The brushless direct current motor (BLDCM) for aviation fuel pump has the blockage rotor failure fault phenomena. The fault factors, detecting technologies, and severity, controllability and impact areas are analyzed, and a method of fault detection and emergency control mechanism for BLDCM is designed. Then, for the operating condition of the BLDCM during and after blockage, a method of fault detection and emergency control mechanisms based on the BLDCM speed and bus current is designed and the simulations are completed. With the help of the existed BLDCM test bench for fuel pump, the fault detection and emergency control mechanism verification under the condition of the BLDCM blockage failure are completed. Based on the traditional stoppage protection, an emergency control mechanism of blockage failure which reduces the PWM duty cycle and delayed restart is designed according to the occurrence probability and disappearance sequence of the blockage failure in the BLDCM operation process. The control mechanism improves the survival ability of the system after blockage failure and reduces the false alarm rate. The results have technical maturity and provide engineering application value.