SPIN ENTRY
The spin should be entered from a power-off glide by reducing speed at
about 1 kt/sec until the airplane stalls. Apply full aft control wheel and full
rudder in the desired spin direction. This control configuration with the
throttle closed should be held throughout the spin. The ailerons must remain
neutral throughout the spin and recovery, since aileron application may
alter the spin characteristics to the degree that the spin is broken prematurely
or that recovery is delayed.
SPIN RECOVERY
(a) Apply and maintain full rudder opposite the direction of rotation.
(b) As the rudder hits the stop, rapidly move the control wheel full
forward and be ready to relax the forward pressure as the stall is
broken.
(c) As rotation stops, centralize the rudder and smoothly recover from
the dive.
Normal recoveries may take up to 1-1/2 turns when proper technique is
used; improper technique can increase the turns to recover and the resulting
altitude loss.
FURTHER ADVICE ON SPINNING
SPIN ENTRY
Application of full aft control wheel and full rudder before the airplane
stalls is not recommended as it results in large changes in pitch attitude
during entry and the first turn of the spin. Consequently the initial 2-3 turns
of the spin can be more oscillatory than when the spin is entered at the stall.
SPIN RECOVERY
The recommended procedure has been designed to minimize turns and
height loss during recovery. If a modified recovery is employed (during
which a pause of about 1 second - equivalent to about one half turn of the
spin - is introduced between the rudder reaching the stop and moving the
control column forward) spin recovery will be achieved with equal certainty.
However the time taken for recovery will be delayed by the length of the
pause, with corresponding increase in the height lost.
In all spin recoveries the control column should be moved forward
briskly, continuing to the forward stop if necessary. This is vitally important
because the steep spin attitude may inhibit pilots from moving the control
column forward positively.
PIPER AIRCRAFT CORPORATION
SECTION 4
PA-38-112, TOMAHAWK
NORMAL PROCEDURES
ISSUED: JANUARY 20, 1978
REPORT: 2126
REVISED: APRIL 30, 1981
4-25
SPIN ENTRY
The spin should be entered from a power-off glide by reducing speed at
about 1 kt/sec until the airplane stalls. Apply full aft control wheel and full
rudder in the desired spin direction. This control configuration with the
throttle closed should be held throughout the spin. The ailerons must remain
neutral throughout the spin and recovery, since aileron application may
alter the spin characteristics to the degree that the spin is broken prematurely
or that recovery is delayed.
SPIN RECOVERY
(a) Apply and maintain full rudder opposite the direction of rotation.
(b) As the rudder hits the stop, rapidly move the control wheel full
forward and be ready to relax the forward pressure as the stall is
broken.
(c) As rotation stops, centralize the rudder and smoothly recover from
the dive.
Normal recoveries may take up to 1-1/2 turns when proper technique is
used; improper technique can increase the turns to recover and the resulting
altitude loss.
FURTHER ADVICE ON SPINNING
SPIN ENTRY
Application of full aft control wheel and full rudder before the airplane
stalls is not recommended as it results in large changes in pitch attitude
during entry and the first turn of the spin. Consequently the initial 2-3 turns
of the spin can be more oscillatory than when the spin is entered at the stall.
SPIN RECOVERY
The recommended procedure has been designed to minimize turns and
height loss during recovery. If a modified recovery is employed (during
which a pause of about 1 second - equivalent to about one half turn of the
spin - is introduced between the rudder reaching the stop and moving the
control column forward) spin recovery will be achieved with equal certainty.
However the time taken for recovery will be delayed by the length of the
pause, with corresponding increase in the height lost.
In all spin recoveries the control column should be moved forward
briskly, continuing to the forward stop if necessary. This is vitally important
because the steep spin attitude may inhibit pilots from moving the control
column forward positively.
PIPER AIRCRAFT CORPORATION
SECTION 4
PA-38-112, TOMAHAWK
NORMAL PROCEDURES
ISSUED: JANUARY 20, 1978
REPORT: 2126
REVISED: APRIL 30, 1981
4-25
