80_FR_17374 80 FR 17312 - Special Conditions: Honda Aircraft Company (Honda) Model HA-420, HondaJet; Full Authority Digital Engine Control (FADEC) System

80 FR 17312 - Special Conditions: Honda Aircraft Company (Honda) Model HA-420, HondaJet; Full Authority Digital Engine Control (FADEC) System

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 62 (April 1, 2015)

Page Range17312-17313
FR Document2015-07502

These special conditions are issued for the Honda Aircraft Company HA-420 airplane. This airplane will have a novel or unusual design feature associated with the use of an electronic engine control system instead of a traditional mechanical 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 62 (Wednesday, April 1, 2015)
[Federal Register Volume 80, Number 62 (Wednesday, April 1, 2015)]
[Rules and Regulations]
[Pages 17312-17313]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-07502]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. FAA-2015-0723; Special Conditions No. 23-264-SC]


Special Conditions: Honda Aircraft Company (Honda) Model HA-420, 
HondaJet; Full Authority Digital Engine Control (FADEC) System

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

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

SUMMARY: These special conditions are issued for the Honda Aircraft 
Company HA-420 airplane. This airplane will have a novel or unusual 
design feature associated with the use of an electronic engine control 
system instead of a traditional mechanical 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: The effective date of these special conditions is April 1, 2015, 
and is applicable on March 25, 2015.
    We must receive your comments by May 1, 2015.

ADDRESSES: Send comments identified by docket number [FAA-2015-0723] 
using any of the following methods:
    [squ] Federal eRegulations Portal: Go to http://www.regulations.gov 
and follow the online instructions for sending your comments 
electronically.
    [squ] Mail: Send comments to Docket Operations, M-30, U.S. 
Department of Transportation (DOT), 1200 New Jersey Avenue SE., Room 
W12-140, West Building Ground Floor, Washington, DC, 20590-0001.
    [squ] Hand Delivery of Courier: Take comments to Docket Operations 
in Room W12-140 of the West Building Ground Floor at 1200 New Jersey 
Avenue SE., Washington, DC, between 9 a.m., and 5 p.m., Monday through 
Friday, except Federal holidays.
    [squ] Fax: Fax comments to Docket Operations at 202-493-2251.
    Privacy: The FAA will post all comments it receives, without 
change, to http://regulations.gov, including any personal information 
the commenter provides. Using the search function of the docket Web 
site, anyone can find and read the electronic form of all comments 
received into any FAA docket, including the name of the individual 
sending the comment (or signing the comment for an association, 
business, labor union, etc.). DOT's complete Privacy Act Statement can 
be found in the Federal Register published on April 11, 2000 (65 FR 
19477-19478), as well as at http://DocketsInfo.dot.gov.
    Docket: Background documents or comments received may be read at 
http://www.regulations.gov at any time. Follow the online instructions 
for accessing the docket or go to the Docket Operations in Room W12-140 
of the West Building Ground Floor at 1200 New Jersey Avenue SE., 
Washington, DC, between 9 a.m., and 5 p.m., Monday through Friday, 
except Federal holidays.

FOR FURTHER INFORMATION CONTACT: John G. VanHoudt, Federal Aviation 
Administration, Aircraft Certification Service, Small Airplane 
Directorate, ACE-111, 901 Locust, Kansas City, Missouri 64106; 816-329-
4142, fax 816-329-4090.

SUPPLEMENTARY INFORMATION: The FAA has determined, in accordance with 5 
U.S. Code Sec. Sec.  553(b)(3)(B) and 553(d)(3), that notice and 
opportunity for prior public comment hereon are unnecessary because the 
substance of these special conditions has been subject to the public 
comment process in several prior instances with no substantive comments 
received. The FAA therefore finds that good cause exists for making 
these special conditions effective upon issuance.

