The fixed door assembly an aircraft has cracked by fatigue. Multiple fatigue cracks were found to have initiated on the L-angle close to the rivet region. Detailed examination revealed network of surface cracks in the vicinity of the crack origin regions. These surface cracks acted as stress concentration sites for multiple fatigue crack initiation. No metallurgical abnormalities were found responsible for the fatigue crack initiation. The type and nature of surface cracks observed in the crack initiation region indicates that these cracks are preexisting ones and appears to have developed during fabrication. The exact reason for presence of such surface cracks needs to be established and necessary measures incorporated to prevent the recurrence of similar failure.