CS-VLA 221 Spinning

• ED Decision 2003/18/RM found in: CS-VLA Amdt 1 - Very Light Aeroplanes (Mar 2009)

CS-VLA 221 Spinning ED Decision 2003/18/RM (a) The aeroplane must be able to recover from a one-turn spin or a 3-second spin, whichever takes longer, in not more than one additional turn, with the controls used in the manner normally used for recovery. In addition - (1) For both the flaps-retracted and flaps-extended conditions, the applicable airspeed limit and positive limit manoeuvring load factor may not be exceeded; (2) There may be no excessive back pressure during the spin or recovery; and (3) It must be impossible to obtain uncontrollable spins with any use of the controls. For the flaps-extended condition, the flaps may be retracted during recovery. (b) *Aeroplanes ‘characteristically incapable of spinning’*. If it is desired to designate an aeroplane as ‘characteristically incapable of spinning’, this characteristic must be shown with - (1) A weight five percent more than the highest weight for which approval is requested; (2) A centre of gravity at least three percent of the mean aerodynamic chord aft of the rearmost position for which approval is requested; (3) An available elevator up-travel 4° in excess of that to which the elevator travel is to be limited for approval; and (4) An available rudder travel, 7° in both directions, in excess of that to which the rudder travel is to be limited for approval.