The landing gear is a vital structural unit of an aircraft that enables it to take off and land safely on the ground. A variety of landing gear arrangements are used depending on the type and size of an aircraft. Nowadays we can see that majority of failures of aircraft structure take place because of the malfunction of the landing gear system solely. This work is mainly focused on structural design and analysis of the main landing gear for an aircraft, that is economical and possesses a high strength to weight ratio but still simple in design. A typical landing load case will be assumed for which structural analysis will be carried out. During landing, there will be three different types of loads: 1. Vertical load (Compressive Load) 2. Drag load 3. Sideload Drag load and sideload values are terribly tiny in comparison to compressive load. So we will be focusing on the Vertical load. So we have taken the standard landing gear of an aircraft and it is designed by using Solid-works 2019 and analyzed for structural safety using ANSYS 19.2 software. The maximum possible load is given as design load. The landing gear assembly is analyzed for the traditional metallic materials like Aluminium Alloy-AlSI1030 Carbon Steel, Structural Steel IS2062 Fe440, and Titanium Alloy-Ti-8Al-1Mo-1V using ANSYS software and by comparing the results obtained by the mentioned material the best suitable material will be concluded that may be considered as best suitable and safer material.