 42000125
with SB-420-55-001, and 42000126 through 42000184: Remove the
Abnormal Procedure pages for ANTI-SKID FAIL and replace with Page A-
124 and Page A-125 from Model HA-420, HJ1-29001-007-001, Quick
Reference Handbook, Revision B, dated December 12, 2019.
(h) Corrective Actions for the Wheel Speed Transducer Wiring Harness
Within 90 days after April 6, 2020 (the effective date of this
AD), do the actions specified in steps 1 through 7 of the
Accomplishment Instructions in Honda Aircraft Company Service
Bulletin Alert SB-420-32-008, Revision B, dated November 16, 2019.
(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 provisions of paragraphs
(i)(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 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.
(j) 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].
(k) 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. 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) Pages 3A-178 through 3A-180 from Section 3A--Abnormal
Procedures in Honda Aircraft Company Airplane Flight Manual,
HondaJet, Effectivity: 42000012 through 42000125, Model HA-420, Part
No.: HJ1-29000-003-001, Revision D, dated December 12, 2019.
(ii) Page A-126 and Page A-127 from HondaJet, Model HA-420, HJ1-
29000-007-001, Volume 1 of 2, Effectivity 42000012 through 42000125,
Quick Reference Handbook, Normal Procedures, Revision D, dated
December 12, 2019.
(iii) Pages 3A-178 through 3A-180 from Section 3A--Abnormal
Procedures in Honda Aircraft Company Airplane Flight Manual,
HondaJet ELITE, Effectivity: 42000011, 42000126 and after, HondaJet
APMG, Effectivity: 42000012 through 42000125 with SB-420-55-001,
Model HA-420, Part No.: HJ1-29001-003-001, Revision B1, dated
December 12, 2019.
(iv) Page A-124 and Page A-125 from HondaJet, Model HA-420, HJ1-
29001-007-001, HondaJet ELITE, Effectivity: 42000011, 42000126 and
after, HondaJet APMG, Effectivity: 42000012 through 42000125 with
SB-420-55-001, Quick Reference Handbook, Revision B, dated December
12, 2019.
(v) Honda Aircraft Company Service Bulletin Alert SB-420-32-008,
Revision B, dated November 16, 2019.
(3) For service information identified in this AD, contact Honda
Aircraft Company LLC, 6430 Ballinger Road, Greensboro, North
[[Page 15930]]
Carolina 27410; telephone (336) 662-0246; internet: https://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, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on March 16, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020-05891 Filed 3-19-20; 8:45 am]
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