Bird collision is one of the most important safety issues in the aviation industry. All modern aircraft designs are designed with bird collisions in mind. Experiments on aircraft collisions with birds are very expensive. Therefore, the importance of numerical modeling techniques has increased. Airplane structural elements are highly vulnerable to in-flight damage from bird impact. A theoretical approach and results of numerical modeling of the dynamic response of the horizontal stabilizer leading edge during bird impact are presented. The modeling is performed using the finite element method. The bird is modeled as an ellipsoid. The pressure impulse reproducing the bird impact is derived from hydrodynamic theory. The focus is on verifying the stresses and deformations of the horizontal stabilizer leading edge in the impact zone. The numerical model has been validated with published experimental results and will be further used to investigate the effect of various parameters on the dynamic behavior of the leading edge of the aircraft.