Validated stress justification reports for the A350 concessions and repair instructions for composite rear spar and metallic rib posts and attachments. Some specific divergences and defects are summarized as follows:
OE was responsible for preliminary sizing and strength justification of the CFRP Spars and Form Ribs, all metallic Load Introduction Ribs with fail-safe requirements and Support End Ribs, Trailing Edge sandwich construction parts with metallic faceplates and honeycomb cores and all their attachments to upper and lower covers for the A350 XWB aircraft inboard flap. The detail stress analyses were all being carried out in accordance with Airbus requirements.
OE was responsible for preliminary sizing and strength justification of the CFRP Spars and Form Ribs, all metallic Load Introduction Ribs with fail-safe requirements and Support End Ribs, Trailing Edge sandwich construction parts with metallic faceplates and honeycomb cores and all their attachments to upper and lower covers for A350 XWB aircraft outboard flap. The detail stress analyses were all being carried out in accordance with Airbus requirements.
Detail stress analysis performed in order to size the upper and lower covers of the inboard flap of the A350 aircraft based on laser beam welded skin-stringer configuration made in AlMgSc alloy. In comparison with the A340-600 inboard flap baseline design, the total potential weight savings were determined. All design, manufacturing, fatigue and strength requirements (static yield and ultimate strength, local skin and stringer buckling, global skin-stringer buckling and post-buckling, crippling and the diagonal tension effects) were taken into account.