The main goal of the present paper is a numerical study of the fatigue strength indicators in filled holes using the example of a repair patch on an aircraft panel. The stress state characteristics of the first hole were considered in most detail being the most load-bearing and therefore the most susceptible to the formation of fatigue cracks. The analysis of the finite element mesh density in the calculated holes was carried out to stabilize the obtained values of the equivalent stresses in the contact elements. The acquired data was further processed to obtain the dependencies of the fatigue safety margins reduced to a symmetric cycle in normal and shear stresses for a filled hole with a clearance fit, an interference fit and for a mixed type of bolt setting. The results were used to determine a preferable type of fit for the bolted joint of the first hole in the patched panel for the compressed and tensioned zone.