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The traditional turbo-fan engine has fewer measurable parameters using traditional testing techniques, which leads to a lower accuracy of the troubleshooting test. In response to this problem, a turbo-fan engine fueling system troubleshooting test technology is proposed. Based on the structure of the afterburner fuel supply system of the aviation turbofan engine, the working principle of the afterburner fuel supply system is analyzed. By analyzing the abnormal fluctuation of the position of the measuring valve of the afterburner culvert, the cause of insufficient fuel flow of the afterburner culvert is determined. List the fault tree and confirm the abnormality of the frictional force of the linear variable differential transformer according to the analysis result of the fault cause. Investigate the structure of linear variable differential transformer, use F150 type endoscope to observe the metal deposits on the bottom of the transformer, and complete the swing valve troubleshooting test of the afterburner fueling system. Start the fuel supply device according to the afterburner, analyze the specific failure cause, and calculate the pressure loss during the startup process to obtain the fuel flow of the working nozzle of the aviation turbofan engine. Contrast analysis and simulation of the pump outlet pressure and actual pressure when the electromagnetic valve is closed, excluding the ignition failure of the afterburner fuel supply system. It can be known from the experimental results that the test accuracy of this technology is relatively high, which can reach a maximum of 0.9815, providing support for the system's stable working margin.