5. Conclusion
Loading in operation and at the device of structural components of the
RRJ-type aircraft wing with variable stress amplitudes leads to a long
period of fatigue crack propagation in them, which is approximately 50%
of the total lifetime of the structure. It allows to organize reliable
monitoring of crack propagation with a large operating time interval
between adjacent inspections. The duration of the fatigue crack advance
per flight can be approximately 80 variable loading cycles.