An aircraft propeller is directly connected to the rotor shaft of an electric motor. Rotating components are axially supported by a bearing cap. A semi-analytical parametric (second moment of area dependent) mathematical model is built using the Laplace transform. The model is implemented in MATLAB to dimension the bearing cap. Static, modal, frequency response and transient analyses are performed on semi-analytical base. The determined mechanical stresses and deformations are verified in NX NASTRAN by means of the finite element method (FEM). Structural results are used as an input for fatigue calculations performed according to the analytical strength assessment guideline of the Cooperative Research Association for Mechanical Engineering (the FKM guideline). Based on optimal material utilization, a geometry of the bearing cap is developed. Using the fatigue software RIFEST, it is demonstrated that the analyzed geometry can withstand 1E7 load cycles due to propeller excitation