80 FR 66788 - Special Conditions: Honda Aircraft Company (Honda) Model HA-420, HondaJet; Cruise Speed Control System

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 210 (October 30, 2015)

Page Range		66788-66789
FR Document		2015-27700

These special conditions are issued for the Honda Aircraft Company HA-420 airplane. This airplane will have a novel or unusual design feature(s) associated with the use of a cruise speed control system. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

Federal Register, Volume 80 Issue 210 (Friday, October 30, 2015)

[Federal Register Volume 80, Number 210 (Friday, October 30, 2015)]
[Rules and Regulations]
[Pages 66788-66789]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-27700]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. FAA-2015-3880; Special Conditions No. 23-271-SC]


Special Conditions: Honda Aircraft Company (Honda) Model HA-420, 
HondaJet; Cruise Speed Control System

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions.

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SUMMARY: These special conditions are issued for the Honda Aircraft 
Company HA-420 airplane. This airplane will have a novel or unusual 
design feature(s) associated with the use of a cruise speed control 
system. The applicable airworthiness regulations do not contain 
adequate or appropriate safety standards for this design feature. These 
special conditions contain the additional safety standards that the 
Administrator considers necessary to establish a level of safety 
equivalent to that established by the existing airworthiness standards.

DATES: These special conditions are effective October 30, 2015 and are 
applicable on October 26, 2015.

FOR FURTHER INFORMATION CONTACT: Jeff Pretz, Federal Aviation 
Administration, Small Airplane Directorate, Aircraft Certification 
Service, 901 Locust, Room 301, Kansas City, MO 64106; telephone (816) 
329-3239; facsimile (816) 329-4090.

SUPPLEMENTARY INFORMATION:

Background

    On October 11, 2006, Honda Aircraft Company applied for a type 
certificate for their new Model HA-420. On October 10, 2013, Honda 
Aircraft Company requested an extension with an effective application 
date of October 1, 2013. This extension changed the type certification 
basis to amendment 23-62.
    The HA-420 is a four to five passenger (depending on 
configuration), two crew, lightweight business jet with a 43,000-foot 
service ceiling and a maximum takeoff weight of 9963 pounds. The 
airplane is powered by two GE-Honda Aero Engines (GHAE) HF-120 turbofan 
engines.
    The HA-420 airplane will use a cruise speed control system (CSC), 
which is part of the automatic flight control system (AFCS), to reduce 
pilot workload during cruise flight only. The intended function is 
automatic airplane speed control during altitude hold AFCS mode by 
adjustment of the engine thrust within a narrow authority band 
utilizing the existing engine synchronization control. The CSC system 
does not back drive the throttles. The command authority is limited to 
values used for engine synchronization and can only be engaged when the 
throttle is positioned in a pre-determined range typically used for 
cruise power. This significantly reduces the CSC authority such that 
failure modes of the system should be minor. The proposed CSC system 
functions in a manner similar to an auto-throttle system, but has 
significantly less authority when compared to a traditional auto-
throttle system.

Type Certification Basis

    Under the provisions of 14 CFR 21.17, Honda Aircraft Company must 
show that the HA-420 meets the applicable provisions of part 23, as 
amended by amendments 23-1 through 23-62, thereto.
    If the Administrator finds that the applicable airworthiness 
regulations (i.e., 14 CFR part 23) do not contain adequate or 
appropriate safety standards for the HA-420 because of a novel or 
unusual design feature, special conditions are prescribed under the 
provisions of Sec.  21.16.
    In addition to the applicable airworthiness regulations and special 
conditions, the HA-420 must comply with the fuel vent and exhaust 
emission requirements of 14 CFR part 34 and the noise certification 
requirements of 14 CFR part 36. In addition, the FAA must issue a 
finding of regulatory adequacy pursuant to Sec.  611 of Public Law 92-
574, the ``Noise Control Act of 1972.''
    The FAA issues special conditions, as defined in 14 CFR 11.19, in 
accordance with Sec.  11.38, and they become part of the type-
certification basis under Sec.  21.17(a)(2). Special conditions are 
initially applicable to the model for which they are issued. Should the 
type certificate for that model be amended later to include any other 
model that incorporates the same or similar novel or unusual design 
feature, the special conditions would also apply to the other model 
under Sec.  21.101.

