This paper aims to calculate the fuselage loads, and analyzing the structure to determine the margin of safety.
Configuration of the aircraft was completed and frozen as addressed in a previous publications [1]. However, the aircraft should meet the agricultural requirements in Sudan. It could be manufactured locally and equipped with an engine that works with cheaper type of fuel (Jet-A1). Preliminary arrangement and sizing of structural component of fuselage has
been done. FEM software of ABAQUS® used for structure modeling and analysis, hence the shear forces and bending moment diagrams have been obtained. Accordingly, the working shear and bending stresses within the flight envelope have been calculated. The margin of safety is found to be positive along the fuselage structural parts, which shows
good enough strength.