Linearize the pitching moment equation about a steady turn maneuver
u₀, ɸ₀, and ψ₀ ≠ 0
assuming that the aerodynamic pitching moment M has the dependence
M = M(u, w, q, δₑ, δₜ).
Hint: r₀ ≠ ₀; you need to determine it in terms of ψ₀ and ɸ₀.