The near-threshold behaviour of a high-strength low-alloy steel used in helicopter rotors under variable amplitude loading is investigated in ambient air and in vacuum. Strong sequence effects occur, in particular a high decrease in crack growth rates after overloads of 40% on maximum load while keeping the amplitude constant. A detailed study of the retardation phenomenon due to the overloads provides an explanation for the different behaviour observed in air and in vacuum and has laid the basis for a method of predicting crack propagation under helicopter loading spectra. NOMENCLATURE ct = parameter used to describe retardation A = maximum on retardation mastercurve (A = (Nr/Nt)max) B = sDecimen thickness A % = strain at rupture da -= crack growth rate d N ( $) a = nominal crack growth rate (without sequence effect) Aa = distance grown from the point of overload application AK = cyclic stress intensity factor AK,, = effective cyclic stress intensity factor AKq = equivalent cyclic stress intensity factor n = parameter used to describe retardation AN = number of cycles between overload application N, = number of delay cycles N, = total number of applied cycles after overload Ro,2 = yield stress R,,, = stress at failure R, = monotonic plastic zone size due to overloads x = fraction of growth within the overload plastic zone (x = Aa/R,) xa = point of maximum retardation W = specimen width