In this paper, the pitch angle control of a laboratory model helicopter is discussed. The control has some specific features. As a main feature, it is observed that the steady state control command is completely dependent on the setpoint, so error-based controller design is not applicable to this case. Moreover, the system has a highly oscillating dynamics. In order to solve this control problem, two controllers are designed, an artificial neural network, whose input is the setpoint, is used to provide the steady state control command, and a fuzzy inference system ,whose input is the error of the system, is used to provide the transient control command. The total control command is the sum of the aforementioned two control commands. It is proved that both ANN and FIS are bounded-input bounded-output (BIBO) systems.