------------------------------------------------------------------------
        Special condition number              Company/airplane model
------------------------------------------------------------------------
23-237-SC..............................  Spectrum Aeronautical Model S-
                                          40.
23-246-SC..............................  Cirrus Design Corporation Model
                                          SF50.
23-253-SC..............................  Diamond Aircraft Industries
                                          Model DA-40NG.
------------------------------------------------------------------------

Comments Invited

    We invite interested people to take part in this rulemaking by 
sending written comments, data, or views. The most helpful comments 
reference a specific portion of the special conditions, explain the 
reason for any recommended change, and include supporting data. We ask 
that you send us two copies of written comments.
    We will consider all comments we receive on or before the closing 
date for comments. We will consider comments filed late if it is 
possible to do so without incurring expense or delay. We may change 
these special conditions based on the comments we receive.

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 an electronic engine control system 
(FADEC) instead of a traditional mechanical control system. Even though 
the engine control system will be

[[Page 17313]]

certificated as part of the engine, the installation of an engine with 
an electronic control system requires evaluation due to critical 
environmental effects and possible effects on or by other airplane 
systems. For example, indirect effects of lightning, radio interference 
with other airplane electronic systems, shared engine and airplane data 
and power sources.
    The regulatory requirements in 14 CFR part 23 for evaluating the 
installation of complex systems, including electronic systems and 
critical environmental effects, are contained in Sec.  23.1309. 
However, when Sec.  23.1309 was developed, the use of electronic 
control systems for engines was not envisioned. Therefore, Sec.  
23.1309 requirements were not applicable to systems certificated as 
part of the engine (reference Sec.  23.1309(f)(1)). Parts of the system 
that are not certificated with the engine could be evaluated using the 
criteria of Sec.  23.1309. However, the integral nature of these 
systems makes it unfeasible to evaluate the airplane portion of the 
system without including the engine portion of the system.
    In some cases, the airplane that the engine is used in will 
determine a higher classification than the engine controls are 
certificated for; requiring the FADEC systems be analyzed at a higher 
classification. As of November 2005, FADEC special conditions mandated 
the classification for Sec.  23.1309 analyses for loss of FADEC control 
as catastrophic for any airplane using FADEC. This is not to imply an 
engine failure is classified as catastrophic, but that the digital 
engine control must provide an equivalent reliability to mechanical 
engine controls.

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 model 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 Sec.  11.19, under 
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 novel or 
unusual design feature, the special conditions would also apply to the 
other model under the provisions of Sec.  21.101(a)(1).

Novel or Unusual Design Features

    The HA-420 will incorporate the following novel or unusual design 
features: Electronic engine control system.

Discussion

    As defined in the summary section, this airplane makes use of an 
electronic engine control system instead of a traditional mechanical 
control system is a novel design for this type of airplane. The 
applicable airworthiness regulations do not contain adequate or 
appropriate safety standards for this design feature. Mandating a 
structured assessment to determine potential installation issues 
mitigates the concerns that the addition of a full authority engine 
controller does not produce a failure condition not previously 
considered.

Applicability

    As discussed above, these special conditions are applicable to the 
model HA-420. Should Honda Aircraft Company apply at a later date for a 
change to the type certificate to include another model incorporating 
the same novel or unusual design feature, the special conditions would 
apply to that model as well.

Conclusion

    This action affects only certain novel or unusual design features 
on the model HA-420 airplanes. It is not a rule of general 
applicability and it affects only the applicant who applied to the FAA 
for approval of these features on the airplane.
    The substance of these special conditions has been subjected to the 
notice and comment period in several prior instances, identified above, 
and has been derived without substantive change from those previously 
issued. It is unlikely that prior public comment would result in a 
significant change from the substance contained herein. Therefore, 
notice and opportunity for prior public comment hereon are unnecessary 
and the FAA finds good cause, in accordance with 5 U.S. Code Sec. Sec.  
553(b)(3)(B) and 553(d)(3), making these special conditions effective 
upon issuance. The FAA is requesting comments to allow interested 
persons to submit views that may not have been submitted in response to 
the prior opportunities for comment described above.

List of Subjects in 14 CFR Part 23

    Aircraft, Aviation safety, Signs and symbols.

