[Federal Register Volume 84, Number 82 (Monday, April 29, 2019)]
[Rules and Regulations]
[Pages 17942-17944]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-08606]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 21

[Docket No. FAA-2018-0379]


Airworthiness Criteria: Special Class Airworthiness Criteria for 
the Yamaha Fazer R

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of issuance of airworthiness criteria.

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SUMMARY: The FAA announces airworthiness criteria for a special class 
of aircraft, the Yamaha Motor Corporation, U.S.A., model Fazer R, which 
is an unmanned aircraft system. It designates airworthiness criteria 
found by the FAA to provide an equivalent level of safety to existing 
standards.

DATES: These airworthiness design criteria are effective May 29, 2019.

FOR FURTHER INFORMATION CONTACT: Mr. Quentin Coon, AIR-692, Federal 
Aviation Administration, Policy and Innovation Division, Small Airplane 
Standards Branch, Aircraft Certification Service, 901 Locust, Room 301, 
Kansas City, MO 64106, telephone (816) 329-4168, facsimile (816) 329-
4090.

SUPPLEMENTARY INFORMATION: 

Background

    Yamaha Motor Corporation, U.S.A. (Yamaha) applied to the FAA on 
April 28, 2017 for special class type certification under Title 14, 
Code of Federal Regulations (14 CFR) 21.17(b) for the Fazer R Unmanned 
Aircraft System (UAS). The Fazer R UAS (Fazer R) consists of the 
Unmanned Aircraft (UA), flight transmitter ground control

[[Page 17943]]

station, and payload spray system. The Fazer R is a vertical take-off 
UAS that is of the traditional main/tail rotor helicopter design. Its 
intended primary use is conducting crop-spraying operations in the 
agricultural industry.
    The aircraft and payload spray system would weigh approximately 244 
pounds with full fuel and oil tanks, and be able to carry a payload of 
approximately 105 pounds. The main rotor is just over nine feet in 
diameter, and the aircraft would be just over three feet high and 12 
feet long with a carbon frame. The aircraft would be powered by a fuel-
injected 2-cylinder engine running on regular gasoline. The aircraft 
would have a ``Turn Assistance'' function that enables automatic 
turning to facilitate back-and-forth agricultural operations.

Discussion of Comments

    Notice of proposed airworthiness design criteria for the Yamaha 
Fazer R UAS was published in the Federal Register on May 1, 2018 (83 FR 
19021). The FAA received comments from two commenters.
    One individual requested the FAA consider limiting operations to 
remotely populated areas and requiring primary operations of spraying, 
sensing, and imaging and two persons for operation. The commenter 
stated these considerations are necessary because of the agricultural 
requirements for the aircraft. The commenter also stated these 
requirements should be the minimum requirements for all UAS, and not 
only the Fazer R.
    Under the Concept of Operations submitted by the applicant for the 
Fazer R, the primary operations are agricultural spraying, sensing, and 
imaging in remote, uninhabited areas such as farms and fields, and the 
aircraft has a required minimum crew of two persons. No changes to 
these airworthiness criteria are necessary as a result of this comment. 
The request to apply these requirements to all UAS is beyond the scope 
of this notice.
    Another individual requested the FAA consider the possible risks--
fuel and security of the system--associated with the insecticide 
carried by the Fazer R.
    The applicant's documentation identifies and provides appropriate 
mitigation for these risks. No changes to these airworthiness criteria 
are necessary as a result of this comment.

Conclusion

    After review of the comments, the FAA sees no need to modify the 
proposed airworthiness criteria. Accordingly, the airworthiness 
criteria, as proposed, are adopted as the certification basis for the 
Yamaha Fazer R under the provisions of 14 CFR 21.17(b).