Novel or Unusual Design Features

    The HA-420 will incorporate the following novel or unusual design 
features: Cruise Speed Control system

Discussion

    As defined in the summary section, this airplane makes use of a CSC 
system, which is a novel design for this type of airplane. The 
applicable airworthiness

[[Page 66789]]

regulations do not contain adequate or appropriate safety standards for 
this design feature. Mandating additional requirements, developed in 
part by adapting relevant portions of 14 CFR 25.1329, Automatic pilot 
systems, applicable to auto-throttle systems along with FAA experience 
with similar autothrust systems, mitigates the concerns associated with 
installation of the proposed CSC system.

Discussion of Comments

    Notice of proposed special conditions No. 23-15-05-SC for the Honda 
Aircraft Company model HA-420 airplanes was published in the Federal 
Register on September 23, 2015 (80 FR 57312). No comments were 
received; therefore, the special conditions are adopted as proposed.

Applicability

    As discussed above, these special conditions are applicable to the 
HA-420. Should Honda Aircraft Company apply at a later date for a 
change to the type certificate to include another model on the same 
type certificate incorporating the same novel or unusual design 
feature, the special conditions would apply to that model as well.
    Under standard practice, the effective date of final special 
conditions would be 30 days after the date of publication in the 
Federal Register; however, as the certification date for the Honda 
Aircraft Company model HA-420 airplane is imminent, the FAA finds that 
good cause exists to make these special conditions effective upon 
issuance.

Conclusion

    This action affects only certain novel or unusual design features 
on one model of HA-420 airplane. It is not a rule of general 
applicability and affects only the applicant who applied to the FAA for 
approval of these features on the airplane.

List of Subjects in 14 CFR Part 23

    Aircraft, Aviation safety, Signs and symbols.

    The authority citation for these special conditions is as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701, 14 CFR 21.16 and 
21.17; and 14 CFR 11.38 and 11.19.

The Special Conditions

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the following special conditions are issued as part of 
the type certification basis for Honda Aircraft Company HA-420 
airplanes.
    1. Cruise Speed Control.
    In addition to the requirements of Sec. Sec.  23.143, 
Controllability and Maneuverability--General; 23.1309, Equipment, 
systems, and installations; and 23.1329, Automatic pilot system; auto 
throttle systems of limited authority that do not back drive the 
throttles and for which all failure modes are shown to be no greater 
than minor, the following requirements apply:
    (a) Quick disengagement controls for the autothrust functions must 
be provided for each pilot. Quick disengagement controls must be 
readily accessible to each pilot while operating the thrust control 
levers.
    (b) The effects of a failure of the system to disengage the 
autothrust functions when manually commanded by the pilot must be 
assessed in accordance with the requirements of Sec.  23.1309.
    (c) Engagement or switching of the flight guidance system, a mode, 
or a sensor may not cause the autothrust system to effect a transient 
response that alters the airplane's flight path any greater than a 
minor transient, as defined in paragraph (l)(1) of this section.
    (d) Under normal conditions, the disengagement of any automatic 
control function of a flight guidance system may not cause a transient 
response of the airplane's flight path any greater than a minor 
transient.
    (e) Under rare normal and non-normal conditions, disengagement of 
any automatic control function of a flight guidance system may not 
result in a transient any greater than a significant transient, as 
defined in paragraph (l)(2) of this section.
    (f) The function and direction of motion of each command reference 
control (such as CSC) must be plainly indicated on, or adjacent to, 
each control, if necessary to prevent inappropriate use or confusion.
    (g) Under any condition of flight appropriate to its use, the 
flight guidance system may not produce hazardous loads on the airplane, 
nor create hazardous deviations in the flight path. This applies to 
both fault-free operation and in the event of a malfunction, and 
assumes that the pilot begins corrective action within a reasonable 
period of time.
    (h) When the flight guidance system is in use, a means must be 
provided to avoid excursions beyond an acceptable margin from the speed 
range of the normal flight envelope. If the airplane experiences an 
excursion outside this range, a means must be provided to prevent the 
flight guidance system from providing guidance or control to an unsafe 
speed.
    (i) The flight guidance system functions, controls, indications, 
and alerts must be designed to minimize flightcrew errors and confusion 
concerning the behavior and operation of the flight guidance system. 
Means must be provided to indicate the current mode of operation, 
including any armed modes, transitions, and reversions. Selector switch 
position is not an acceptable means of indication. The controls and 
indications must be grouped and presented in a logical and consistent 
manner. The indications must be visible to each pilot under all 
expected lighting conditions.
    (j) Following disengagement of the autothrust function, a caution 
(visual and, unless there are no misleading or hazardous consequences 
associated with its absence, auditory) must be provided to each pilot.
    (k) During autothrust operation, it must be possible for the 
flightcrew to move the thrust levers without requiring excessive force. 
The autothrust may not create a potential hazard when the flightcrew 
applies an override force to the thrust levers.
    (l) For purposes of this section, a transient is a disturbance in 
the control or flight path of the airplane that is not consistent with 
response to flightcrew inputs or environmental conditions.
    (1) A minor transient would not significantly reduce safety margins 
and would involve flightcrew actions that are well within their 
capabilities. A minor transient may involve a slight increase in 
flightcrew workload or some physical discomfort to passengers or cabin 
crew.
    (2) A significant transient may lead to a significant reduction in 
safety margins, an increase in flightcrew workload, discomfort to the 
flightcrew, or physical distress to the passengers or cabin crew, 
possibly including non-fatal injuries. Significant transients do not 
require, in order to remain within or recover to the normal flight 
envelope, any of the following:
    (i) Exceptional piloting skill, alertness, or strength.
    (ii) Forces applied by the pilot which are greater than those 
specified in Sec.  23.143(c).
    (iii) Accelerations or attitudes in the airplane that might result 
in further hazard to secured or non-secured occupants.

