Question 5 An Aircraft Fuselage Skin Has Been Damaged And Repaired 5 1 If The Damage Has Been Cut To 75 Mm Horizonta 1 (74.39 KiB) Viewed 14 times
Question 5 An Aircraft Fuselage Skin Has Been Damaged And Repaired 5 1 If The Damage Has Been Cut To 75 Mm Horizonta 2 (55.57 KiB) Viewed 14 times
Question 5 - An aircraft fuselage skin has been damaged and repaired. 5.1 If the damage has been cut to 75 mm (horizontally) and 50 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 = 480Mpa and Ultime Shear Stress is 250MPa ). The skin thickness is 1.6 mm. In calculation, consider; calculate the cross-sectional area (vertically and horizontally of the cut) Longintunal load (tension) Circumferential load (tension due the pressurization)
5.1 If the damage has been cut to 75 mm (horizontally) and 50 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 = 480Mpa and Ultime Shear Stress is 250MPa ). The skin thickness is 1.6 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 tenison and shear (10 marks) b). Write the repair instruction based on the above diagram. The repair instruction must have inspection, removing of damage, fabrication of doubler, installation of doubler and post repair inspection. (10 marks)
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