Reliable and stable performance is a key requirement for controlling Unmanned Aerial Vehicles (UAVs). Traditional control systems are typically designed to maintain stable flight and ensure safe operation. However, UAVs are susceptible to various flight faults that can compromise performance and potentially cause instability. Such instability poses significant risks to properties, lives, and the operating environment. To mitigate these risks, it is essential to develop a system that can detect faults, pinpoint their location and severity, and adapt in real-time, allowing the UAV to maintain safe operation. Although analyzing the impact of faults on UAV performance is critical for selecting optimal tolerance and detection methods, few research works has been done in this area, especially with hardware. This research study evaluates the control system performance of a 2-degree-of-freedom (2DOF) two-rotor helicopter under various actuator faults, including different blade break types and thicknesses. The analysis demonstrates how various fault conditions affect performance metrics, showing that faults contribute to performance degradation and induce vibrations in the system, especially in scenarios involving imbalance or asymmetry.