Citation

    The authority citation for these special conditions is as follows:

    Authority: 49 U.S.C. 106(g), 40113 and 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 model HA-420 
airplanes.

1. Electronic Engine Control

    a. The installation of the electronic engine control system must 
comply with the requirements of Sec.  23.1309(a) through (d) at 
amendment 23-62. The intent of this requirement is not to reevaluate 
the inherent hardware reliability of the control itself, but rather 
determine the effects, including environmental effects addressed in 
Sec.  23.1306 and 23.1308 on the airplane systems and engine control 
system when installing the control on the airplane. When appropriate, 
engine certification data may be used when showing compliance with this 
requirement; however, the effects of the installation on this data must 
be addressed.
    b. For these evaluations, the loss of FADEC control will be 
analyzed utilizing the threat levels associated with a catastrophic 
failure.

    Issued in Kansas City, Missouri on March 25, 2015.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-07502 Filed 3-31-15; 8:45 am]
 BILLING CODE 4910-13-P



                                             17312             Federal Register / Vol. 80, No. 62 / Wednesday, April 1, 2015 / Rules and Regulations

                                             processed as defined in Federal Motor                   engine control system instead of a                    ACE–111, 901 Locust, Kansas City,
                                             Vehicle Safety Standard (FMVSS) part                    traditional mechanical control system.                Missouri 64106; 816–329–4142, fax
                                             571.214, section S6.13.5.                               The applicable airworthiness                          816–329–4090.
                                                (4) Pelvis: Pelvic lateral acceleration              regulations do not contain adequate or                SUPPLEMENTARY INFORMATION: The FAA
                                             must be shown by dynamic test or by                     appropriate safety standards for this                 has determined, in accordance with 5
                                             rational analysis based on previous                     design feature. These special conditions              U.S. Code §§ 553(b)(3)(B) and 553(d)(3),
                                             test(s) of a similar seat installation to not           contain the additional safety standards               that notice and opportunity for prior
                                             exceed 130g. Pelvic acceleration data                   that the Administrator considers                      public comment hereon are unnecessary
                                             must be processed as defined in FMVSS                   necessary to establish a level of safety              because the substance of these special
                                             part 571.214, section S6.13.5.                          equivalent to that established by the                 conditions has been subject to the
                                                (5) Shoulder Strap Loads: Where                      existing airworthiness standards.                     public comment process in several prior
                                             upper torso straps (shoulder straps) are                DATES: The effective date of these                    instances with no substantive comments
                                             used for occupants, tension loads in                    special conditions is April 1, 2015, and              received. The FAA therefore finds that
                                             individual straps must not exceed 1,750                 is applicable on March 25, 2015.                      good cause exists for making these
                                             pounds. If dual straps are used for                        We must receive your comments by                   special conditions effective upon
                                             restraining the upper torso, the total                  May 1, 2015.                                          issuance.
                                             strap tension loads must not exceed                     ADDRESSES: Send comments identified
                                             2,000 pounds.                                           by docket number [FAA–2015–0723]                       Special
                                                                                                                                                           condition         Company/airplane model
                                             b. General Test Guidelines                              using any of the following methods:                    number
                                                                                                        b Federal eRegulations Portal: Go to
                                                (1) One longitudinal test with the SID
                                                                                                     http://www.regulations.gov and follow                 23–237–     Spectrum Aeronautical Model S–
                                             ATD or its equivalent, un-deformed
                                                                                                     the online instructions for sending your                SC.         40.
                                             floor, no yaw, and with all lateral
                                                                                                     comments electronically.                              23–246–     Cirrus Design Corporation Model
                                             structural supports (armrests/walls).
                                                                                                        b Mail: Send comments to Docket                      SC.         SF50.
                                                Pass/fail injury assessments: TTI and                                                                      23–253–     Diamond Aircraft Industries Model
                                                                                                     Operations, M–30, U.S. Department of
                                             pelvic acceleration.                                                                                            SC.         DA–40NG.
                                                                                                     Transportation (DOT), 1200 New Jersey
                                                (2) One longitudinal test with the
                                                                                                     Avenue SE., Room W12–140, West
