This project work undertakes the task of analyzing stresses and preliminary designing of the tail structure members of a newly designed light agricultural aircraft. Schrenk's method has been used for estimating the span-wise lift distribution, while the tail weight was assumed to be uniformly distribution along the span. Hence, the shear force and bending moment diagrams have been obtained. Accordingly, the working shear and bending stresses within the flight envelope have been calculated. The design has been based on the limit load while the maximum bending and shear values are encountered at the tail root, with the gust load being neglected. The bending and shear margins are found to be positive along the semi-span/height, which shows good enough strength.