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This specification covers the minimum requirement for designing, testing, and labeling of weight-shift-control aircraft. This specification covers only weight-shift-control aircraft in which flight control systems do not use hinged surfaces controlled by the pilot. Flight requirements are specified for: (1) proof of compliance including hang point and trimming setting; (2) general performance such as (a) stall speed in the landing configuration, (b) stall speed free of control limits, (c) minimum climb performance, (d) flutter, buffeting, and vibration, (e) turning flight and stalls, and (f) maximum sustainable speed in straight and level flight; (3) controllability and maneuverability such as general, longitudinal, and lateral control; and (4) longitudinal stability and pitch testing. Structural requirements specified include: (1) strength requirements, (2) fulfillment of design requirements, (3) safety factors, (4) design airspeeds, (5) flight loads, (6) pilot control loads, (7) ground loads including landing gear shock absorption, and (8) emergency landing loads. Design and construction requirements are specified for: (1) materials, (2) fabrication methods, (3) self-locking nuts, (4) protection of structure, (5) accessibility, (6) setup and breakdown, (7) control system evaluated by operation test, (8) mast (pylon) safety device, (9) cockpit design, and (10) markings and placards. Powerplant requirements including installation, fuel system, oil system, induction system, and fire prevention, as well as equipment requirements such as powerplant instruments, miscellaneous equipment, and lap belts and harnesses, are detailed. Operating limitations such as load distribution limits are also specified.
This abstract is a brief summary of the referenced standard. It is informational only and not an official part of the standard; the full text of the standard itself must be referred to for its use and application. ASTM does not give any warranty express or implied or make any representation that the contents of this abstract are accurate, complete or up to date.
1.1 This specification covers the minimum airworthiness standards a manufacturer shall meet in the designing, testing, and labeling of weight-shift-control aircraft.
1.2 This specification covers only weight-shift-control aircraft in which flight control systems do not use hinged surfaces controlled by the pilot.
Note 1—This section is intended to preclude hinged surfaces such as typically found on conventional airplanes such as rudders and elevators. Flexible sail surfaces typically found on weight-shift aircraft are not considered hinged surfaces for the purposes of this specification.
1.3 Weight-shift-control aircraft means a powered aircraft with a framed pivoting wing and a fuselage (trike carriage) controllable only in pitch and roll by the pilot's ability to change the aircraft's center of gravity with respect to the wing. Flight control of the aircraft depends on the wing's ability to flexibly deform rather than the use of control surfaces.
1.4 This specification is organized and numbered in accordance with the bylaws established for Committee F37. The main sections are:
2. Referenced Documents (purchase separately) The documents listed below are referenced within the subject standard but are not provided as part of the standard.
F2339 Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft
Federal Aviation RegulationsFAR-35 Airworthiness Standards: Propellers
ICS Number Code 49.020 (Aircraft and space vehicles in general)
UNSPSC Code 25132005(Ultra light aircraft)
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ASTM F2317 / F2317M-10, Standard Specification for Design of Weight-Shift-Control Aircraft, ASTM International, West Conshohocken, PA, 2010, www.astm.orgBack to Top