(Solved): \( 5.1 \) If the damage has been cut to \( 75 \mathrm{~mm} \) (horizontally) and \( 50 \mathrm{~mm ...

\( 5.1 \) If the damage has been cut to \( 75 \mathrm{~mm} \) (horizontally) and \( 50 \mathrm{~mm} \) (vertically). a). Calculate the resultant load lost, take into consideration of circumferential loads due to pressurization on top of the fuselage longitudinal load. The skin is Aluminum Alloy 2024-T3 (Ultimate Tensile Stress = \( 480 \mathrm{Mpa} \) and Ultime Shear Stress is \( 250 \mathrm{MPa}) \). The skin thickness is \( 1.6 \mathrm{~mm} \). In calculation, consider; calculate the cross-sectional area (vertically and horizontally of the cut) Longintunal load (tension) Circumferential load (tension due the pressurization) Shear load along the cut resultant load from the tension and shear