An aircraft consists of large components which are connected by discontinuities like joints which are imminent while
they play an important role and are being subjected to failure under cyclic loading conditions. The occurrence of high stress
concentration and geometric irregularities which determine the primary load carrying capacity effects the performance of such
brackets. The failure of which may cause unexpected failure of the system there by the failure of aircraft. A primary load
carrying structure of an aircraft are longerons, stringers, spars and bulkhead. These structures are further supported by
splicing, truss structures and brackets etc. This bracket transfers load from the engine to a truss structure effectively. A bracket
being considered as a part of engine assembly that is safe from failure. The criteria being on weight in regard to the various
parts of the aircraft is looked at and studied, having to consider overall – strength. The static analysis (global) will be carried out
for the study
