The aircraft for which the stalling speed Vs in level flight is 52.5 m/s has a maximum allowable maneuver load factor n1 of 3.61. In assessing gyroscopic effects on the engine mounting, the following two cases are to be considered: 

(a) Pull-out at a maximum permissible rate from a dive in symmetric flight, the angle of the flight path to the horizontal being limited to 60o for this aircraft. 

(b) Steady, correctly banked turn at the maximum permissible rate in horizontal flight. Find the corresponding maximum angular velocities in yaw and pitch.