ASTM F3298-19
(Specification)Standard Specification for Design, Construction, and Verification of Lightweight Unmanned Aircraft Systems (UAS)
Standard Specification for Design, Construction, and Verification of Lightweight Unmanned Aircraft Systems (UAS)
ABSTRACT
This specification establishes the airworthiness requirements for the design of fixed-wing unmanned aircraft systems. It defines the baseline design, construction, and verification requirements for an unmanned aircraft system (UAS), defined as a system composed of the unmanned aircraft and all required on-board subsystems, payload, control station, other required off-board subsystems, any required launch and recovery equipment, all required crew members, and command and control (C2) links between UA and the control station. This specification applies to fixed wing UAS with permission to operate over a defined area and in airspace authorized by a nation's civil aviation authority (CAA) with a fully interactive ground-based person as ”Remote Pilot in Command.”
This specification covers requirements for flight (e.g., proof of compliance, load distribution limits, propeller speed and pitch limits); performance (stalling speed, takeoff, climb, landing, multi-engine); design (equipment, systems, and installation, workmanship, airframe, airspeed limitations, loads and dynamics); construction (fabrication methods, fasteners); structure (loads, flight loads, limit load factors, design airspeeds); command and control system (flight and navigations instruments, automatic flight control system, datalinks, teleoperated flight controls); other required off-board subsystems (required launch and recovery equipment, tethering systems); miscellaneous equipment (payloads, digital flight data recording system); operating limitations and information (weight and center of gravity, propulsion system limitations, electromagnetic environmental effects); documentation (design control, aircraft flight manual, maintenance manual); verification (system verification, methods of verification); and best practices (performance verification, airframe, propulsion system, propeller, miscellaneous equipment such as payloads and high-intensity radiated fields [HIRF] protection).
SCOPE
1.1 This specification covers the airworthiness requirements for the design of light unmanned aircraft systems. This specification defines the baseline design, construction, and verification requirements for an unmanned aircraft system (UAS).
1.2 As a minimum, a UAS is defined as a system composed of the unmanned aircraft and all required on-board subsystems, payload, control station, other required off-board subsystems, any required launch and recovery equipment, all required crew members, and command and control (C2) links between UA and the control station.
1.3 The intent is for this standard of practice for CAA, self- or third-party determinations of airworthiness for UAS. This specification provides the core requirements for airworthiness certification of lightweight (UAS) (not necessarily limited to UAs under 55 lb GTOW) or for certain CAA operational approvals using risk-based categories. Additional requirements are envisioned to address the requirements for expanded operations and characteristics not addressed by this specification.
1.4 This specification is intended to support UAS operations. It is assumed that the risk of UAS will vary based on concept of operations, environment, and other variables. The fact that there are no human beings onboard the UAS may reduce or eliminate some hazards and risks. However, at the discretion of the CAA, this specification may be applied to other UAS operations.
1.5 The values in Imperial units are to be regarded as the standard. The values in SI are for information only.
1.6 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.7 This international standard was developed in accordance with internationally recognized principles on standardization establi...
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This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the
Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
Designation:F3298 −19
Standard Specification for
Design, Construction, and Verification of Lightweight
1
Unmanned Aircraft Systems (UAS)
This standard is issued under the fixed designation F3298; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision.Anumber in parentheses indicates the year of last reapproval.A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope 1.7 This international standard was developed in accor-
dance with internationally recognized principles on standard-
1.1 Thisspecificationcoverstheairworthinessrequirements
ization established in the Decision on Principles for the
for the design of light unmanned aircraft systems. This
Development of International Standards, Guides and Recom-
specification defines the baseline design, construction, and
mendations issued by the World Trade Organization Technical
verification requirements for an unmanned aircraft system
Barriers to Trade (TBT) Committee.
(UAS).
1.2 As a minimum, a UAS is defined as a system composed
2. Referenced Documents
oftheunmannedaircraftandallrequiredon-boardsubsystems,
2
2.1 ASTM Standards:
payload, control station, other required off-board subsystems,
F2245Specification for Design and Performance of a Light
any required launch and recovery equipment, all required crew
Sport Airplane
members, and command and control (C2) links between UA
F2908Specification for Unmanned Aircraft Flight Manual
and the control station.
(UFM) for an Unmanned Aircraft System (UAS)
1.3 The intent is for this standard of practice for CAA, self-
F2909Practice for Maintenance and Continued Airworthi-
or third-party determinations of airworthiness for UAS. This
ness of Small Unmanned Aircraft Systems (sUAS)
specification provides the core requirements for airworthiness
F2911Practice for Production Acceptance of Small Un-
certification of lightweight (UAS) (not necessarily limited to
manned Aircraft System (sUAS)
UAs under 55 lb GTOW) or for certain CAA operational
F3002Specification for Design of the Command and Con-
approvalsusingrisk-basedcategories.Additionalrequirements
trolSystemforSmallUnmannedAircraftSystems(sUAS)
are envisioned to address the requirements for expanded
F3003Specification for Quality Assurance of a Small Un-
operations and characteristics not addressed by this specifica-
manned Aircraft System (sUAS)
tion.