    Issued in Kansas City, Missouri, on October 26, 2015.
Mel Johnson
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-27700 Filed 10-29-15; 8:45 am]
BILLING CODE 4910-13-P

66788 Federal Register / Vol. 80, No. 210 / Friday, October 30, 2015 / Rules and Regulations

otherwise provided by the agency for DEPARTMENT OF TRANSPORTATION control during altitude hold AFCS mode
good cause found and published with by adjustment of the engine thrust
the rule.’’ Id. Federal Aviation Administration within a narrow authority band utilizing
The Board finds that use of an the existing engine synchronization
14 CFR Part 23 control. The CSC system does not back
immediately effective interim final rule
[Docket No. FAA–2015–3880; Special drive the throttles. The command
instead of notice and comment
Conditions No. 23–271–SC] authority is limited to values used for
rulemaking is appropriate here because
engine synchronization and can only be
the amendments contained herein engaged when the throttle is positioned
Special Conditions: Honda Aircraft
merely reflect the decision of the Company (Honda) Model HA–420, in a pre-determined range typically used
Federal Circuit in Bernard and are HondaJet; Cruise Speed Control for cruise power. This significantly
necessary to avert any further confusion System reduces the CSC authority such that
regarding the Board’s practice and failure modes of the system should be
procedures governing the right to AGENCY: Federal Aviation minor. The proposed CSC system
discovery in compliance cases. Under Administration (FAA), DOT. functions in a manner similar to an
these circumstances, notice and ACTION: Final special conditions. auto-throttle system, but has
comment rulemaking is unnecessary significantly less authority when
and not required by any public interest. SUMMARY: These special conditions are
compared to a traditional auto-throttle
issued for the Honda Aircraft Company
system.
List of Subjects in 5 CFR Part 1201 HA–420 airplane. This airplane will
have a novel or unusual design Type Certification Basis
Administrative practice and feature(s) associated with the use of a Under the provisions of 14 CFR 21.17,
procedure. cruise speed control system. The Honda Aircraft Company must show
Accordingly, for the reasons set forth applicable airworthiness regulations do that the HA–420 meets the applicable
in the preamble, the Board amends 5 not contain adequate or appropriate provisions of part 23, as amended by
CFR part 1201 as follows: safety standards for this design feature. amendments 23–1 through 23–62,
These special conditions contain the thereto.
PART 1201—PRACTICES AND additional safety standards that the If the Administrator finds that the
PROCEDURES Administrator considers necessary to applicable airworthiness regulations
establish a level of safety equivalent to (i.e., 14 CFR part 23) do not contain
■ 1. The authority citation for 5 CFR that established by the existing adequate or appropriate safety standards
part 1201 continues to read as follows: airworthiness standards. for the HA–420 because of a novel or
DATES: These special conditions are unusual design feature, special
Authority: 5 U.S.C. 1204, 1305, and 7701,
effective October 30, 2015 and are conditions are prescribed under the
and 38 U.S.C. 4331, unless otherwise noted.
applicable on October 26, 2015. provisions of § 21.16.
FOR FURTHER INFORMATION CONTACT: Jeff In addition to the applicable
■ 2. Section 1201.183 is amended by airworthiness regulations and special
adding paragraph (a)(9) to read as Pretz, Federal Aviation Administration,
Small Airplane Directorate, Aircraft conditions, the HA–420 must comply
follows: with the fuel vent and exhaust emission
Certification Service, 901 Locust, Room
§ 1201.183 Procedures for processing 301, Kansas City, MO 64106; telephone requirements of 14 CFR part 34 and the
petitions for enforcement. (816) 329–3239; facsimile (816) 329– noise certification requirements of 14
4090. CFR part 36. In addition, the FAA must
(a) * * * issue a finding of regulatory adequacy
SUPPLEMENTARY INFORMATION: pursuant to § 611 of Public Law 92–574,
(9) Discovery may be undertaken in
accordance with the Board’s regular Background the ‘‘Noise Control Act of 1972.’’
discovery procedures (§§ 1201.71 The FAA issues special conditions, as
On October 11, 2006, Honda Aircraft defined in 14 CFR 11.19, in accordance
through 1201.75 of this part), except Company applied for a type certificate
that unless otherwise directed by the with § 11.38, and they become part of
for their new Model HA–420. On the type-certification basis under
judge, initial discovery requests must be October 10, 2013, Honda Aircraft
served no later than 15 days after the § 21.17(a)(2). Special conditions are
Company requested an extension with initially applicable to the model for
alleged noncomplying party files a an effective application date of October which they are issued. Should the type
response to the petition for enforcement 1, 2013. This extension changed the certificate for that model be amended
as required under paragraph (a)(1) of type certification basis to amendment later to include any other model that
this section. 23–62. incorporates the same or similar novel
* * * * * The HA–420 is a four to five or unusual design feature, the special
passenger (depending on configuration), conditions would also apply to the other
William D. Spencer, two crew, lightweight business jet with model under § 21.101.
Clerk of the Board. a 43,000-foot service ceiling and a
[FR Doc. 2015–27652 Filed 10–29–15; 8:45 am] maximum takeoff weight of 9963 Novel or Unusual Design Features
BILLING CODE 7400–01–P pounds. The airplane is powered by two The HA–420 will incorporate the
GE-Honda Aero Engines (GHAE) HF– following novel or unusual design
120 turbofan engines. features: Cruise Speed Control system
Lhorne on DSK5TPTVN1PROD with RULES

