In the field of civil aircraft engineering, the accurate measurement of dynamic landing response load is of utmost importance. This paper focuses on developing a comprehensive test method for this purpose. The research is carried out in multiple aspects. Firstly, in the flight test method, considerations are made to ensure the prototype lands symmetrically under heavy weight and relevant parameters are measured accurately. Flight test instrumentation and modification involve installing a large number of vibration and strain sensors with appropriate sampling rates and ranges, along with high-speed cameras and other sensors for speed and landing time measurement. Risk assessment is crucial as the test has a high risk of heavy landing, so safety measures like pre-flight inspections and familiarizing test personnel with procedures are emphasized. Configuration evaluation determines the optimal payload distribution for maximum landing load response. The developed method is applied to a prototype’s flight test, and the test result validity analysis shows the stability of the prototype during landing and the normalcy of sensor data, validating the method. However, some improvements are identified, such as increasing the sampling rate of line displacement sensors, deploying more high-speed cameras if possible, and pasting targets closer to the aircraft’s center of gravity. This research provides valuable guidance for future dynamic landing response load tests of civil aircraft.