ASTM F3316/F3316M-19
(Specification)Standard Specification for Electrical Systems for Aircraft with Electric or Hybrid-Electric Propulsion
Standard Specification for Electrical Systems for Aircraft with Electric or Hybrid-Electric Propulsion
ABSTRACT
This specification applies to the electrical systems, electrical equipment, and electrical power distribution aspects of airworthiness and design for aircraft with electric or hybrid-electric propulsion. Developed through open consensus of international experts in general aviation, this material focused on Normal Category Airplanes. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance.
This specification establishes the Aircraft Type Code (ATC) compliance matrix based on certification level, number of engines, type of engine(s), stall speed, cruise speed, meteorological conditions, altitude, and maneuvers. An ATC is defined by taking into account both the technical considerations regarding the design of the aircraft and the airworthiness level established based upon risk-based criteria. Requirements for electrical systems for electric propulsion cover power source capacity and distribution, electrical systems and equipment, circuit protective devices, master switch arrangement, switches, electrical cables and equipment, electrical system fire protection, electronic equipment, and storage battery design and installation.
SCOPE
1.1 This specification covers the electrical systems, electrical equipment, and electrical power distribution aspects of airworthiness and design for aircraft with Electric or Hybrid-Electric Propulsion. This specification was written with the focus on electric propulsion systems with conventional system layout, characteristics, and operation. This specification does not address all of the requirements that may be necessary for possible hybrid-electric configurations where an EPU and a combustion engine are used in combination to provide propulsion. The use of this specification combined with the applicable portions of Specification F3231/F3231M may be necessary for hybrid-electric configurations. This material was developed through open consensus of international experts in general aviation. This material was created by focusing on Normal Category Aeroplanes. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance.
1.2 An applicant intending to propose this information as a means of compliance for design approval shall seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as a Means of Compliance to their regulatory requirements (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm).
1.3 Units—This standard may present information in either SI units, English Engineering units, or both. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.
1.4 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.
1.5 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.
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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:F3316/F3316M −19
Standard Specification for
Electrical Systems for Aircraft with Electric or Hybrid-
1
Electric Propulsion
ThisstandardisissuedunderthefixeddesignationF3316/F3316M;thenumberimmediatelyfollowingthedesignationindicatestheyear
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 1.4 This standard does not purport to address all of the
safety concerns, if any, associated with its use. It is the
1.1 This specification covers the electrical systems, electri-
responsibility of the user of this standard to establish appro-
cal equipment, and electrical power distribution aspects of
priate safety, health, and environmental practices and deter-
airworthiness and design for aircraft with Electric or Hybrid-
mine the applicability of regulatory limitations prior to use.
Electric Propulsion. This specification was written with the
1.5 This international standard was developed in accor-
focus on electric propulsion systems with conventional system
dance with internationally recognized principles on standard-
layout, characteristics, and operation. This specification does
ization established in the Decision on Principles for the
not address all of the requirements that may be necessary for
Development of International Standards, Guides and Recom-
possible hybrid-electric configurations where an EPU and a
mendations issued by the World Trade Organization Technical
combustion engine are used in combination to provide propul-
Barriers to Trade (TBT) Committee.
sion.Theuseofthisspecificationcombinedwiththeapplicable
portions of Specification F3231/F3231M may be necessary for
2. Referenced Documents
hybrid-electric configurations. This material was developed 2
2.1 ASTM Standards:
through open consensus of international experts in general
F2490–05Standard Guide forAircraft Electrical Load and
aviation. This material was created by focusing on Normal
Power Source Capacity Analysis
Category Aeroplanes. The content may be more broadly
F2639Practice for Design, Alteration, and Certification of
applicable; it is the responsibility of the applicant to substan-
Aircraft Electrical Wiring Systems
tiate broader applicability as a specific means of compliance.
