Inertial system errors in case of using the new structural correction method have been determined. Inertial system errors, which determine the kinematic parameters of aircraft movement, are finally generated in the computing circuit. This is the part of inertial system structure which is presented as a closed loop with a feedback. The forward circuit of the main loop consists of several velocity and distance integrators connected in series. Accelerometer signal corrections are calculated in the feedback loop. New corrective circuits have been introduced to the inertial system structure. And the errors of the changed system have been determined. The structural corrective circuits got signals from exterior onboard navigation systems. The conducted research has shown that the use of structural corrective circuits in some cases leads to a considerable decrease of inertial system errors. It means that the new structural method of inertial system correction provides positive results. Further research of inertial system errors should be conducted for the case of its full structure.