SCHEMPP-HIRTH FLUGZEUGBAU GmbH., KIRCHHEIM/TECK
Ventus-2cM
FLIGHT MANUAL
3.5 Spin
recovery
A safe recovery from a spin is effected by the following method:
a)
Hold aileron neutral.
b)
Apply opposite rudder
(i.e. against the direction of rotation of the spin).
c)
Ease control stick forward until rotation ceases and the airflow is
restored.
d)
Centralize rudder and pull gently out of dive.
With the center of gravity in rearward positions, a steady spinning motion is
possible.
After having applied the standard recovery method, the aircraft will stop rotating
after about ¼ to ¾ of a turn.
The loss of height, from the point at which recovery is initiated to the point at
which horizontal flight is first regained, can be up to 250 m / 820 ft.
The recovery speeds are between 145 and 250 km/h (78 - 135 kt, 90 - 155
mph) depending on the flap setting.
At positive flap settings and high all-up masses a resetting of the flaps at “-1”
may be required so as to avoid exceeding their speed limits when pulling out of
the dive.
With the center of gravity in the foremost position, a steady spinning motion is
not possible - the aircraft stops rotating after a half to three full turns and,
depending on the control surface deflections, usually enters a spiral dive or a
side slip or steepens its nose-down attitude.
Recovery is by normal use of opposite controls.
NOTE:
1. Spinning may be safely avoided by following the actions
given in section 3.4 “Stall recovery”.
2. If the aircraft with a rearmost c of g position and an uneven
ballast load in the wing tanks enters a spin, it may only stop
rotating after 1.0 turns following initiating recovery.
November
2003
LBA-app.
Revision --
3.5
Summary of Contents for Ventus-2cM
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