ASTM F2245-13b
(Specification)Standard Specification for Design and Performance of a Light Sport Airplane
Standard Specification for Design and Performance of a Light Sport Airplane
ABSTRACT
This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an �airplane.� In order to comply with flight requirements, the following shall be evaluated: load distribution limit, propeller speed and pitch limit, stalling speed, takeoff, climb, landing, balked landing, controllability and maneuverability, vibrations, and ground control and stability. For compliance of structure requirements, the following shall be considered: flight loads; control surface and system loads; horizontal stabilizing and balancing surfaces (balancing loads, maneuvering loads, and gust loads); vertical stabilizing surfaces (maneuvering loads, gust loads, and outboard fins or winglets); supplementary conditions for stabilizing surfaces; ailerons, wing flaps, and special devices; ground load conditions; water load conditions; emergency landing conditions; and other loads. The aircraft shall be designed with the following minimum instrumentation and equipment: flight and navigation instruments such as airspeed indicator, and altimeter; powerplant instruments such as fuel quantity indicator, tachometer (RPM), engine �kill� switch, and engine instruments; miscellaneous equipment such as master switch, and overload protection device; and safety belts and harnesses. Each airplane shall include a Pilot Operating Handbook (POH).
SCOPE
1.1 This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.”
1.2 This specification is applicable to the design of a light sport aircraft/airplane as defined by regulations and limited to VFR flight.
1.3 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 and health practices and determine the applicability of regulatory requirements prior to use.
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Designation:F2245 −13b
StandardSpecification for
1
Design and Performance of a Light Sport Airplane
This standard is issued under the fixed designation F2245; 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.
4
1. Scope 2.3 EASA Requirements:
CS-22Sailplanes and Powered Sailplanes
1.1 Thisspecificationcoversairworthinessrequirementsfor
CS-EEngines
the design of powered fixed wing light sport aircraft, an
CS-PPropellers
“airplane.”
2.4 Other Standards:
1.2 This specification is applicable to the design of a light
GAMASpecification No. 1Specification for Pilot’s Operat-
sport aircraft/airplane as defined by regulations and limited to
5
ing Handbook
VFR flight.
1.3 This standard does not purport to address all of the
3. Terminology
safety concerns, if any, associated with its use. It is the
3.1 Definitions:
responsibility of the user of this standard to establish appro-
3.1.1 electric propulsion unit, EPU—any electric motor and
priate safety and health practices and determine the applica-
all associated devices used to provide thrust for an electric
bility of regulatory requirements prior to use.
aircraft.
3.1.2 energy storage device, ESD—used to store energy as
2. Referenced Documents
part of a Electric Propulsion Unit (EPU). Typical energy
2
2.1 ASTM Standards:
storage devices include but are not limited to batteries, fuel
F2316Specification for Airframe Emergency Parachutes
cells, or capacitors.
F2339Practice for Design and Manufacture of Reciprocat-
3.1.3 flaps—any movable high lift device.
ing Spark Ignition Engines for Light Sport Aircraft
3.1.4 maximumemptyweight,W (N)—largestemptyweight
F2506Specification for Design and Testing of Light Sport
E
of the airplane, including all operational equipment that is
Aircraft Propellers
installed in the airplane: weight of the airframe, powerplant,
F2538Practice for Design and Manufacture of Reciprocat-
EnergyStorageDevice(ESD)aspartofanElectricPropulsion
ingCompressionIgnitionEnginesforLightSportAircraft
Unit (EPU), required equipment, optional and specific
F2564Specification for Design and Performance of a Light
equipment, fixed ballast, full engine coolant and oil, hydraulic
Sport Glider
fluid, and the unusable fuel. Hence, the maximum empty
F2746Specification for Pilot’s Operating Handbook (POH)
for Light Sport Airplane weightequalsmaximumtakeoffweightminusminimumuseful
load: W = W − W .
F2840Practice for Design and Manufacture of Electric
E U
Propulsion Units for Light Sport Aircraft
3.1.5 minimum useful load, W (N)—where W = W − W .
U U E
3
2.2 Federal Aviation Regulations:
3.1.6 night—hoursbetweentheendofeveningciviltwilight
14 CFR Part 33Airworthiness Standards: Aircraft Engines
and the beginning of morning civil twilight.
14 CFR Part 35Airworthiness Standards: Propellers
3.1.6.1 Discussion—Civiltwilightendsintheeveningwhen
the center of the sun’s disc is 6° below the horizon, and begins
inthemorningwhenthecenterofthesun’sdiscis6°belowthe
1
This specification is under the jurisdiction of ASTM Committee F37 on Light horizon.
SportAircraft and is the direct responsibility of Subcommittee F37.20 on Airplane.
