An investigation of buckling of the crown skin of an aircraft fuselage, and its effect on the fatigue life of that crown skin are presented in this thesis. Buckling occurs in crown skin segments between the landing gear when a high gross weight aircraft is on the ground. This ground load experience forms one half of a load cycle called the ground-air-ground cycle which is noted to be the major cause of crown skin fatigue damage. Four fuselage cross sections, varying in size, have been chosen for study. Each section is examined with a range of applied loads so that the trends established may be more easily applied to any given high gross weight aircraft. It is smooth tan increase in crown skin thickness does not necessarily cause an increase in fatigue life of the crown skin. This becomes more noticeable as cross sectional area is increased. It is recommended that methods other than increasing crown skin thickness be used to increase crown skin fatigue life.