The HA–420 airplane will use a cruise
speed control system (CSC), which is Discussion
part of the automatic flight control As defined in the summary section,
system (AFCS), to reduce pilot workload this airplane makes use of a CSC system,
during cruise flight only. The intended which is a novel design for this type of
function is automatic airplane speed airplane. The applicable airworthiness

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Federal Register / Vol. 80, No. 210 / Friday, October 30, 2015 / Rules and Regulations 66789

regulations do not contain adequate or In addition to the requirements of (i) The flight guidance system
appropriate safety standards for this §§ 23.143, Controllability and functions, controls, indications, and
design feature. Mandating additional Maneuverability—General; 23.1309, alerts must be designed to minimize
requirements, developed in part by Equipment, systems, and installations; flightcrew errors and confusion
adapting relevant portions of 14 CFR and 23.1329, Automatic pilot system; concerning the behavior and operation
25.1329, Automatic pilot systems, auto throttle systems of limited of the flight guidance system. Means
applicable to auto-throttle systems along authority that do not back drive the must be provided to indicate the current
with FAA experience with similar throttles and for which all failure modes mode of operation, including any armed
autothrust systems, mitigates the are shown to be no greater than minor, modes, transitions, and reversions.
concerns associated with installation of the following requirements apply: Selector switch position is not an
the proposed CSC system. (a) Quick disengagement controls for acceptable means of indication. The
the autothrust functions must be controls and indications must be
Discussion of Comments provided for each pilot. Quick grouped and presented in a logical and
Notice of proposed special conditions disengagement controls must be readily consistent manner. The indications
No. 23–15–05–SC for the Honda Aircraft accessible to each pilot while operating must be visible to each pilot under all
Company model HA–420 airplanes was the thrust control levers. expected lighting conditions.
published in the Federal Register on (b) The effects of a failure of the (j) Following disengagement of the
September 23, 2015 (80 FR 57312). No system to disengage the autothrust autothrust function, a caution (visual
comments were received; therefore, the functions when manually commanded and, unless there are no misleading or
special conditions are adopted as by the pilot must be assessed in hazardous consequences associated
proposed. accordance with the requirements of with its absence, auditory) must be
§ 23.1309. provided to each pilot.
Applicability (c) Engagement or switching of the (k) During autothrust operation, it
As discussed above, these special flight guidance system, a mode, or a must be possible for the flightcrew to
conditions are applicable to the HA– sensor may not cause the autothrust move the thrust levers without requiring
420. Should Honda Aircraft Company system to effect a transient response that excessive force. The autothrust may not
apply at a later date for a change to the alters the airplane’s flight path any create a potential hazard when the
type certificate to include another greater than a minor transient, as flightcrew applies an override force to
model on the same type certificate defined in paragraph (l)(1) of this the thrust levers.
incorporating the same novel or unusual section. (l) For purposes of this section, a
design feature, the special conditions (d) Under normal conditions, the transient is a disturbance in the control
would apply to that model as well. disengagement of any automatic control or flight path of the airplane that is not
Under standard practice, the effective function of a flight guidance system may consistent with response to flightcrew
date of final special conditions would not cause a transient response of the inputs or environmental conditions.
be 30 days after the date of publication airplane’s flight path any greater than a (1) A minor transient would not
