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In this paper, a finite-time adaptive attitude control scheme is proposed based on fast terminal sliding mode surface for twin-rotor aircrafts with model uncertainties and external disturbances. A fast terminal sliding mode surface is constructed, and a piecewise continuous function is developed to avoid the singularity problem caused by differentiating the sliding mode variable. Then, the finite-time attitude controller is designed and adaptive update laws of system uncertainties are developed, such that the effect of the model uncertainties and external disturbances can be compensated. The Lyapunov synthesis is provided to show that the sliding mode variable, attitude error and velocity error could be uniform ultimate boundedness and converge to the neighborhood of the equilibrium within the finite time, and the setting time is relevant to the system state variable initial values. Finally, by contrast experiments of rectangular wave and S curve tracking, the effectiveness of the proposed scheme is validated on the twin-rotor platform. And that experimental results by using hyperbolic tangent function show that it can reduce the system flutter phenomenon.