ESDU 83007 gives constant amplitude fatigue crack propagation rate data for several aluminium alloy sheet materials commonly used in the aerospace industry. The data have been derived from tests in laboratory air at room temperature and mean crack propagation rate curves are presented in terms of the stress intensity factor range and the stress ratio. Where possible, curves representing the upper limit of 95 per cent of the data are also provided. The range of propagation rate covered is from 1E-3 m/cycle (3.9E-2 in/cycle) down to the fatigue threshold factor range at 1E-11 m/cycle (3.9E-10 in/cycle). The effects of variations in stress ratio, test piece thickness, grain flow and environment are discussed. Details of all the alloys and types of test pieces are tabulated and summary curves compare the performance of the different alloys. Curves showing the effect of variations in the value of stress ratio at threshold for the various alloys are also presented.