This work presents an alleviation control system for the rotorcraft pitch link load based on the dynamic inversion controller using direct load feedback and extremum seeking control to regulate the load. The proposed method is applied to a compound utility rotorcraft with similar airframe properties as a UH-60A along with lifting wings. The nonlinear model is developed in FLIGHTLAB® from where the vehicle dynamics and critical fatigue loads are extracted as a linear time-periodic system due to its cyclic nature. Via harmonic decomposition, this model is converted to a high-order linear time-invariant (LTI) system and then a reduced-order method is applied to extract a more tractable system for controller design over a range of airspeeds. The design is tested in both, the high-order LTI and the nonlinear system. The results present a significant reduction in the pitch link peak-to-peak loads with a minimum change in the response characteristics.