1. A method of making an airplane fuselage section from a plurality of individual subassemblies including panels, frame members and a floor grid, comprising: drilling coordination holes in the marginal regions of said panels said panels each including longitudinal stiffening stringers, stringer clips, and shear ties fastened thereto; aligning said coordination holes in adjacent edges of a plurality of panels; fastening said panels together temporarily with temporary fasteners through said aligned coordination holes; clamping said panels together along said adjacent edges; drilling holes in said adjacent edges of said panels with a single drill plunge for each hole during said clamping of said panels: riveting said panels together along said adjacent edges through the drilled holes during said clamping of said panels to produce a superpanel; drilling a coordination hole in each of said stringer clips of said superpanel and corresponding coordination holes in said frame members; orienting said frame members on station planes adjacent corresponding stringer clips; aligning said coordination holes in said stringer clips with said corresponding coordination holes in said frame members; fastening said frame members to said stringer clips temporarily with temporary fasteners through their aligned coordination holes; clamping said frame members to said stringer clips and to said shear ties fastened to said superpanel and extending between said stiffening stringers along said station planes; drilling holes in said frame members and their corresponding stringer clips with a single drill plunge for each hole during said clamping of said frame members: riveting said frame members and their corresponding stringer clips together through the drilled holes during said clamping of said frame members: drilling holes in said frame members and corresponding shear ties with a single drill plunge for each hole during said clamping of said frame members: riveting said frame members and their corresponding shear ties together through the drilled holes during said clamping of said frame members: drilling a coordination hole adjacent each end of a plurality of cross members of said floor grid, and corresponding coordination holes in said frame members at each location therealong at which it is desired to connect said floor grid to said frame members; orienting said floor grid adjacent said frame members and aligning said coordination holes in said cross members of said floor grid with said corresponding coordination holes in said frame members: fastening said cross members to said frame members temporarily with temporary fasteners through their aligned coordination holes; clamping said floor grid cross members to said frame members; drilling holes in said cross members and said frame members with a single drill plunge for each hole during said clamping of said cross members: fastening said cross members and said frame members together through the drilled holes during said clamping of said cross members to form a fuselage lower lobe: drilling coordination holes along two longitudinally extending edges of said fuselage lower lobe, and along two corresponding longitudinally extending edges on a fuselage upper lobe; orienting said fuselage upper lobe over said fuselage lower lobe and aligning said coordination holes along said longitudinally extending edges of said fuselage upper lobe with said corresponding coordination holes along said longitudinally extending edges of said fuselage lower lobe; sealing and temporarily fastening said upper lobe and said lower lobe with temporary fasteners along said longitudinally extending edges through their aligned coordination holes; clamping said fuselage upper and lower lobes together along said longitudinally extending edges; drilling holes in said fuselage upper and lower lobes with a single drill plunge for each hole along said longitudinally extending edges during said clamping of said fuselage upper and lower lobes; and fastening said fuselage upper and lower lobes together through the drilled holes along said longitudinally extending edges to form a fuselage section; wherein said drilling of said coordination holes in said panels, in said stringer clips, in said shear ties, in said frame members, in said cross members of said floor grid, and in said fuselage lower and upper lobe is done using an end effector carried by a precision computer controlled robot that is directed to the drilling locations using a digital data set taken directly from digital engineering part definition records, said drilling locations being determined with respect to reference points on each drilled component, so the spatial relationships between key features of said subassemblies as defined by said coordination holes make said subassemblies self-locating and intrinsically determinate of the final contour and configuration of said fuselage section, independent of tooling.