ASTM F2245-10b
(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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NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.
Please contact ASTM International (www.astm.org) for the latest information.
Designation: F2245 – 10b
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.Anumber in parentheses indicates the year of last reapproval.A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope 3. Terminology
1.1 Thisspecificationcoversairworthinessrequirementsfor 3.1 Definitions:
the design of powered fixed wing light sport aircraft, an 3.1.1 flaps—any movable high lift device.
“airplane.” 3.1.2 maximum empty weight, W (N)—largest empty
E
1.2 This specification is applicable to the design of a light weightoftheairplane,includingalloperationalequipmentthat
sport aircraft/airplane as defined by regulations and limited to is installed in the airplane: weight of the airframe, powerplant,
VFR flight. required equipment, optional and specific equipment, fixed
1.3 This standard does not purport to address all of the ballast, full engine coolant and oil, hydraulic fluid, and the
safety concerns, if any, associated with its use. It is the unusable fuel. Hence, the maximum empty weight equals
responsibility of the user of this standard to establish appro- maximumtakeoffweightminusminimumusefulload:W =W
E
priate safety and health practices and determine the applica- − W .
U
bility of regulatory requirements prior to use. 3.1.3 minimum useful load, W (N)—where W = W − W .
U U E
3.1.4 night—hoursbetweentheendofeveningciviltwilight
2. Referenced Documents
and the beginning of morning civil twilight.
2
2.1 ASTM Standards: 3.1.4.1 Discussion—Civiltwilightendsintheeveningwhen
F2316 SpecificationforAirframeEmergencyParachutesfor
the center of the sun’s disc is 6° below the horizon, and begins
Light Sport Aircraft inthemorningwhenthecenterofthesun’sdiscis6°belowthe
F2339 Practice for Design and Manufacture of Reciprocat-
horizon.
ing Spark Ignition Engines for Light Sport Aircraft 3.2 Abbreviations:
2
F2538 Practice for Design and Manufacture of Reciprocat-
3.2.1 AR—aspect ratio = b S
/
ing Compression Ignition Engines for Light SportAircraft
3.2.2 b—wing span (m)
F2746 Specification for Pilot’s Operating Handbook (POH)
3.2.3 c—chord (m)
for Light Sport Airplane
3.2.4 CAS—calibrated air speed (m/s, kts)
3
2.2 Federal Aviation Regulations:
3.2.5 C —lift coefficient of the airplane
L
FAR-33 Airworthiness Standards: Aircraft Engines
3.2.6 C —drag coefficient of the airplane
D
4
2.3 Joint Aviation Requirements:
3.2.7 CG—center of gravity
JAR-E Engines
3.2.8 C —moment coefficient (C is with respect to c/4
m m
JAR-22 Sailplanes and Powered Sailplanes
point, positive nose up)
2.4 Other Standards:
3.2.9 C —zero lift moment coefficient
MO
GAMA Specification No. 1 Specification for Pilot’s Oper-
3.2.10 C —normal coefficient
n
5 2
ating Handbook
3.2.11 g—acceleration as a result of gravity = 9.81 m/s
3.2.12 IAS—indicated air speed (m/s, kts)
3.2.13 ICAO—International Civil Aviation Organization
1
This specification is under the jurisdiction of ASTM Committee F37 on Light
3.2.14 LSA—Light Sport Aircraft
SportAircraft and is the direct responsibility of Subcommittee F37.20 onAirplane.
Current edition approved Nov. 1, 2010. Published January 2011. Originally
3.2.15 MAC—mean aerodynamic chord (m)
approved in 2004. Last previous edition approved in 2010 as F2245–10a. DOI:
3.2.16 n—load factor
10.1520/F2245-10B.
2 3.2.17 n —airplane positive maneuvering limit load factor
1
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
3.2.18 n —airplane negative maneuvering limit load factor
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
2
Standards volume information, refer to the standard’s Document Summary page on
3.2.19 n —load factor on wheels
3
the ASTM website.
