The civil aircraft must undergo the full-scale fatigue test according to the airworthiness regulations，so as to obtain the type certificate. The new generation turboprop regional aircraft MA600F rear fuselage fatigue test will need too long period and high cost under the conventional technology, which affects the airworthiness certification and service use. Carrying out accelerated research on fatigue test of MA600f rear fuselage can obtain airworthiness permit and be put into commercial use as soon as possible. At the same time, it provides support for the optimization and improvement of design and manufacturing process, which is of great economic value and great significance to improve test technology. An integrated loading frame was designed according to the loading situation of rear fuselage fatigue test to complete installation, maintenance and inspection quickly. The equivalent damage conversion method was established to simplify the load spectrum based on DFR and liner damage accumulation theory. The overall load balance optimization was proposed based on nonlinear programming. The two above acceleration methods were applied to the fatigue test of small test pieces and MA600F rear fuselage. The cycles number of small test pieces was reduced by about 98%, and the fatigue life results were within engineering reasonable range. The crack damage of the rear fuselage acceleration test occurred during 15000 cycles, which is basically the same as the damage result of 25000 cycles in the conventional full-scale fatigue test.