Fatigue failure is a complex phenomenon. Therefore, development of a fatigue damage model that considers all associated complexities resulting from the application of different cyclic loading types, geometries, materials, and environmental conditions is a challenging task. Nevertheless, fatigue damage models such as critical plane-based models are popular because of their capability to estimate life mostly within ±2 and ±3 factors of life for smooth specimens. In this study, a method is proposed for assessing the fatigue life estimation capability of different critical plane-based models. In this method, a subroutine was developed and used to search for best estimated life regardless of critical plane assumption. Therefore, different fatigue damage models were evaluated at all possible planes to search for the best life. Smith-Watson-Topper (normal strain-based), Fatemi-Socie (shear strain-based), and Jahed-Varvani (total strain energy density-based) models are compared by using the proposed assessment method. The assessment is done on smooth specimen level by using the experimental multiaxial fatigue data of 3 alloys, namely, AZ31B and AZ61A extruded magnesium alloys and S460N structural steel alloy. Using the proposed assessment method, it was found that the examined models may not be able to reproduce the experimental lives even if they were evaluated at all physical planes. KEYWORDS critical plane approach, damage assessment method, fatigue damage model, fatigue life estimation, multiaxial fatigue Nomenclature: b, axial fatigue strength exponent; b s , torsional fatigue strength exponent; c, axial fatigue ductility exponent; c s , torsional fatigue ductility exponent; k, Fatemi-Socie constant; B, axial energy-based fatigue strength exponent; B s , torsional energy-based fatigue strength exponent; C, axial energy-based fatigue toughness exponent; C s , torsional energy-based fatigue toughness exponent; E, tensile modulus of elasticity; E ′ e , axial energy-based fatigue strength coefficient; E ′ f , axial energy-based fatigue toughness coefficient; G, shear modulus; N A , fatigue life under purely axial loading; N f , number of cycles to failure; N T , fatigue life under purely torsion loading; W ′ e , torsional energy-based fatigue strength coefficient; W ′ f , torsional energy-based fatigue toughness coefficient; ΔE, total strain energy density; ΔE A , axial strain energy density; ΔE T , torsional strain energy density; Δε 1 , principal normal strain range; Δγ max , maximum shear strain range; ε ′ f , axial fatigue ductility coefficient; γ ′ f , torsional fatigue ductility coefficient; v, Poisson ratio; σ ′ f , axial fatigue strength coefficient; σ n , max , maximum normal stress at critical plane; σ uc , ultimate compressive strength; σ ut , ultimate tensile strength; σ yc , compressive yield strength; σ yt , tensile yield strength; τ ′ f , torsional fatigue strength coefficient