ASTM F2245-12a

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.

General Information

• Status: Historical
• Publication Date: 31-Aug-2012
• ICS: 49.020 - Aircraft and space vehicles in general
• Technical Committee: F37 - Light Sport Aircraft
• Drafting Committee: F37.20 - Airplane

Relations

• Replaces: ASTM F2245-12 - Standard Specification for Design and Performance of a Light Sport Airplane
• Effective Date: 01-Sep-2012
• Replaced By: ASTM F2245-12b - Standard Specification for Design and Performance of a Light Sport Airplane
• Effective Date: 01-Oct-2012
• Referred By: ASTM F2745-15(2023) - Standard Specification for Required Product Information to be Provided with an Airplane
• Effective Date: 01-Sep-2012
• Referred By: ASTM F2507-15 - Standard Specification for Recreational Airpark Design
• Effective Date: 01-Sep-2012
• Referred By: ASTM F3035-22 - Standard Practice for Production Acceptance in the Manufacture of a Fixed Wing Light Sport Aircraft
• Effective Date: 01-Sep-2012
• Referred By: ASTM F2483-18e1 - Standard Practice for Maintenance and the Development of Maintenance Manuals for Light Sport Aircraft
• Effective Date: 01-Sep-2012
• Referred By: ASTM F2746-14(2023) - Standard Specification for Pilot’s Operating Handbook (POH) for Light Sport Airplane
• Effective Date: 01-Sep-2012
• Referred By: ASTM F2840-14(2023) - Standard Practice for Design and Manufacture of Electric Propulsion Units for Light Sport Aircraft
• Effective Date: 01-Sep-2012
• Referred By: ASTM F3409-19e1 - Standard Practice for Simplified Aircraft Loads Determination
• Effective Date: 01-Sep-2012
• Referred By: ASTM F3298-19 - Standard Specification for Design, Construction, and Verification of Lightweight Unmanned Aircraft Systems (UAS)
• Effective Date: 01-Sep-2012
• Referred By: ASTM F3060-20 - Standard Terminology for Aircraft
• Effective Date: 01-Sep-2012
• Referred By: ASTM F2930-16e1 - Standard Guide for Compliance with Light Sport Aircraft Standards
• Effective Date: 01-Sep-2012

Standards Content (Sample)

NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.
Contact ASTM International (www.astm.org) for the latest information
Designation: F2245 – 12a
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 (ϵ) indicates an editorial change since the last revision or reapproval.
1. Scope GAMA Specification No. 1 Specification for Pilot’s Oper-
5
ating Handbook
1.1 Thisspecificationcoversairworthinessrequirementsfor
the design of powered fixed wing light sport aircraft, an
3. Terminology
“airplane.”
3.1 Definitions:
1.2 This specification is applicable to the design of a light
3.1.1 flaps—any movable high lift device.
sport aircraft/airplane as defined by regulations and limited to
3.1.2 maximum empty weight, W (N)—largest empty
E
VFR flight.
weightoftheairplane,includingalloperationalequipmentthat
1.3 This standard does not purport to address all of the
is installed in the airplane: weight of the airframe, powerplant,
safety concerns, if any, associated with its use. It is the
required equipment, optional and specific equipment, fixed
responsibility of the user of this standard to establish appro-
ballast, full engine coolant and oil, hydraulic fluid, and the
priate safety and health practices and determine the applica-
unusable fuel. Hence, the maximum empty weight equals
bility of regulatory requirements prior to use.
maximumtakeoffweightminusminimumusefulload:W =W
E
2. Referenced Documents − W .
U
2
3.1.3 minimum useful load, W (N)—where W = W − W .
U U E
2.1 ASTM Standards:
3.1.4 night—hoursbetweentheendofeveningciviltwilight
F2316 Specification for Airframe Emergency Parachutes
and the beginning of morning civil twilight.
F2339 Practice for Design and Manufacture of Reciprocat-
3.1.4.1 Discussion—Civiltwilightendsintheeveningwhen
ing Spark Ignition Engines for Light Sport Aircraft
the center of the sun’s disc is 6° below the horizon, and begins
F2538 Practice for Design and Manufacture of Reciprocat-
inthemorningwhenthecenterofthesun’sdiscis6°belowthe
ing Compression Ignition Engines for Light SportAircraft
horizon.
F2564 Specification for Design and Performance of a Light
3.2 Abbreviations:
Sport Glider
2
3.2.1 AR—aspectratio 5 b S
F2746 Specification for Pilot’s Operating Handbook (POH)
/
3.2.2 b—wing span (m)
for Light Sport Airplane
3
3.2.3 c—chord (m)
2.2 Federal Aviation Regulations:
3.2.4 CAS—calibrated air speed (m/s, kts)
14 CFR Part 33 Airworthiness Standards: Aircraft Engines
4
3.2.5 C —lift coefficient of the airplane
2.3 EASA Requirements: L
3.2.6 C —drag coefficient of the airplane
CS-E Engines D
3.2.7 CG—center of gravity
CS-22 Sailplanes and Powered Sailplanes
3.2.8 C —moment coefficient (C is with respect to c/4
2.4 Other Standards: m m
point, positive nose up)
3.2.9 C —zero lift moment coefficient
MO
1
This specification is under the jurisdiction ofASTM Committee F37 on Light
3.2.10 C —normal coefficient
n
SportAircraft and is the direct responsibility of Subcommittee F37.20 onAirplane.
2
3.2.11 g—acceleration as a result of gravity = 9.81 m/s
Current edition approved Sept. 1, 2012. Published November 2012. Originally
3.2.12 IAS—indicated air speed (m/s, kts)
approved in 2004. Last previous edition approved in 2012 as F2245–12. DOI:
10.1520/F2245-12A.
3.2.13 ICAO—International Civil Aviation Organization
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
3.2.14 LSA—Light Sport Aircraft
contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM
3.2.15 MAC—mean aerodynamic chord (m)
Standards volume information, refer to the standard’s Document Summary page on
3.2.16 n—load factor
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 5
Available from EASA European Aviation Safety Agency, Postfach 10 12 53, Available from the General Aviation Manufacturers Association, http://
D-50452 Koeln, Germany, http://easa.europa.eu. www.gama.aero/.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
1

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F2245 – 12a
3.2.17 n —airplane positive maneuvering limit load factor
P = rated engine power, kW.
1
3.2.18 n —airplane negative maneuvering limit load factor
2 4.2.1.2 For a two-place airplane:
3.2.19 n —load factor on wheels
3
W 51690 13P, ~N!
U
3.2.20 P—power, (kW)
3
3.2.21 ρ—air density (kg/m )=1.225 at sea level standard
where:
conditions
P = rated engine power, kW.
3.2.22 POH—Pilot Operating Handbook
4.2.2 Minimum flying weight shall be determined.
2 2
3.2.23 q—dynamic pressure ~N/m !51 2ρV
/
NOTE 1
...