In this thesis we present the loads that occur on gyrocopter. Loads on gyrocopter are different than on the other aircrafts. Main reason is that they are operating in autorotation. Even though that the maximum allowed load faktors are between 3 and 3,5, these values cannot be reached under normal flying conditions. Additionally in the process of manufacturing the gyrocopter, the safety factor is also taken into the account. Load test were conducted in Trixy Aviation Corporation. In thesis there are represented calculated load tests for gyrocopter and required power for pre rotation for the NACA 9h12 profile. From presented calculations is clear that gyrocopters are designed for considerable amount of security, mainly due to strict regulation. Another advantage is that gyrocopters for autorotation do not need high amount of power, which means that there is a possibility of different sources providing the required working power.