An actuator-link assembly manufacturing method for manufacturing an actuator that can be attached pivotably, at one end thereof, to a control surface of an aircraft or to a horn arm member attached to the control surface in order to drive the control surface, and a link that is coupled to the actuator, the method comprising: a material determining step (S101a) of determining a material constituting the actuator and a material constituting the link; a computing step (S101b) of computing a change in gain margin with a change in a rigidity ratio, which is the ratio of the rigidity of the link to the rigidity of the actuator, using a computation model that includes an inertial mass of the control surface, a rigidity of the control surface, a rigidity of the actuator, and a rigidity of the link as parameters and that defines a relationship between the parameters; a rigidity determining step (S101c) of determining rigidities of the actuator and the link such that the rigidity ratio and the gain margin fall within respective predetermined ranges, based on a computation result obtained in the computing step (S102b); a shape determining step (S101d) of determining shapes of the actuator and the link such that rigidities of the actuator and the link are set to the rigidities determined in the rigidity determining step (S101c); a formation step (S102a) of forming the actuator and the link into the shapes determined in the shape determining step (S101d); and an assembly step (S102b) of coupling and assembling the actuator and the link formed in the formation step (S102a), wherein the link is attached pivotably to a fulcrum shaft for rotatably supporting the control surface, and is also attached pivotably to the other end of the actuator via a pivot shaft, and, in the material determining step (S101a), the materials are determined such that at least one of the material constituting the actuator and the material constituting the link contains fiber reinforced plastic. a material determining step (S101a) of determining a material constituting the actuator and a material constituting the link; a computing step (S101b) of computing a change in gain margin with a change in a rigidity ratio, which is the ratio of the rigidity of the link to the rigidity of the actuator, using a computation model that includes an inertial mass of the control surface, a rigidity of the control surface, a rigidity of the actuator, and a rigidity of the link as parameters and that defines a relationship between the parameters; a rigidity determining step (S101c) of determining rigidities of the actuator and the link such that the rigidity ratio and the gain margin fall within respective predetermined ranges, based on a computation result obtained in the computing step (S102b); a shape determining step (S101d) of determining shapes of the actuator and the link such that rigidities of the actuator and the link are set to the rigidities determined in the rigidity determining step (S101c); a formation step (S102a) of forming the actuator and the link into the shapes determined in the shape determining step (S101d); and an assembly step (S102b) of coupling and assembling the actuator and the link formed in the formation step (S102a), wherein the link is attached pivotably to a fulcrum shaft for rotatably supporting the control surface, and is also attached pivotably to the other end of the actuator via a pivot shaft, and, in the material determining step (S101a), the materials are determined such that at least one of the material constituting the actuator and the material constituting the link contains fiber reinforced plastic.