Fatigue life of damaged wing-fuselage fitting

Experimental analysis of full-scale wing was carried out for the purpose of numerical model verification. Comparisons of deformations measured and deformations calculated in FE simulations of aircraft wing deflection under load showed very good agreement, also confirming that loads acting on the wing-fuselage attachment lug were accurately evaluated in the analytical step. The detailed analysis has shown that the total maximum axial force transferred to lug by pin would be Pax,max = 208.83 kN, whereas the maximum transverse force would be Ptr,max = 20.17 kN.