Inter spar ribs of wing of a transport aircraft is ubjected to various types of loads. One of the loads that poses
stability problem to the interspar ribs of a wing is brazier load, which arises due to flexure of the wing. This
paper describes about the finite element analysis of inter spar ribs of a wing at local level against brazier load.
This study has been taken place while converting metal wing in to composite wing. The objective of this study is to
reduce the weight penalty to the maximum possible extent by removing material wherever feasible. This paper is limited to discuss about the linear buckling analysis of ribs against brazier load. The buckling factor of ribs under
consideration are reported in terms of square root times the eigenvalue obtained from finite element analysis,
which represent the nonlinear effect of bending moment on brazier load. This study has helped to reconfigure/redesign the interspar ribs of wing. This has led to substantial weight saving of 2.85 Kg which accpunts 15.77% reductions of total mass of inter spar ribs