3.1.7 The terms “engine” referring to internal combustion
Current edition approved Sept. 1, 2013. Published September 2013. Originally
approved in 2004. Last previous edition approved in 2013 as F2245–13a. DOI: enginesand“motor”referringtoelectricmotorsforpropulsion
10.1520/F2245-13B.
are used interchangeably within this standard.
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’s Document Summary page on
4
the ASTM website. Available from EASA European Aviation Safety Agency, Postfach 10 12 53,
3
Available from Federal Aviation Administration (FAA), 800 Independence D-50452 Koeln, Germany, http://easa.europa.eu.
5
Ave., SW, Washington, DC 20591, http://www.faa.gov or http://ecfr.gpoaccess.gov. Available from the General Aviation Manufacturers Association, http://
www.gama.aero/.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1
---------------------- Page: 1 ----------------------
F2245−13b
3.1.8 The term “engine idle” when in reference to electric 3.2.38 V —stalling speed or minimum steady flight speed
S0
propulsion units shall mean the minimum power or propeller atwhichtheaircraftiscontrollableinthelandingconfiguration
rotational speed condition for the electric motor as defined
3.2.39 V —maximum spoiler/speed brake extended speed
SP
without electron
...
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: F2245 − 13a F2245 − 13b
Standard Specification for
1
Design and Performance of a Light Sport Airplane
This standard is issued under the fixed designation F2245; 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 airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.”
1.2 This specification is applicable to the design of a light sport aircraft/airplane as defined by regulations and limited to VFR
flight.
1.3 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 and health practices and determine the applicability of regulatory
requirements prior to use.
2. Referenced Documents
2
2.1 ASTM Standards:
F2316 Specification for Airframe Emergency Parachutes
F2339 Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft
F2506 Specification for Design and Testing of Light Sport Aircraft Propellers
F2538 Practice for Design and Manufacture of Reciprocating Compression Ignition Engines for Light Sport Aircraft
F2564 Specification for Design and Performance of a Light Sport Glider
F2746 Specification for Pilot’s Operating Handbook (POH) for Light Sport Airplane
F2840 Practice for Design and Manufacture of Electric Propulsion Units for Light Sport Aircraft
3
2.2 Federal Aviation Regulations:
14 CFR Part 33 Airworthiness Standards: Aircraft Engines
14 CFR Part 35 Airworthiness Standards: Propellers
4
2.3 EASA Requirements:
CS-22 Sailplanes and Powered Sailplanes
CS-E Engines
CS-P Propellers
2.4 Other Standards:
5
GAMA Specification No. 1 Specification for Pilot’s Operating Handbook
3. Terminology
3.1 Definitions:
3.1.1 electric propulsion unit, EPU—any electric motor and all associated devices used to provide thrust for an electric aircraft.
3.1.2 energy storage device, ESD—used to store energy as part of a Electric Propulsion Unit (EPU). Typical energy storage
devices include but are not limited to batteries, fuel cells, or capacitors.
3.1.3 flaps—any movable high lift device.
1
This specification is under the jurisdiction of ASTM Committee F37 on Light Sport Aircraft and is the direct responsibility of Subcommittee F37.20 on Airplane.
Current edition approved May 1, 2013Sept. 1, 2013. Published June 2013September 2013. Originally approved in 2004. Last previous edition approved in 2013 as
F2245 – 13.F2245 – 13a. DOI: 10.1520/F2245-13A.10.1520/F2245-13B.
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’s Document Summary page on the ASTM website.
3
Available from Federal Aviation Administration (FAA), 800 Independence Ave., SW, Washington, DC 20591, http://www.faa.gov or http://ecfr.gpoaccess.gov.
4
Available from EASA European Aviation Safety Agency, Postfach 10 12 53, D-50452 Koeln, Germany, http://easa.europa.eu.
5
Available from the General Aviation Manufacturers Association, http://www.gama.aero/.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1
---------------------- Page: 1 ----------------------
F2245 − 13b
3.1.4 maximum empty weight, W (N)—largest empty weight of the airplane, including all operational equipment that is installed
E
in the airplane: weight of the airframe, powerplant, Energy Storage Device (ESD) as part of an Electric Propulsion Unit (EPU),
required equipment, optional and specific equipment, fixed ballast, full engine coolant and oil, hydraulic fluid, and the unusable
fuel. Hence, the maximum empty weight equals maximum takeoff weight minus minimum useful load: W = W − W .
E U
3.1.5 minimum useful load, W (N)—where W = W − W .
U U E
3.1.6 night—hours between the end of evening civil twilight and the beginning of morning civil twilight.
3.1.6.1 Discussion—
Civil twilight ends in the evening when the center of the sun’s disc is 6° below the horizon, and begins in the morning when the
center of the sun’s disc is 6° below the horizon.
3.1.7 The terms “engine” referring to internal combustion engines and “motor” referring to electric motors for p
...
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