                                             Hybrid II ATD, deformed floor, with 10                                                                        Comments Invited
                                                                                                     Building Ground Floor, Washington,
                                             degrees yaw, and with all lateral
                                                                                                     DC, 20590–0001.                                          We invite interested people to take
                                             structural supports (armrests/walls).
                                                Pass/fail injury assessments: HIC; and                  b Hand Delivery of Courier: Take                   part in this rulemaking by sending
                                             upper torso restraint load, restraint                   comments to Docket Operations in                      written comments, data, or views. The
                                             system retention and pelvic                             Room W12–140 of the West Building                     most helpful comments reference a
                                             acceleration.                                           Ground Floor at 1200 New Jersey                       specific portion of the special
                                                (3) A vertical (15 G’s) test is to be                Avenue SE., Washington, DC, between 9                 conditions, explain the reason for any
                                             conducted with modified Hybrid II                       a.m., and 5 p.m., Monday through                      recommended change, and include
                                             ATDs using existing pass/fail criteria.                 Friday, except Federal holidays.                      supporting data. We ask that you send
                                                                                                        b Fax: Fax comments to Docket                      us two copies of written comments.
                                               Issued in Kansas City, Missouri on March              Operations at 202–493–2251.
                                             25, 2015.
                                                                                                                                                              We will consider all comments we
                                                                                                        Privacy: The FAA will post all                     receive on or before the closing date for
                                             Pat Mullen,                                             comments it receives, without change,                 comments. We will consider comments
                                             Acting Manager, Small Airplane Directorate,             to http://regulations.gov, including any              filed late if it is possible to do so
                                             Aircraft Certification Service.                         personal information the commenter                    without incurring expense or delay. We
                                             [FR Doc. 2015–07503 Filed 3–31–15; 8:45 am]             provides. Using the search function of                may change these special conditions
                                             BILLING CODE 4910–13–P                                  the docket Web site, anyone can find                  based on the comments we receive.
                                                                                                     and read the electronic form of all
                                                                                                     comments received into any FAA                        Background
                                             DEPARTMENT OF TRANSPORTATION                            docket, including the name of the                        On October 11, 2006, Honda Aircraft
                                                                                                     individual sending the comment (or                    Company applied for a type certificate
                                             Federal Aviation Administration                         signing the comment for an association,               for their new Model HA–420. On
                                                                                                     business, labor union, etc.). DOT’s                   October 10, 2013, Honda Aircraft
                                             14 CFR Part 23                                          complete Privacy Act Statement can be                 Company requested an extension with
                                             [Docket No. FAA–2015–0723; Special                      found in the Federal Register published               an effective application date of October
                                             Conditions No. 23–264–SC]                               on April 11, 2000 (65 FR 19477–19478),                1, 2013. This extension changed the
                                                                                                     as well as at http://DocketsInfo.dot.gov.             type certification basis to amendment
                                             Special Conditions: Honda Aircraft                         Docket: Background documents or                    23–62.
                                             Company (Honda) Model HA–420,                           comments received may be read at                         The HA–420 is a four to five
                                             HondaJet; Full Authority Digital Engine                 http://www.regulations.gov at any time.               passenger (depending on configuration),
                                             Control (FADEC) System                                  Follow the online instructions for                    two crew, lightweight business jet with
                                             AGENCY:  Federal Aviation                               accessing the docket or go to the Docket              a 43,000-foot service ceiling and a
                                             Administration (FAA), DOT.                              Operations in Room W12–140 of the                     maximum takeoff weight of 9963
                                                                                                     West Building Ground Floor at 1200                    pounds. The airplane is powered by two
                                             ACTION: Final special conditions; request
                                                                                                     New Jersey Avenue SE., Washington,                    GE-Honda Aero Engines (GHAE) HF–
rmajette on DSK2TPTVN1PROD with RULES




