Integrally machined components used for highly loaded members and skin panels. In centre wing, spars are continuous across fuselage, the spars and associated frames being built as single assemblies extending between the engine nacelles. Forward wing sections built as separate components attached to each side of fuselage, spar loads being transferred to cross-members in lower part of main fuselage frames. Window surround in passenger cabin formed of integral skin-stringer panels machined from aluminium alloy planks. Nose is drooped hydraulically to improve forward view during take-off, initial climb, approach and landing.
Retractable visor is raised hydraulically to fair in windscreen in cruising flight.
The tail unit is a vertical fin and rudder only. Fin is multispar torsion box of similar construction to wings. Intakes are of RR.58 or AU2GN aluminium alloy with steel leading-edges. The engine bay has an Inconel centre wall with aluminium alloy forward doors and titanium rear doors. The nozzle bay, aft of the rear spar, is of welded Stresskin sandwich panels and heat-resistant nickel alloys.