In this study, topology optimization of a jet engine bracket which was proposed from GE Aviation challenge for improving the brackets is presented using finite element analysis (FEA). The minimum mass, maximum equivalent stress and first natural frequency are selected for the objective functions to topology optimization. Then, topology optimization procedure is implemented according to the identified boundary conditions and objective functions. Finally, the manufacturing model is obtained and compared with the original model according to the maximum equivalent stress, mass reduction and first natural frequency. Also, modal analysis and static analysis results of the proposed models are presented.