Alex : thanks
RBGMW : You might want to derive a simplified flight mechanics formula
The rolling moment equation is (simplified)
Inertia*φ'' =(Cldl*dl + Clp pb/2v) * QSb
Any answer to a rolling question is behind this equation.
Then you just have to interpret your question.
Are we talking about the maximum achievable rate of roll ?
If yes, then phi''=0 when max rate of roll is reached and :
Cldl * dlmax = Clp pmax*b/2V
Cldl, dlmax, Clp, b are constant.
So pmax will increase if V will increase. At constant IAS, V will increase with altitude
The rate of turn is unrelated to the angle of aileron deflection.
Depending on the aircraft, you will be in a steady turn with aileron undeflected or deflected in any direction (towards the turn, outwards the turn, more directions if they existed)
So I'd go A