Abstract: A method of manufacturing aircraft parts includes creating corresponding 3D geometry models representing surface features and holes of the aircraft parts sized to nominal dimensions. The method includes sending the 3D geometry models to respective manufacturing facilities for each to generate a NC machining program directly from a 3D geometry model, with instructions for a single NC machining apparatus to machine an aircraft part, and including instructions to machine the surface features and/or holes to the modeled dimensions. And for each of the respective manufacturing facilities to machine the aircraft part utilizing the NC machining program. For this, the NC machining apparatus utilizes tool(s) set at substantially the modeled dimensions, instead of at a high or low side of related tolerance range(s) to allow for tight geometric dimensioning and tolerancing requirements. This method enables the full process capability of the CNC machines while utilizing inspection tolerances that are measurable.

Abstract: A method is provided for assembling an aircraft structure assembly composed of a plurality of sections without use of any shimming, locating fixtures or final-hole-size drill jigs. The method includes supporting a first and second frame sections on respective adjustable supports, and positioning an interconnecting frame section therebetween. The method includes aligning first pre-drilled mating holes in the interconnecting frame section, and installing fasteners through the aligned, first pre-drilled mating holes. The method includes aligning second pre-drilled mating holes in structural mating sections, and installing fasteners through the aligned, second pre-drilled mating holes. The method includes positioning the structural mating sections relative to the first and second frame sections and the interconnecting frame section. The structural mating sections are assembled inwardly from the first and second frame sections that form an outer perimeter structure of the aircraft structure assembly.

Abstract: A method of manufacturing aircraft parts includes creating corresponding 3D geometry models representing surface features and holes of the aircraft parts sized to nominal dimensions. The method includes sending the 3D geometry models to respective manufacturing facilities for each to generate a NC machining program directly from a 3D geometry model, with instructions for a single NC machining apparatus to machine an aircraft part, and including instructions to machine the surface features and/or holes to the modeled dimensions. And for each of the respective manufacturing facilities to machine the aircraft part utilizing the NC machining program. For this, the NC machining apparatus utilizes tool(s) set at substantially the modeled dimensions, instead of at a high or low side of related tolerance range(s) to allow for tight geometric dimensioning and tolerancing requirements. This method enables the full process capability of the CNC machines while utilizing inspection tolerances that are measurable.

Abstract: A method is provided for assembling an aircraft structure assembly composed of a plurality of sections, and doing so without use of any shimming, locating fixtures or final-hole-size drill jigs. The method includes supporting the first and second frame sections on respective adjustable supports, and positioning the interconnecting frame section therebetween. The method includes aligning first pre-drilled mating holes in the interconnecting frame section with first pre-drilled mating holes in the first and second frame sections, and installing fasteners through the aligned, first pre-drilled mating holes. The method includes positioning a structural mating section relative to the first and second frame sections and interconnecting frame section.

Abstract: A method is provided for assembling an aircraft structure assembly composed of a plurality of sections, and doing so without use of any shimming, locating fixtures or final-hole-size drill jigs. The method includes supporting the first and second frame sections on respective adjustable supports, and positioning the interconnecting frame section therebetween. The method includes aligning first pre-drilled mating holes in the interconnecting frame section with first pre-drilled mating holes in the first and second frame sections, and installing fasteners though the aligned, first pre-drilled mating holes. The method includes positioning a structural mating section relative to the first and second frame sections and interconnecting frame section.

Abstract: A method is provided for assembling an aircraft structure assembly composed of a plurality of sections, and doing so without use of any shimming, locating fixtures or final-hole-size drill jigs. The method includes supporting the first and second frame sections on respective adjustable supports, and positioning the interconnecting frame section therebetween. The method includes aligning first pre-drilled mating holes in the interconnecting frame section with first pre-drilled mating holes in the first and second frame sections, and installing fasteners though the aligned, first pre-drilled mating holes. The method includes positioning a structural mating section relative to the first and second frame sections and interconnecting frame section.