<p>A model based on the Paris law that describes the growth of a crack at its random rates is proposed to predict the life cycle of fatigue crack-bearing aircraft skin sheet structures with a. Analysis of empirical and literature data demonstrated the relation between the coefficients C and m of this law for a wide range of structural aluminum alloys, viz log C decreases linearly with m. The data of numerous investigations into fatigue fracture kinetics wherein the coefficients of the Paris law were determined suggest a certain invariance of this relation influenced by the type of material and methodical aspects of testing, viz specimen design, loading modes, methods of calculating the stress intensity factor, etc. The points corresponding to the results of extensive interlaboratory studies on crack growth kinetics and much literature evidence define the general relation between the Paris law coefficients with a sufficiently high correlation level. A model of fatigue crack growth in aluminum alloys is proposed wherein, unlike the Paris equation, a single coefficient, viz the m exponent, is used. The random crack growth rate is given by a random value of this coefficient. From available empirical data from various studies, it was assumed that the m distribution for aluminum alloys follows the lognormal law, and the numerical characteristics of this distribution were determined. The crack growth in the aircraft fuselage skin sheet structures was simulated, and their predicted life up to the crack length limit was obtained. The lifetime distribution of cracked structures corresponds to the Pareto power law wherein the location parameter determines the onset of fracture and can be taken as a criterion predicting the limiting state of fatigue crack-bearing structures.</p>