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.
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