The lateral-directional stability and control characteristics of some aircraft are given by Cn=+0.004 deg^-1, Cns = -0.0037 deg^-1, Cna = 0 deg^-1, -208r + 20, C1g = -0.0023 deg^-1, C1s = 0 deg^-1, C1 = +0.00076 deg^-1, -25α + 25°. The aircraft is landing with the following conditions: IM = 70 lbf/ft^2, CLmax = 1.2, Viand = 1.2 Vstall Sliand.

a) Determine the rudder and ailerons deflection required to trim the aircraft in yaw and roll with maintained sideslip of β = 8 deg.
b) Determine the landing speed for the aircraft, Viand.
c) Estimate the maximum crosswind component that can be handled by the rudder and ailerons if the aircraft is to be landed with its longitudinal axis aligned with the runway.