F3060Terminology for Aircraft
1.2 An applicant intending to propose this information as a
F3061/F3061MSpecification for Systems and Equipment in
means of compliance for design approval shall seek guidance Small Aircraft
from their respective oversight authority (for example, pub- F3066/F3066MSpecification forAircraft Powerplant Instal-
lishedguidancefromapplicableCAAs)concerningtheaccept- lation Hazard Mitigation
able use and application thereof. For information on which F3231/F3231MSpecification for Electrical Systems forAir-
oversight authorities have accepted this standard (in whole or craft with Combustion Engine Electrical Power Genera-
in part) as a Means of Compliance to their regulatory require- tion
ments (Hereinafter referred to as “the Rules”), refer toASTM F3235Specification for Aircraft Storage Batteries
F44 webpage (www.ASTM.org/COMMITTEE/F44.htm). F3239SpecificationforAircraftElectricPropulsionSystems
F3338Specification for Design of Electric Propulsion Units
1.3 Units—This standard may present information in either
for General Aviation Aircraft
SI units, English Engineering units, or both. The values stated
3
2.2 FAA Standard:
in each system are not necessarily exact equivalents; therefore,
DOT/FAA/AR-00/12Aircraft Materials Fire Test Handbook
to ensure conformance with the standard, each system shall be
used independently of the other, and values from the two
3. Terminology
systems shall not be combined.
3.1 Terminology specific to this specification is provided
below. For general terminology, refer to Terminology F3060.
1 2
ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral For referenced ASTM standards, visit the ASTM website, www.astm.org, or
Aviation Aircraft and is the direct responsibility of Subcommittee F44.50 on contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
Systems and Equipment. Standards volume information, refer to the standard’s Document Summary page on
Current edition approved Nov. 1, 2019. Published December. Originally ap- the ASTM website.
3
provedin2018.Lastpreviouseditionapprovedin2019asF3316/F3316M–19.DOI: Available from Federal Aviation Administration (FAA), 800 Independence
10.1520/F3316_F3316M–19. Ave., SW, Washington, DC 20591, http://www.faa.gov.
Copyright © ASTM International, 100 Barr Ha
...
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: F3316/F3316M − 18 F3316/F3316M − 19
Standard Specification for
Electrical Systems for Aircraft with Electric or Hybrid-
1
Electric Propulsion
This standard is issued under the fixed designation F3316/F3316M; 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 electrical systems, electrical equipment, and electrical power distribution aspects of
airworthiness and design for aircraft with Electric or Hybrid-Electric Propulsion. This specification was written with the focus on
electric propulsion systems with conventional system layout, characteristics, and operation. This specification does not address all
of the requirements that may be necessary for possible hybrid-electric configurations where an EPU and a combustion engine are
used in combination to provide propulsion. The use of this specification combined with the applicable portions of Specification
F3231/F3231M may be necessary for hybrid-electric configurations. This material was developed through open consensus of
international experts in general aviation. This material was created by focusing on Normal Category Airplanes.Aeroplanes. The
content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific
means of compliance.
1.2 An applicant intending to propose this information as a means of compliance for design approval mustshall seek guidance
from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use
and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as a Means
of Compliance to their regulatory requirements (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage
(www.ASTM.org/COMMITTEE/F44.htm).
1.3 Units—This standard may present information in either SI units, English Engineering units, or both; theboth. The values
stated in each system mayare not be exact equivalents. Each necessarily exact equivalents; therefore, to ensure conformance with
the standard, each system shall be used independently of the other; combiningother, and values from the two systems may result
in nonconformance with the standard.shall not be combined.
1.4 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.
1.5 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:
F2490 – 05 Standard Guide for Aircraft Electrical Load and Power Source Capacity Analysis
F2639 Practice for Design, Alteration, and Certification of Aircraft Electrical Wiring Systems
F3060 Terminology for Aircraft
F3061/F3061M Specification for Systems and Equipment in Small Aircraft
F3066/F3066M Specification for Aircraft Powerplant Installation Hazard Mitigation
F3231/F3231M Specification for Electrical Systems for Aircraft with Combustion Engine Electrical Power Generation
F3235 Specification for Aircraft Storage Batteries
F3239 Specification for Aircraft Electric Propulsion Systems
1
This specification is under the jurisdiction of ASTM Committee F44 on General Aviation Aircraft and is the direct responsibility of Subcommittee F44.50 on Systems
and Equipment.
Current edition approved May 15, 2018Nov. 1, 2019. Published June 2018December. Originally approved in 2018. Last previous edition approved in 2019 as
F3316/F3316M–19. DOI: 10.1520/F3316_F3316M-18.10.1520/F3316_F3316M–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. Un
...
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