The analysis of the cyclic stresses on part of the landing gear of an aircraft shows that during each flight it is subjected to the following stress history:

100 000 cycles at ± 50 MN/m ²

10 000 cycles at ± 100 MN/m ²

        500 cycles at ± 150 MN/m ²

        200 cycles at ± 180 MN/m ²

        100 cycles at ± 185 MN/m ²

           50 cycles at ± 200 MN/m ²

           10 cycles at ± 210 MN/m ²

If the S–N curve for the part material is given by S = 500 N ^–0.064 , where S is in MN/m ² , estimate how many flights this component can withstand before fatigue failure occurs.