Production of airframe components

A method of producing at least part of an aircraft airframe, the at least part of an aircraft airframe being for attachment to a further system, the method comprising:

• providing an initial airframe structure comprising an airframe component having a first surface;
• providing an over press tool having a second surface, the second surface being substantially complementary to the first surface;
• coupling one or more layers of sacrificial material to the second surface of the over press tool;
• applying an adhesive to the first surface and/or the one or more layers of sacrificial material;
• moving the over press tool with the one or more layers of sacrificial material coupled thereto in such a way that the one or more layers of sacrificial material are pressed against the first surface of the initial airframe component, the adhesive being between the one or more layers of sacrificial material and the first surface of the initial airframe component;
• at least for some time during curing of the adhesive:
• positioning the over press tool such that the second surface is in contact with an outer surface of the one or more layers of sacrificial material and the one or more layers of sacrificial material are between the first and second surfaces;
• and
• forcing the over press tool against the first surface such that the over press tool exerts a normal force on the first surface;
• thereafter removing the over press tool from the one or more layers of sacrificial material;
• providing a reference structure;
• positioning the initial airframe structure with respect to the reference structure such that the position and orientation of the initial airframe structure relative to the reference structure is the same as the position and orientation relative to the further system that the initial airframe structure would have if the at least part of the aircraft airframe was attached to the further system;
• specifying a surface, the surface being a desired inner mould line for the at least part of the aircraft airframe;
• and
• machining said one or more layers of sacrificial material within a predefined tolerance wherein the step of machining said one or more layers of sacrificial material within a predefined tolerance comprises machining, using a cutting device, the one or more layers of sacrificial material such that the position and orientation of the outer surface of the one or more layers of sacrificial material with respect to the reference structure is the same as the position and orientation with respect to the further system that the specified surface would have if the at least part of the aircraft airframe was attached to the further system.