The invention discloses a test system and a method for the air bleed mechanism of an aircraft engine. The test system comprises a servo control system, a hydraulic controller and a measurement mechanism. The servo control system and the hydraulic controller are connected together. An air-bleed valve servo-actuated rod is driven by the hydraulic controller, and then the on/off state of an air-bleed valve can be adjusted. One end of the air-bleed valve servo-actuated rod is connected with the air-bleed valve, and the other end of the air-bleed valve servo-actuated rod is connected with an intermediate case assembly. The air-bleed valve is arranged on the outer side of an air-bleed header pipe. The air-bleed header pipe is arranged on a case of a high-pressure compressor. The air-bleed valve servo-actuated rod is provided with a measurement mechanism. The air-bleed valve is provided with a loading assembly. According to the technical scheme of the invention, the invention also provides a test method for the air bleed mechanism of the aircraft engine. The test method is clear and feasible in test procedure and minute in loading process. Meanwhile, the working state of the air bleed mechanism of the aircraft engine can be really simulated and a load can be applied on a tester. Therefore, a reference is provided for the test on structures similar to the air bleed mechanism of the aircraft engine.