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desired spin rotation while applying full back (up)
elevator to the limit of travel. Always maintain the
ailerons in the neutral position during the spin
procedure unless AFM/POH specifies otherwise.
INCIPIENT PHASE
The incipient phase is from the time the airplane stalls
and rotation starts until the spin has fully developed.
This change may take up to two turns for most airplanes.
Incipient spins that are not allowed to develop into a
steady-state spin are the most commonly used in the
introduction to spin training and recovery techniques. In
Ch 04.qxd 5/7/04 6:47 AM Page 4-13
4-14
this phase, the aerodynamic and inertial forces have not
achieved a balance. As the incipient spin develops, the
indicated airspeed should be near or below stall airspeed,
and the turn-and-slip indicator should indicate
the direction of the spin.
The incipient spin recovery procedure should be
commenced prior to the completion of 360° of
rotation. The pilot should apply full rudder opposite
the direction of rotation. If the pilot is not sure of the
direction of the spin, check the turn-and-slip indicator;
it will show a deflection in the direction of rotation.
DEVELOPED PHASE
The developed phase occurs when the airplane’s
angular rotation rate, airspeed, and vertical speed are
stabilized while in a flightpath that is nearly vertical.
This is where airplane aerodynamic forces and inertial
forces are in balance, and the attitude, angles, and selfsustaining
motions about the vertical axis are constant
or repetitive. The spin is in equilibrium.
RECOVERY PHASE
The recovery phase occurs when the angle of attack of
the wings decreases below the critical angle of attack
and autorotation slows. Then the nose steepens and
rotation stops. This phase may last for a quarter turn to
several turns.
To recover, control inputs are initiated to disrupt the
spin equilibrium by stopping the rotation and stall. To
accomplish spin recovery, the manufacturer’s
Less Stalled
Stall
More Drag
Relative Wind
Greater
Angle of
Attack
Chord Line
Relative Wind
Less
Angle of
Attack
Chord Line
INCIPIENT SPIN
• Lasts about 4 to 6
seconds in light
aircraft.
• Approximately 2
turns.
FULLY
DEVELOPED SPIN
• Airspeed, vertical
speed, and rate of
rotation are
stabilized.
• Small, training
aircraft lose
approximately 500
feet per each 3
second turn.
RECOVERY
• Wings regain lift.
• Training aircraft
usually recover in
about 1/4 to 1/2 of
a turn after antispin
inputs are
applied.
More Stalled
Figure 4-10. Spin entry and recovery.
Ch 04.qxd 5/7/04 6:47 AM Page 4-14
4-15
recommended procedures should be followed. In the
absence of the manufacturer’s recommended spin
recovery procedures and techniques, the following
spin recovery procedures are recommended.
Step 1—REDUCE THE POWER (THROTTLE)
TO IDLE. Power aggravates the spin
characteristics. It usually results in a flatter spin
attitude and increased rotation rates.
Step 2—POSITION THE AILERONS TO
NEUTRAL. Ailerons may have an adverse effect
on spin recovery. Aileron control in the direction
of the spin may speed up the rate of rotation and
delay the recovery. Aileron control opposite the
direction of the spin may cause the down aileron
to move the wing deeper into the stall and
aggravate the situation. The best procedure is to
ensure that the ailerons are neutral.
Step 3—APPLY FULL OPPOSITE RUDDER
AGAINST THE ROTATION. Make sure that full
(against the stop) opposite rudder has been
applied.
Step 4—APPLY A POSITIVE AND BRISK,
STRAIGHT FORWARD MOVEMENT OF THE
ELEVATOR CONTROL FORWARD OF THE
NEUTRAL TO BREAK THE STALL. This
should be done immediately after full rudder
application. The forceful movement of the
elevator will decrease the excessive angle of attack
and break the stall. The controls should be held
firmly in this position. When the stall is “broken,”
the spinning will stop.
Step 5—AFTER SPIN ROTATION STOPS,
NEUTRALIZE THE RUDDER. If the rudder is
not neutralized at this time, the ensuing increased
airspeed acting upon a deflected rudder will cause
a yawing or skidding effect.
Slow and overly cautious control movements
during spin recovery must be avoided. In certain
cases it has been found that such movements result
　
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