1.1 This specification covers the minimum airworthiness standards a manufacturer shall meet in the designing, testing, and labeling of weight-shift-control aircraft.<\/p>\n
1.2 This specification covers only weight-shift-control aircraft in which flight control systems do not use hinged surfaces controlled by the pilot.<\/p>\n
Note 1 <\/p>\n
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.<\/p>\n
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.<\/p>\n
1.4 This specification is organized and numbered in accordance with the bylaws established for Committee F37. The main sections are:<\/p>\n
1.5 The values stated in SI units are to be regarded as the standard. The values given in parentheses are for information only.<\/p>\n
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.<\/p>\n
| PDF Pages<\/th>\n | PDF Title<\/th>\n<\/tr>\n | ||||||
|---|---|---|---|---|---|---|---|
| 1<\/td>\n | Scope Referenced Documents Terminology <\/td>\n<\/tr>\n | ||||||
| 2<\/td>\n | Flight Requirements <\/td>\n<\/tr>\n | ||||||
| 3<\/td>\n | Structural Requirements <\/td>\n<\/tr>\n | ||||||
| 4<\/td>\n | TABLE 1 <\/td>\n<\/tr>\n | ||||||
| 5<\/td>\n | Design and Construction Requirements <\/td>\n<\/tr>\n | ||||||
| 6<\/td>\n | Powerplant Equipment Requirements Operating Limitations <\/td>\n<\/tr>\n | ||||||
| 7<\/td>\n | Keywords A1. DESIGN AND PERFORMANCE STANDARDS FOR LIGHT SPORT AIRCRAFT USED TO AERO-TOW GLIDERS A1.1 Applicability A1.2 Controllability and Maneuverability A1.3 Stability A1.4 Structure and Strength Requirements A1.5 Design and Construction A1.6 Operating Limitations <\/td>\n<\/tr>\n | ||||||
| 8<\/td>\n | X1. STATIC TEST PROTOCOL WING STRENGTH TESTS X1.1 Load Tests Required X1.2 Calculation Of Total Test Loads To Be Applied X1.3 Positive Load X1.4 Negative Load FIG. X1.1 <\/td>\n<\/tr>\n | ||||||
| 9<\/td>\n | TABLE X1.1 FIG. X1.2 TABLE X1.2 <\/td>\n<\/tr>\n<\/table>\n","protected":false},"excerpt":{"rendered":" F2317\/F2317M-05 Standard Specification for Design of Weight-Shift-Control Aircraft<\/b><\/p>\n |