F3005Specification for Batteries for Use in Small Un-
manned Aircraft Systems (sUAS)
1.4 This specification is intended to support UAS opera-
tions. It is assumed that the risk of UAS will vary based on F3120/F3120MSpecification for Ice Protection for General
Aviation Aircraft
concept of operations, environment, and other variables. The
F3178Practice for Operational Risk Assessment of Small
fact that there are no human beings onboard the UAS may
Unmanned Aircraft Systems (sUAS)
reduce or eliminate some hazards and risks. However, at the
F3201Practice for Ensuring Dependability of Software
discretion of the CAA, this specification may be applied to
Used in Unmanned Aircraft Systems (UAS)
other UAS operations.
2.2 ANSI Standard:
1.5 The values in Imperial units are to be regarded as the
ANSI Z535.1-1998American National Standard for Safety
standard. The values in SI are for information only.
Colors
1.6 This standard does not purport to address all of the
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2.3 FAA Standard:
safety concerns, if any, associated with its use. It is the
Order 8130.34DAirworthiness Certification of Unmanned
responsibility of the user of this standard to establish appro-
Aircraft Systems and Optionally Piloted Aircraft
priate safety, health, and environmental practices and deter-
mine the applicability of regulatory limitations prior to use.
1 2
This specification is under the jurisdiction of ASTM Committee F38 on For referenced ASTM standards, visit the ASTM website, www.astm.org, or
UnmannedAircraftSystemsandisthedirectresponsibilityofSubcommitteeF38.01 contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
on Airworthiness. Standards volume information, refer to the standard’s Document Summary page on
Current edition approved Feb. 1, 2019. Published March 2019. Originally the ASTM website.
3
approved in 2018. Last previous edition approved in 2018 as F3298–18. DOI: Available from Federal Aviation Administration (FAA), 800 Independence
10.1520/F3298–19. Ave., SW, Washington, DC 20591, http://www.faa.gov.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1
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F3298−19
2.4 Federal St
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This document is not an ASTM standard and is intended only to provide the user of an ASTM standard an indication of what changes have been made to the previous version. Because
it may not be technically possible to adequately depict all changes accurately, ASTM recommends that users consult prior editions as appropriate. In all cases only the current version
of the standard as published by ASTM is to be considered the official document.
Designation: F3298 − 18 F3298 − 19
Standard Specification for
Design, Construction, and Verification of Fixed-
1
WingLightweight Unmanned Aircraft Systems (UAS)
This standard is issued under the fixed designation F3298; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope
1.1 This specification covers the airworthiness requirements for the design of fixed-winglight unmanned aircraft systems. This
specification defines the baseline design, construction, and verification requirements for an unmanned aircraft system (UAS).
1.2 As a minimum, a UAS is defined as a system composed of the unmanned aircraft and all required on-board subsystems,
payload, control station, other required off-board subsystems, any required launch and recovery equipment, all required crew
members, and command and control (C2) links between UA and the control station.
1.3 The intent is for this standard of practice for CAA, self- or third-party determinations of airworthiness for UAS. This
specification provides the core requirements for airworthiness certification of lightweight (UAS) (not necessarily limited to UAs
under 55 lb GTOW) or for certain CAA operational approvals using risk-based categories. Additional requirements are envisioned
to address the requirements for expanded operations and characteristics not addressed by this specification.
1.4 This specification is intended to support UAS operations. It is assumed that the risk of UAS will vary based on concept of
operations, environment, and other variables. The fact that there are no human beings onboard the UAS may reduce or eliminate
some hazards and risks. However, at the discretion of the CAA, this specification may be applied to other UAS operations.
1.5 The values in Imperial units are to be regarded as the standard. The values in SI are for information only.
1.6 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility
of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of
regulatory limitations prior to use.
1.7 This international standard was developed in accordance with internationally recognized principles on standardization
established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued
by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
2. Referenced Documents
2
2.1 ASTM Standards:
F2245 Specification for Design and Performance of a Light Sport Airplane
F2908 Specification for Unmanned Aircraft Flight Manual (UFM) for an Unmanned Aircraft System (UAS)
F2909 Practice for Maintenance and Continued Airworthiness of Small Unmanned Aircraft Systems (sUAS)
F2911 Practice for Production Acceptance of Small Unmanned Aircraft System (sUAS)
F3002 Specification for Design of the Command and Control System for Small Unmanned Aircraft Systems (sUAS)
F3003 Specification for Quality Assurance of a Small Unmanned Aircraft System (sUAS)
F3005 Specification for Batteries for Use in Small Unmanned Aircraft Systems (sUAS)
F3120/F3120M Specification for Ice Protection for General Aviation Aircraft
F3178 Practice for Operational Risk Assessment of Small Unmanned Aircraft Systems (sUAS)
F3201 Practice for Ensuring Dependability of Software Used in Unmanned Aircraft Systems (UAS)
2.2 ANSI Standard:
ANSI Z535.1-1998 American National Standard for Safety Colors
1
This specification is under the jurisdiction of ASTM Committee F38 on Unmanned Aircraft Systems and is the direct responsibility of Subcommittee F38.01 on
Airworthiness.
Current edition approved May 1, 2018Feb. 1, 2019. Published May 2018March 2019. Originally approved in 2018. Last previous edition approved in 2018 as F3298–18.
DOI: 10.1520/F3298-18.10.1520/F3298–19.
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM Standards
volume information, refer to the standard’sstandard’s Document Summary page on the ASTM website.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1
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F3298 − 19
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2.3 Unmanned Systems Canada Bes
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