An aircraft with a weight of 250 kN could not make a balanced landing due to pilot error during landing and the loads in the figure fell on the wheels (loads of 150 kN and 100 kN are in the x direction). a) The weight of each wheel is 3kN. Find the pressure and bending moment (moment distribution graph) in the oleo strut. b) The weight of the section after section AA is 8 kN and the center of gravity of the wing is at 40% of the chord from the leading edge (chord length c-120 cm) and 3 m away from section AA. Accordingly, find the shear forces and bending moments in section AA. Attention: The axis passes through the middle of the wing. Section AA is 40 cm outside the wheel line.Ix=40 kN m s, Iy-200 kN m s, Iz- 150 kN m sNote: Do not forget to take into account the angular accelerations caused by rotation. 1) 50 kN 200 kN 50lN 150 kN A 30KNY 200m G 200kN 220cm 160 kN 30kN y TUDEN 35 an 160km $1 W 120 cm X y