<p>The service life of aircraft is determined by their optimal weight characteristics. Achieving the optimal service life requires commercializing new methods for increasing the fatigue life of aircraft wings. To reduce the amount of aviation fuel that is neither produced nor drained, holes are made in the wing bottom panel stringers of wide-body long-range aircraft to allow it to flow. The operation and ground tests of aircraft show that such holes are fatigue crack nucleation sites and can lead to the premature failure of the wing structure. Various technological methods are used to increase the durability of the wing bottom panels in the area of fuel flow holes, most of which are based on the local deep plastic deformation (LDPD) of the stringer in the hole area. The study of the effectiveness of various schemes of the LDPD of holes using electrodynamic treatment (EDT) was carried out on specimens of stringers made of D16 aluminum alloy, which is used to manufacture aircraft wing stringers. The electrodynamic action was used as a force factor that ensures the dynamic contact interaction of the electrode (working tool for EDT) with the metal in the area of the hole to be treated. Three schemes of LDPD by EDT have been proposed, such as EDT-mandrelling, EDT-mandrelling+ compression, and EDT-compression. The maximum value of the longitudinal (relative to the metal loading direction) compressive stress component <i>σ</i>_<i>x</i> in the specimen after its LDPD by EDT reached –105 MPa, and of the transverse one <i>σ</i>_<i>y</i> = –120 MPa. The tests of specimens were carried out under a pulsating tensile loading cycle <i>σ</i>_<i>max</i> = 200–203 MPa. It is shown that the LDPD by EDT of specimens of aircraft wing stringers made of D16 aluminum alloy in the hole zone increases the resistance to delayed fracture by a factor of 1.6–2.5 and that the most effective treatment scheme is EDT compression.</p>