                                             for comments.
                                                                                                     DC, between 9 a.m., and 5 p.m., Monday                120 turbofan engines.
                                             SUMMARY:   These special conditions are                 through Friday, except Federal holidays.                 The HA–420 airplane will use an
                                             issued for the Honda Aircraft Company                   FOR FURTHER INFORMATION CONTACT: John                 electronic engine control system
                                             HA–420 airplane. This airplane will                     G. VanHoudt, Federal Aviation                         (FADEC) instead of a traditional
                                             have a novel or unusual design feature                  Administration, Aircraft Certification                mechanical control system. Even though
                                             associated with the use of an electronic                Service, Small Airplane Directorate,                  the engine control system will be


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                                                               Federal Register / Vol. 80, No. 62 / Wednesday, April 1, 2015 / Rules and Regulations                                               17313

                                             certificated as part of the engine, the                 pursuant to § 611 of Public Law 92–574,               unnecessary and the FAA finds good
                                             installation of an engine with an                       the ‘‘Noise Control Act of 1972.’’                    cause, in accordance with 5 U.S. Code
                                             electronic control system requires                        The FAA issues special conditions, as               §§ 553(b)(3)(B) and 553(d)(3), making
                                             evaluation due to critical environmental                defined in § 11.19, under § 11.38 and                 these special conditions effective upon
                                             effects and possible effects on or by                   they become part of the type                          issuance. The FAA is requesting
                                             other airplane systems. For example,                    certification basis under § 21.17(a)(2).              comments to allow interested persons to
                                             indirect effects of lightning, radio                      Special conditions are initially                    submit views that may not have been
                                             interference with other airplane                        applicable to the model for which they                submitted in response to the prior
                                             electronic systems, shared engine and                   are issued. Should the type certificate               opportunities for comment described
                                             airplane data and power sources.                        for that model be amended later to
                                                                                                                                                           above.
                                                The regulatory requirements in 14                    include any other model that
                                             CFR part 23 for evaluating the                          incorporates the same novel or unusual                List of Subjects in 14 CFR Part 23
                                             installation of complex systems,                        design feature, the special conditions
                                             including electronic systems and critical               would also apply to the other model                     Aircraft, Aviation safety, Signs and
                                             environmental effects, are contained in                 under the provisions of § 21.101(a)(1).               symbols.
                                             § 23.1309. However, when § 23.1309
                                                                                                     Novel or Unusual Design Features                      Citation
                                             was developed, the use of electronic
                                             control systems for engines was not                       The HA–420 will incorporate the                       The authority citation for these
                                             envisioned. Therefore, § 23.1309                        following novel or unusual design                     special conditions is as follows:
                                             requirements were not applicable to                     features: Electronic engine control
                                             systems certificated as part of the engine              system.                                                 Authority: 49 U.S.C. 106(g), 40113 and
                                             (reference § 23.1309(f)(1)). Parts of the                                                                     44701; 14 CFR 21.16 and 21.17; and 14 CFR
                                                                                                     Discussion                                            11.38 and 11.19.
                                             system that are not certificated with the
                                             engine could be evaluated using the                        As defined in the summary section,                 The Special Conditions
                                             criteria of § 23.1309. However, the                     this airplane makes use of an electronic
                                             integral nature of these systems makes                  engine control system instead of a                      Accordingly, pursuant to the
                                             it unfeasible to evaluate the airplane                  traditional mechanical control system is              authority delegated to me by the
                                             portion of the system without including                 a novel design for this type of airplane.             Administrator, the following special
                                             the engine portion of the system.                       The applicable airworthiness                          conditions are issued as part of the type
                                                In some cases, the airplane that the                 regulations do not contain adequate or                certification basis for Honda Aircraft
                                             engine is used in will determine a                      appropriate safety standards for this                 Company model HA–420 airplanes.
                                             higher classification than the engine                   design feature. Mandating a structured
                                             controls are certificated for; requiring                assessment to determine potential                     1. Electronic Engine Control