The Airworthiness Design Criteria

    The FAA finds that compliance with the following will appropriately 
mitigate the risks associated with the proposed design and Concept of 
Operations (CONOPS) and provide an equivalent level of safety to 
existing rules:
    Concept of Operations: The applicant must define and submit to the 
FAA a (CONOPS) proposal describing the intended Fazer R operation in 
the National Airspace System (NAS).
    Accepted Means of Compliance:
    1. The applicant must comply with these airworthiness criteria 
using a means of compliance, which may include consensus standards, 
accepted by the FAA.
    2. The applicant requesting acceptance of a means of compliance 
must provide the means of compliance to the FAA in a form and manner 
acceptable to the FAA.
    Operational Envelope and Limitations: The operational envelope and 
operational limitations must be defined as follows:
    1. The Fazer R must be shown to perform as intended within the 
defined operational envelope and operational limitations.
    2. The Fazer R must be consistently and predictably controllable 
and maneuverable within the operating envelope, including:
    (a) At all loading conditions for which certification is requested;
    (b) During all phases of flight; and
    (c) During configuration changes.
    Instructions for Continued Airworthiness: The applicant must 
prepare Instructions for Continued Airworthiness (ICA) for the Fazer R 
that are acceptable to the FAA. The ICA may be incomplete at type 
certification if a program exists to ensure their completion prior to 
delivery of the first Fazer R or issuance of a standard certificate of 
airworthiness, whichever occurs later.
    The ICA must contain a section titled Airworthiness Limitations 
that is segregated and clearly distinguishable from the rest of the 
document. This section must set forth each mandatory replacement time, 
structural inspection interval, and related structural inspection 
procedure required for type certification. If the ICA consist of 
multiple documents, the section required by this paragraph must be 
included in the principal manual. This section must contain a legible 
statement in a prominent location that reads ``The Airworthiness 
Limitations section is FAA approved and specifies maintenance conducted 
under Sec. Sec.  43.16 and 91.403 of Title 14 of the Code of Federal 
Regulations unless an alternative program has been FAA approved.''
    Flight Manual: The applicant must provide a UAS Flight Manual with 
each Fazer R. The UAS Flight Manual must contain the following 
information--
    (a) Fazer R operating limitations;
    (b) Fazer R normal and emergency operating procedures;
    (c) Performance information;
    (d) Loading information; and
    (e) Other information that is necessary for safe operation because 
of design, operating, or handling characteristics.
    Flight Testing: The Fazer R must successfully complete at least 150 
hours of flight testing to determine whether there is reasonable 
assurance that the Fazer R, its components, its equipment, and 
structures are adequate, reliable, and function properly. The testing 
must consist of:
    1. At least 50 hours with the Unmanned Aircraft (UA) at 5 percent 
over maximum weight at critical weight, altitude, and temperature; and
    2. At least 100 hours in normal operations.
    Critical Parts: A critical part is a part, the failure of which 
could have a catastrophic effect upon the UAS. If the type design 
includes critical parts, a critical parts list must be established.
    The applicant must develop and define inspections or other 
procedures to prevent failures due to degradation of critical parts. 
Each of these inspections or procedures must be included in the 
Airworthiness Limitations Section of the ICA.
    Controls:
    1. Flight Controls: The applicant must design the flight control 
systems and control station to:
    (a) Operate easily, smoothly, and positively enough to allow proper 
performance of their functions, and
    (b) Protect against likely hazards.
    2. Flight Crew Interface: The control station must be designed to 
allow the flight crew to perform their duties and to perform any 
maneuvers within the operating envelope of the Fazer R, without 
excessive concentration, skill, alertness, or fatigue considering the 
intended operating conditions for the control station.
    3. Equipment: The applicant must define and install necessary 
equipment so the flight crew can monitor and perform defined tasks 
associated with the intended functions of the systems and equipment.
    4. Flight Crew Error: The UAS must be designed to minimize flight 
crew errors

[[Page 17944]]

which could result in additional hazards.
    Flight Termination System:
    1. There must be a means for the flight crew to quickly and safely 
terminate the UA flight.
    2. The Fazer R must have a means to safely terminate the UA flight 
when safe operation cannot continue or be maintained.
    3. There must be means to prevent inadvertent operation of the 
flight termination system.
    Engine and Engine Control System:
    1. The Fazer R Engine and Engine Control System includes each 
component necessary for propulsion or which affects propulsion safety.
    2. The Fazer R Engine and Engine Control System installation must 
be designed, constructed, installed, and maintained to ensure its 
continued safe operation within the operational envelope between normal 
inspections and overhauls.
    3. The Fazer R Engine Control System including any Engine Control 
Unit (ECU) software or electronic hardware must be designed and 
developed using methods accepted by the FAA.
    4. The applicant must identify the Fazer R Engine and Engine 
Control System failure modes and effects that may result in a 
catastrophic condition to the UAS. The applicant must mitigate each 
hazard to a level acceptable to the FAA.
    5. The Fazer R Engine and Engine Control System operability, 
durability and reliability must be demonstrated.
    Powerplant Installation:
    1. The powerplant installation includes each part of the Fazer R 
(other than the main and auxiliary rotor structures) that--
    (a) Is necessary for propulsion;
    (b) Affects the control of the major propulsive units; or
    (c) Affects the safety of the major propulsive units between normal 
inspections or overhauls.
    2. Each component of the powerplant installation must be 
constructed, arranged, and installed to ensure its continued safe 
operation between normal inspections or overhauls for the range of 
temperature and altitude for which approval is requested.
    Systems and Equipment: This requirement applies to the Fazer R 
unless another requirement has been imposed for a specific piece of 
equipment, system, or systems. The Fazer R systems and equipment, 
including any software or electronic hardware, must be designed and 
developed using methods accepted by the FAA.
    1. The systems and equipment required for a Fazer R to operate 
safely in the kinds of operations for which certification is requested 
must be designed and installed to perform their intended function 
throughout the operating and environmental limits for which the Fazer R 
is certificated.
    2. All systems and equipment not covered by paragraph 1 of this 
section, considered separately and in relation to other systems, must 
be designed and installed so their operation or failure does not have 
an adverse effect on the Fazer R.
    Communication:
    1. The applicant must define the type, methods, and operational 
limits of communication, including the mitigation of any hazard created 
by any loss of communication between the flight crew and between the 
flight crew and the Fazer R.
    2. A means must be provided to allow for all communication 
necessary to safely operate the UA.
    Interference from External Sources: The design must minimize the 
risks associated with interference to Fazer R electronic systems and 
networks from external sources.
    Interference with Other Aircraft or Obstacles: The Fazer R must 
have a means to remain well clear of obstacles and other aircraft for 
its intended operation and airspace to avoid the risk of collision.

    Issued in Kansas City, Missouri, on April 19, 2019.
Pat Mullen,
Aircraft Certification Service, Manager, Small Airplane Standards 
Branch, AIR-690.
[FR Doc. 2019-08606 Filed 4-26-19; 8:45 am]
 BILLING CODE 4910-13-P


