In order to prevent an aircraft from falling accidentally into stall/spin status in the process of flying at a high angle of attack, the modern fly\|by\|wire combat aircraft in the flight control system is usually is adopted by left boundary protection module . However, such a phenomenon is difficult to stop during use.To insure flight safety, the departure sensitivity in flying at a high angle of attack needs to be evaluated by flight testing. Traditional level\|flight speed and convergent\|turn methods are unable to fully evaluate the aircraft departure sensitivity.According to the demonstration requirement of aircraft high angle of attack departure sensitivity and spin resistance, an evaluation method based on deceleration climbing maneuver is proposed. A set of flight test maneuvers are developed by flight simulation. Moreover, the flight test procedure is built to evaluate high angle of attack departure sensitivity and spin resistance of modern aircraft with angle of attack limit and anti\|spin control law. The method and procedure are validated on a certain type of aircraft. The result show that the method and procedure could satisfy the aircraft with the demonstration requirement. 