This paper presents the response of aircraft fuselage panel to the cabin pressure by idealizing the structure as a flat stiffened panel. The principal stresses developed in the fuselage due to the pressure difference at the altitude during the actual flight conditions were simulated by using the commercial FEA software MSC.PATRAN & MSC.NASTRAN. The response of structure for the hoop stress and longitudinal stress eveloped in the fuselage due to cabin pressurization is studied by using finite element analysis technique. emphasis was given to study the response of I, C and L types of the stringers for the load bearing capacity of the aircraft structure and comparison for the structural responses of stiffened panel was made between these types of stringers. From the analysis it was found that; I and C type of stringers have least deflection than L type; which is an important parameter for the safe design of the aircraft structure.