Most of modern aircraft control surface employ redundant actuation system in active mode. Due to the inherent force-fighting in this system , the traditional aircraft structural load measurement method based on on-station load calibration test is no longer suitable for the flight measurement of hinge moment of modern aircraft control surface. In this paper, a method of measurement for hinge moment of aircraft control surface based on off-station load calibration test and on-station load verification test is presented, the corresponding load measurement model is established, the factors affecting the precision of hinge moment measurement are analyzed and determined, the verification and correction methods of possible systematic errors are given, the procedure for flight measurement of hinge moment of aircraft control surface is developed. The feasibility and effectiveness of this method are verified by flight test of hinge moment measurement of multi-type aircraft control surface, the precision of hinge moment of aircraft control surface is improved, and the reliable measured load is provided for the design load verification and optimization of aircraft control surface. The load distribution of each actuator of aircraft control surface is obtained, and flight monitoring of the force-fighting of the actuation system of aircraft control surface is realized, which ensures the flight safety.