A methodology of formation of the optimal structural strength $\tau_{slice}$ is developed. Aviation fastening bolts made from titanium alloys for the purpose of balance of the combination of strength and plasticity properties by rational selection of a set of their basic mechanical characteristics, i.e., the conditional yield strength $\sigma_{Y}$, the ultimate tensile strength $\sigma_{S}$, and the relative reduction in area $\psi$ at the moment of sample destruction. As determined, the value of the structural strength $\tau_{slice}$ of aviation fastening bolts made from titanium alloys is formed by these basic mechanical characteristics, $\sigma_{Y}$, $\sigma_{S}$, and $\psi$, as well as by the true fracture stress $S_f$ under uniaxial tension tests. As shown, in order to increase the structural strength of aviation fastening bolts made from titanium alloys up to the required level of $\tau_{slice} \cong$ 850 MPa, technologists’ efforts must be aimed to increase the level of parameter $\sigma_{Y}$/$\sigma_{S}$ and to reduce the strain hardening exponent $n$ for advanced titanium alloys. The formation conditions for such a complex of properties make possible not only to form the best values of $\tau_{slice}$ purposefully, but also to give a justified forecast estimation of the possibility of further increase of this parameter.