What is the effect on the aeroplane's static longitudinal stability of a shift of the centre of gravity to a more aft location and on the required control deflection for a certain pitch up or down?
I put: The static longitudinal stability is smaller and the required control deflection is larger.
Correct Answer: The static longitudinal stability is smaller and the required control deflection is smaller.
My thinking was that as the CG is aft, the arm between elevator and CG is smaller therefore a greater deflection would be required for the same movement. Now I'm thinking that it depends if you want to pitch up or down. Pitching up with aft CG would be easier than pitching down???