Engineering flight simulator development. Reconfigurable, electromechanical Control Loading System. Validation according to international standards by using real control data. Figure A. Simulator architecture Purpose: As one of the subsystems of advanced flight simulators, Control Loading System (CLS) enhances the realism of simulation by artificially producing the control forces that occur during the actual flight. In this study, an engineering flight simulator is realized for the purpose of CLS development. The simulator integrates the CLS with a flight dynamics model and a visual system to enable validation with piloted simulations. Theory and Methods: A linkage type CLS is designed with high torque electric motors, while paying special attention to reconfigurability. Data measured from the actual flight controls is transformed to be input to the CLS via a systematic procedure. Performance of the designed CLS is investigated by comparing the measured flight control behavior of the simulator with that of the actual aircraft, according to the requirements of the international certification standards. Results: CLS is experimentally validated by using the data measured from the cyclic control of a real aircraft. The performance of the simulator control is within the allowable ±10% of the real control. Moreover, the average instantaneous force difference between the real and simulator controls is less than half of the allowable minimum value. Conclusion: A reconfigurable engineering flight simulator is designed and built for CLS development. A simple yet effective procedure is presented for using real control force versus control position data in the simulator as control simulation models. It is shown by experimental results that the static test requirements of the international certification standards are met.