Are you talking about the 30% increase in lift due to rapid pitch rate? That has to do with dynamic stall - where a leading edge vortex (LEV) "provides additional suction over the upper airfoil surface as it convects downstream. This increased suction leads to performance gains in lift and stall delay, but the LEV quickly becomes unstable and detaches from the airfoil. The LEV detachment is accompanied by a dramatic decrease in lift and sudden increase in pitching moment."
This mostly has to do with helicopters and flapping wings, it would be hard to duplicate this with an airplane unless it was an aerobatic plane or military fighter jet. You can read more about dynamic stall here:
Dynamic Stall | Aerodynamic Flow Control and Advanced Diagnostics Research Group
I wouldn't worry about it - but what you really should know is:
- At Va or below, you can make one full abrupt control movement and return to neutral and be sure your control surfaces won't break.
- Even below Va, if you apply abrupt control inputs in multiple axis or multiple oscillations, you are not guaranteed to not overstress the control surface or its supporting structure.
- Va does not vary based on weight.
- At all times you are required to ensure that the limit maneuvering load factor is not exceeded. It can be exceeded at speeds below Va.
If you keep those in mind, you'll have no problem operating an airplane safely - in this regard!
