The tail rotor blades of a helicopter have a rotating unbalance of magnitude \(0.5 \mathrm{~kg} \cdot \mathrm{m}\) and operate at a speed of \(1200 \mathrm{rpm}\). Modeling the tail section as a cantilever beam of length \(3.5 \mathrm{~m}\) with \(E=31 \times 10^{6} \mathrm{~N} \cdot \mathrm{m}^{2}\), determine the steady-state response of the tail section.