Airbus Protection against rudder deflection under Normal Law...
Given the well known pitch and bank protections under Normal Law, I was taken to believe that should an inadvertent full deflection of the rudder using the rudder pedals be done the systems would still prevent over banking and pitching, but I've been told that it's not really the case ( ? )
Imagine a scenario where, just after takeoff, already airborne and climbing towards acceleration height, full left or right rudder is input. What will happen regarding the yaw-induced roll ? What about the resulting pitch moments ? Would it be possible to "roll inverted" under such circumstances, or:
.) the forces required for any effective roll due to yaw are so huge that it would not be possible;
.) the protection logic also covers this sort of scenario.
Thank you for any hints