The aim of this research is to develop a methodology which can be utilized to certify an aircraft for tire debris impact onto structural components and also to predict structural response by numerical simulation. After the aircraft experiences a tire burst scenario, tire debris projected from the rotating tire can impact the structural components of the aircraft. European Aviation Safety Agency's notice of proposed amendments (CS 25.734) demonstrated that the structural components and systems which are essential to the safe operation of aircraft should be protected from the damaging effects of tire debris. In this study, a computational methodology is developed to model and analyze the effects of tire debris impact on aircraft structural components. Experimental data from the tire fragment impact test on to the aluminum plate is compared with the numerical data to validate the tire debris model developed in this study. Parametric study is then conducted on validated tire debris model by impacting it onto the aircraft inboard flap. Inboard flaps are one of the major structural parts which are located in the zone of vulnerability defined by European Aviation Safety Agency and Federal Aviation Administration. Structural deformations and energy analysis on inboard flap by impacting tire debris model at two locations for different angle of attack and varying impact velocities are to be considered for this study. Detailed geometry of the inboard flap for the aircraft and tire debris are modeled in Catia V5 R21. Finite element modeling and fastener connections are defined in Altair Hypermesh 12.0. Material properties and boundary conditions are defined in LS-Prepost 4.2. This study provides a computational methodology to certify aircraft as per certification standards. This methodology provides design engineers the effects of tire debris impact on a structural component and also to change initial design requirements for structural components.