3.2.20 P—power, (kW)
3
Available from Federal Aviation Administration (FAA), 800 Independence
3
3.2.21 r—air density (kg/m )=1.225 at sea level standard
Ave., SW, Washington, DC 20591, http://www.faa.gov.
4
Available from Global Engineering Documents, 15 Inverness Way, East conditions
Englewood, CO 80112-5704, http://global.ihs.com.
3.2.22 POH—Pilot Operating Handbook
5
Available from the General Aviation Manufacturers Association, http://
2 2
3.2.23 q—dynamic pressure (N/m)= 1 2rV
www.gama.aero/. /
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
1
---------------------- Page: 1 ----------------------
NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.
Please contact ASTM International (www.astm.org) for the latest information.
F2245 – 10b
3.2.24 RC—climb rate (m/s) 4.2.3 EmptyCG,mostforward,andmostrearward
...
This document is not anASTM standard and is intended only to provide the user of anASTM 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:F2245–10a Designation: F2245 – 10b
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.Anumber in parentheses indicates the year of last reapproval.A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope
1.1 Thisspecificationcoversairworthinessrequirementsforthedesignofpoweredfixedwinglightsportaircraft,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 for Light Sport Aircraft
F2339 Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft
F2538 Practice for Design and Manufacture of Reciprocating Compression Ignition Engines for Light Sport Aircraft
F2746 Specification for Pilot’s Operating Handbook (POH) for Light Sport Airplane
3
2.2 Federal Aviation Regulations:
FAR-33 Airworthiness Standards: Aircraft Engines
4
2.3 Joint Aviation Requirements:
JAR-E Engines
JAR-22 Sailplanes and Powered Sailplanes
2.4 Other Standards:
5
GAMA Specification No. 1 Specification for Pilot’s Operating Handbook
3. Terminology
3.1 Definitions:
3.1.1 flaps—any movable high lift device.
3.1.2 maximum empty weight, W (N)—largest empty weight of the airplane, including all operational equipment that is
E
installed in the airplane: weight of the airframe, powerplant, 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
3.1.3 minimum useful load, W (N)—where W = W − W .
U U E
3.1.4 night—hours between the end of evening civil twilight and the beginning of morning civil twilight.
3.1.4.1 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.
3.2 Abbreviations:
2
3.2.1 AR—aspect ratio = b S
/
3.2.2 b—wing span (m)
3.2.3 c—chord (m)
3.2.4 CAS—calibrated air speed (m/s, kts)
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 Sept.Nov. 1, 2010. Published January 2011. Originally approved in 2004. Last previous edition approved in 2010 as F2245–10a. DOI:
10.1520/F2245-10AB.
2
ForreferencedASTMstandards,visittheASTMwebsite,www.astm.org,orcontactASTMCustomerServiceatservice@astm.org.For Annual Book ofASTM 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.
4
Available from Global Engineering Documents, 15 Inverness Way, East Englewood, CO 80112-5704, http://global.ihs.com.
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 – 10b
3.2.5 C —lift coefficient of the airplane
L
3.2.6 C —drag coefficient of the airplane
D
3.2.7 CG—center of gravity
3.2.8 C —moment coefficient (C is with respect to c/4 point, positive nose up)
m m
3.2.9 C —zero lift moment coefficient
MO
3.2.10 C —normal coefficient
n
2
3.2.11 g—acceleration as a result of gravity = 9.81 m/s
3.2.12 IAS—indicated air speed (m/s, kts)
3.2.13 ICAO—International Civil Aviation Organization
3.2.14 LSA—Light Sport Aircraft
3.2.15 MAC—mean aerodynamic chord (m)
3.2.16 n—load factor
3.2.17 n —airplane positive maneuvering limit load factor
1
3.2.18 n —airplane negative maneuvering limit load factor
2
3.2.19 n —load factor on wheels
3
3.2.20 P—power, (kW)
3
3.2.21 r—air density (kg/m )=1.225 at sea level standard conditions
3.2.22 POH—
...
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