in the Federal Register; however, as the minor transient. significantly reduce safety margins and
(e) Under rare normal and non-normal would involve flightcrew actions that
certification date for the Honda Aircraft
conditions, disengagement of any are well within their capabilities. A
Company model HA–420 airplane is
automatic control function of a flight minor transient may involve a slight
imminent, the FAA finds that good
guidance system may not result in a increase in flightcrew workload or some
cause exists to make these special
transient any greater than a significant physical discomfort to passengers or
conditions effective upon issuance.
transient, as defined in paragraph (l)(2) cabin crew.
Conclusion of this section. (2) A significant transient may lead to
(f) The function and direction of a significant reduction in safety
This action affects only certain novel
motion of each command reference margins, an increase in flightcrew
or unusual design features on one model
control (such as CSC) must be plainly workload, discomfort to the flightcrew,
of HA–420 airplane. It is not a rule of
indicated on, or adjacent to, each or physical distress to the passengers or
general applicability and affects only
control, if necessary to prevent cabin crew, possibly including non-fatal
the applicant who applied to the FAA
inappropriate use or confusion. injuries. Significant transients do not
for approval of these features on the (g) Under any condition of flight
airplane. require, in order to remain within or
appropriate to its use, the flight
recover to the normal flight envelope,
List of Subjects in 14 CFR Part 23 guidance system may not produce
any of the following:
hazardous loads on the airplane, nor
Aircraft, Aviation safety, Signs and (i) Exceptional piloting skill,
create hazardous deviations in the flight
symbols. alertness, or strength.
path. This applies to both fault-free (ii) Forces applied by the pilot which
The authority citation for these operation and in the event of a
special conditions is as follows: are greater than those specified in
malfunction, and assumes that the pilot § 23.143(c).
Authority: 49 U.S.C. 106(g), 40113, 44701, begins corrective action within a (iii) Accelerations or attitudes in the
14 CFR 21.16 and 21.17; and 14 CFR 11.38 reasonable period of time. airplane that might result in further
and 11.19. (h) When the flight guidance system
hazard to secured or non-secured
is in use, a means must be provided to
The Special Conditions occupants.
avoid excursions beyond an acceptable
Accordingly, pursuant to the margin from the speed range of the Issued in Kansas City, Missouri, on
Lhorne on DSK5TPTVN1PROD with RULES

authority delegated to me by the normal flight envelope. If the airplane October 26, 2015.
Administrator, the following special experiences an excursion outside this Mel Johnson
conditions are issued as part of the type range, a means must be provided to Acting Manager, Small Airplane Directorate,
certification basis for Honda Aircraft prevent the flight guidance system from Aircraft Certification Service.
Company HA–420 airplanes. providing guidance or control to an [FR Doc. 2015–27700 Filed 10–29–15; 8:45 am]
1. Cruise Speed Control. unsafe speed. BILLING CODE 4910–13–P

VerDate Sep<11>2014 14:41 Oct 29, 2015 Jkt 238001 PO 00000 Frm 00005 Fmt 4700 Sfmt 9990 E:\FR\FM\30OCR1.SGM 30OCR1

Document Created: 2015-12-14 15:29:19
Document Modified: 2015-12-14 15:29:19

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final special conditions.
Dates		These special conditions are effective October 30, 2015 and are applicable on October 26, 2015.
Contact		Jeff Pretz, Federal Aviation Administration, Small Airplane Directorate, Aircraft Certification Service, 901 Locust, Room 301, Kansas City, MO 64106; telephone (816) 329-3239; facsimile (816) 329-4090.
FR Citation		80 FR 66788
CFR Associated		Aircraft; Aviation Safety and Signs and Symbols

80 FR 66788 - Special Conditions: Honda Aircraft Company (Honda) Model HA-420, HondaJet; Cruise Speed Control System

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 210 (October 30, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration