ASTM International - ASTM F2245-16c
Standard Specification for Design and Performance of a Light Sport Airplane
|Publication Date:||1 December 2016|
|ICS Code (Aircraft and space vehicles in general):||49.020|
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 Units-The values given in this standard are in SI units and are to be regarded as standard. The values given in parentheses are mathematical conversions to inch-pound (or other) units that are provided for information only and are not considered standard. The values stated in each system may not be exact equivalents. Where it may not be clear, some equations provide the units of the result directly following the equation.
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 and health practices and determine the applicability of regulatory requirements prior to use.
This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an â€œairplane.â€ In order to comply with flight requirements, the... View More
This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an â€œairplane.â€ 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 â€œkillâ€ 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).View Less