It will be discussed features of the in-service short crack growth (SCG) through the foil base of the turbine blades manufactured from the superalloy GS6K, Fig.1. There were several cases of inflight fatigue failures turbine blades at the airplane have flown (500–1500) hours. The blade frequency during flight under the biaxial cyclic loads of bending-torsion is approx. 4 kHz. So, the material in-flight fatigue failure took place in VHCF (very-high-cycle-fatigue) area — (4000×3600×[500–1500]) = (0.7–2.0) ×10
cycles. There was during flight temperature neat to the 5000C around the blade volume where the fatigue fracture process was performed.