To ensure that the turboshaft engine does not overheat, surge, or flame out during transient conditions, while minimizing acceleration and deceleration times, this paper completes the design of the transition control schedule for the turboshaft engine. The closed loop n-dot control schedule was designed by direct simulation method based on component level model. With the surge margin limit, the combustor fuel-air ratio limit or the turbine inlet total temperature limit being given during acceleration as input, the optimal acceleration control schedule for the turboshaft engine is obtained; with the combustor fuel-air ratio limit or the corrected rotor speed of the gas turbine limit being given during deceleration as input, the optimal deceleration control schedule for the turboshaft engine is obtained. The full-envelope control schedule can be obtained by selecting the boundaries of the optimal control schedule curve clusters. The results indicate that using the dn/dt/pt3 = f(n) as n-dot control schedule can achieve better transient performance. This paper demonstrates the feasibility of applying the direct simulation method to the turboshaft engine.