An Analytical study was carried out to determine low-cycle13; fatigue life and cr-lck growth rates under random load sequences, generated from three different combat aircraft lead exceedanee curves. The load sequences Were generated using different pseud andors proceedures, including simulated Rainflow cycle count, extreme-to-extreme excursions, upper to lower ooumd excursion- and unrestricted peak-trough excursions . Also, tie response of a fatigue meter to a random load sequences was simulated . Fatibue damage for the different load histories was computed using low-cycle fatigue concepts and fracture mechanics concepts . The analysis was carried cut usin material constants for an Al-Cu alloy
