4. A twin-engine aircraft has a weight of 815450N and the wing of the aircraft produces a lift of 806.5kN. The CoG of the aircraft is located at 49% of the MAC, and the distance between the CoG and the CoP of the horizontal stabiliser is 18.01m. The aspect ratio for the wing and stabiliser is 9.71 and 6.51 respectively and the aerodynamic centre of the wing is (-475 600Nm) Wing Stabiliser Tail Lift slope Span MAC Area Span MAC Area Arm (m) (m) (m?) (m (m) (m?) (m) ao a1 35.33 4.66 128.55 15.20 2.57 35.49 14.01 0.12 0.098 Assuming that the stabiliser is 90% efficient and the value of da /de is 0.631, determine, using the information above, the: a) Neutral point b) Static margin c) Whether the aircraft is statically stable in the longitudinal direction