The invention provides a traction taking-off fatigue test method of a nose landing gear external cylinder suspension joint of an aircraft. The traction taking-off fatigue test method comprises the following steps that a static strength test is conducted on an external cylinder suspension joint test sample piece; a fatigue test is conducted, wherein loads in the X, Y and Z directions are loaded coordinately by adopting a sine wave cyclic loading mode with the stress ratio being 0.06 and the loading frequency being 2 Hz; the fatigue test is conducted by being divided into two stages that in thefirst stage, the load loading cyclic frequency is 7500 times, one-time visual check is conducted every 500 times, if a fatigue damage phenomenon occurs, the test is stopped, parameters are recorded, otherwise the test piece is subjected to crack detection, and the test piece enters into the second stage after being detected to be qualified; and in the second stage, the load loading cyclic frequency is 7500-15000 times, one-time visual check is conducted every 500 times, if the fatigue damage phenomenon occurs, the test is stopped, parameters are recorded, otherwise the test is continued untilthe ending, and cyclic times is recorded. According to the fatigue test method, the fatigue performance and the life of a partial structure are testified in advance by testing the test piece, and thedevelopment cost is lowered.