                                             the FADEC systems be analyzed at a                      installation issues mitigates the
                                             higher classification. As of November                   concerns that the addition of a full                    a. The installation of the electronic
                                             2005, FADEC special conditions                          authority engine controller does not                  engine control system must comply
                                             mandated the classification for                         produce a failure condition not                       with the requirements of § 23.1309(a)
                                             § 23.1309 analyses for loss of FADEC                    previously considered.                                through (d) at amendment 23–62. The
                                             control as catastrophic for any airplane                                                                      intent of this requirement is not to
                                                                                                     Applicability                                         reevaluate the inherent hardware
                                             using FADEC. This is not to imply an
                                             engine failure is classified as                           As discussed above, these special                   reliability of the control itself, but rather
                                             catastrophic, but that the digital engine               conditions are applicable to the model                determine the effects, including
                                             control must provide an equivalent                      HA–420. Should Honda Aircraft                         environmental effects addressed in
                                             reliability to mechanical engine                        Company apply at a later date for a                   § 23.1306 and 23.1308 on the airplane
                                             controls.                                               change to the type certificate to include             systems and engine control system
                                                                                                     another model incorporating the same                  when installing the control on the
                                             Type Certification Basis                                novel or unusual design feature, the                  airplane. When appropriate, engine
                                                Under the provisions of 14 CFR 21.17,                special conditions would apply to that                certification data may be used when
                                             Honda Aircraft Company must show                        model as well.                                        showing compliance with this
                                             that the HA–420 meets the applicable                                                                          requirement; however, the effects of the
                                                                                                     Conclusion
                                             provisions of part 23, as amended by
                                                                                                        This action affects only certain novel             installation on this data must be
                                             amendments 23–1 through 23–62,
                                                                                                     or unusual design features on the model               addressed.
                                             thereto.
                                                If the Administrator finds that the                  HA–420 airplanes. It is not a rule of                   b. For these evaluations, the loss of
                                             applicable airworthiness regulations                    general applicability and it affects only             FADEC control will be analyzed
                                             (i.e., 14 CFR part 23) do not contain                   the applicant who applied to the FAA                  utilizing the threat levels associated
                                             adequate or appropriate safety standards                for approval of these features on the                 with a catastrophic failure.
                                             for the model HA–420 because of a                       airplane.                                               Issued in Kansas City, Missouri on March
                                             novel or unusual design feature, special                   The substance of these special
                                                                                                                                                           25, 2015.
                                             conditions are prescribed under the                     conditions has been subjected to the
                                                                                                     notice and comment period in several                  Pat Mullen,
                                             provisions of § 21.16.
                                                In addition to the applicable                        prior instances, identified above, and                Acting Manager, Small Airplane Directorate,
                                             airworthiness regulations and special                   has been derived without substantive                  Aircraft Certification Service.
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                                             conditions, the HA–420 must comply                      change from those previously issued. It               [FR Doc. 2015–07502 Filed 3–31–15; 8:45 am]
                                             with the fuel vent and exhaust emission                 is unlikely that prior public comment                 BILLING CODE 4910–13–P
                                             requirements of 14 CFR part 34 and the                  would result in a significant change
                                             noise certification requirements of 14                  from the substance contained herein.
                                             CFR part 36. In addition, the FAA must                  Therefore, notice and opportunity for
                                             issue a finding of regulatory adequacy                  prior public comment hereon are


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Document Created: 2015-12-18 11:04:25
Document Modified: 2015-12-18 11:04:25
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal special conditions; request for comments.
DatesThe effective date of these special conditions is April 1, 2015, and is applicable on March 25, 2015.
ContactJohn G. VanHoudt, Federal Aviation Administration, Aircraft Certification Service, Small Airplane Directorate, ACE-111, 901 Locust, Kansas City, Missouri 64106; 816-329- 4142, fax 816-329-4090.
FR Citation80 FR 17312 
CFR AssociatedAircraft; Aviation Safety and Signs and Symbols

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