Aluminum alloys are widely used for constitutive parts of aircrafts and are consequently confronted with a wide range of temperature depending on altitude: from 300K (ambient temperature) on the ground down to 223K during a fly. Fatigue properties and particularly fatigue crack growth resistance at low temperature have been poorly studied. The literature provides results in cryogenic condition (77K) showing improved fatigue strength in Al-Li alloys [
]. This paper deals with a study of the fatigue crack propagation behavior of two high strength 2xxx Aluminum alloys elaborated in naturally-aged and peak-aged conditions.