I A P 2 0 2 3 . 0 0 1 - A F M / I R I S T E X A N I I P A G E | 215
FOR SIMULATION USE ONLY – NOT A TRAINING AID
Due to oil pressure restrictions, aggravated spins were conducted only to 4 turns.
Spins with greater than 4 turns while holding aggravated flight control inputs may
cause oil starvation problems, resulting in damage to the engine.
Inverted Departures/Spins
NOTE
Intentional inverted departures and spins are prohibited.
Inverted spins have been entered by releasing the controls with the aircraft in a 60°
to 90° pitch attitude at maximum power (MAX) and an indicated airspeed of 50
knots.
At control release, the aircraft can be expected to torque roll to the left to a near
inverted, nose-level attitude. After slight hesitation, yaw rate will increase as the
aircraft enters a right spin, reaching 120° per second after 2 turns are completed.
Spins entered using this technique are flatter than erect spins, with slight pitch
oscillations about a mean of 30° nose low. Airspeed will read 40 knots and angle of
attack will be pegged at zero during the spin.
Normal acceleration during this spin is typically -1.5 G. These spins have been
performed with the aircraft loaded at or near the aft centre of gravity limit.
Inverted incipient spins have also been achieved from an inverted stall at maximum
power.
In the inverted spins tested, high engine torque is the primary impetus which drives
the aircraft into, and sustains, the inverted spin. By reducing the power to IDLE
during the first 2 spin turns, the pilot can expect the spin to terminate without using
recovery controls.
Attempts to enter the inverted spin from and inverted stall with power at IDLE and
ailerons neutral typically deteriorates into an inverted spiral in the direction of
applied rudder, with airspeed rapidly increasing in a steep nose low attitude.
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