Certification calculations for the A380 have been produced.  Primary structure evaluated includes the mid and outer rear spar, and associated skin structure.

Front, and rear spar flanges to skin attachments and rear spar flanges were evaluated for fatigue and damage tolerance. A detailed fatigue life survey and stress survey was carried out. Fatigue critical locations per rib bay were identified and fatigue life was calcuated per rib bay. Crack growth analyses were carried out at fatigue critical locations and repeat inspection intervals were calculated.

Static strength analysis for generic rear spar structure was done together with a detailed assessment of joints, wing tip and jack point fitting.

Structural repair justification work is also carried out, where necessary, with account for in-service damage, wear and tear.