The design of an aircraft involves various stages that at all these stages, adequate structural sterngth and stiffness analysis is required of the main components. this will enable the aircraft to perform its intended role at expected level. The aim of this project is to analyse the loading action of the selected component, fuselage in which the lateral forces acting was calculated. To obtain the accurate loading action, various cases have to eb taken into consideration in which, the study was confined to certain category of acases defined as ground cases, asymmetric glight cases and lateral manoeuvring cases. Detail study was conducted on the above mentioned categories to the scope of light civil conventional aircraft. many methods used for estimating the loading analysis were done based on the experience and expected values in conjunction with the assumptions made. These will later bet ransformed into a computer program running under Borland C++. Output results of the program is shown in ht shear force, bending moment and torsion together with the critical value diagrams. The result of this project is suffucuent enough to contribute in determining accurate parameters and values needed during fuselage structural designing stage.