Fatigue test data are presented for aluminium alloy specimens under simulated aircraft gust and manoeuvre loadings, excluding effects of ground-to-air loading cycles. The data show the cumulative fatigue damage as a function of the maximum stress, the material proof stress and the stress concentration factor. The data are presented such that a comparison with the Palmgren-Miner-Hypothesis may be made. The data have been obtained from tests on complete wings and riveted sections and also on notched bars and plates. The loads were ordered in either programmed or random block sequences or in random half cycles about a fixed datum.