=+Problem 5.14 The aircraft model of Figure 5.1 already considered in Example 5.1 (symmetric case) and in Problem 5.9 (antisymmetric case) can easily be treated using a simple finite element model. However, the resulting number of degrees of freedom for the model would 412 Mechanical Vibrations: Theory and Application to Structural Dynamics not allow to perform the analysis by hand. The problem will thus be solved numerically by developing an appropriate piece of software (using any numerical toolbox). The steps of the analysis will be as follows: