12.68.14(c) . high rate of descent at low airspeed; 

In a spiral dive the nose attitude is low, the wings are not stalled
Airspeed is rapidly increasing and rate of descent is high

12.68.14(b) . simultaneous motion about three axes (rolling, pitching, yawing); 

The aircraft is yawing and rolling with one wing producing more lift than the other.
The downgoing wing is more steeply stalled than the other
Greater drag from the stalled lower wing results in further yaw leading to further roll.
Aerodynamic conditions fluctuate – resulting in the nose pitchin up and down

12.68.14(a) . stalled condition of flight; 

Aircaraft is stalled

12.68.14. Define a spin, with reference to:

12.68.12. Define the term autorotation and the conditions leading to it.

The wing drop at the stall is caused by one wing reachi9ng the stalling angle of attack slightly ahead og the other
When this occurs the aircraft will roll because of the imbalance of lift between the wings
As the roll develops the airflow approaches each wing at a different angle and angle of attack of downgoing wing increases while the upgoing wing decreases

The wingdrop at the stall is caused by one wing reaching the stalling angle of attack slightly ahead of the other.
The aircraft rolls because of the imbalance of lift between the wings
As roll develops airflow approaches each wing at a different angle – the downgoing wing angle of attack increases while that of the upgoing wing decreases.
Resulting lateral imbalance of lift and drag causes the aircraft to yaw and to roll automatically – a state called “autorotation”

12.68.10. Describe the possible consequences of using ailerons near, during and in therecovery from a stall. 

Large amounts of aileron should not be used approaching the stall

The wing which has its aileron deflected downwards may be taken beyond the stalkling angle which will cause a wing drop

12.68.8(f) . damage, ice, frost, or other contamination of the wings. 

Any damage will increase stalling speed due to a loss of lift and an increase in drag

12.68.8(e) . flap extension; 

IAS is slower where the flaps are extended
– increase lift and slower IAS before the stalling angle is reached

12.68.8(d) . power; 

Application of power lowers the stalling speed

12.68.8(c) . altitude; 

Altitude does not affect the IAS at which an aircraft will stall

NB: – Altitude increased the TAS at the tail so when operating in a high altitude aerdrome the true airspeed on approach and landing will be higher than same circumstances at sea level