An aircraft wing-to-body join method, the method comprising: applying photogrammetry targets to a wing root of an aircraft wing and to a wing stub of an aircraft body 16 assembly, wherein the wing root includes at least one wing root interface surface, wherein the wing stub includes at least one wing stub interface surface; measuring the wing root and the wing stub with a photogrammetry sensor to determine 3D locations of the photogrammetry targets; generating a wing root 3D surface profile for the at least one wing root interface surface and a wing stub 3D surface profile for the at least one wing stub interface surface by combining scans of a series of wing root inspection regions encompassing the at least one wing root interface surface and combining scans of a series of wing stub inspection regions encompassing the at least one wing stub interface surface, each wing root inspection region including at least two photogrammetry targets, each wing stub inspection region including at least two photogrammetry targets; and calculating a virtual fit between the aircraft wing and the aircraft body assembly that defines one or more gaps between the wing root 3D surface profile and the wing stub 3D surface profile; characterized in that the method further comprises: positioning at least three position sensors, wherein each position sensor is positioned within at least one of the wing root and the wing stub, wherein each position sensor is arranged to observe a distinct alignment pair of reference features (74, 76) for each position sensor, wherein each alignment pair of reference features (74, 76) includes a reference feature (74, 76) on the wing root and a reference feature (74, 76) on the wing stub; and aligning the aircraft wing to the aircraft body assembly to achieve a real fit consistent with the virtual fit using feedback from the at least three position sensors regarding relative positions of the reference features (74, 76) of each alignment pair of reference features (74, 76). applying photogrammetry targets to a wing root of an aircraft wing and to a wing stub of an aircraft body 16 assembly, wherein the wing root includes at least one wing root interface surface, wherein the wing stub includes at least one wing stub interface surface; measuring the wing root and the wing stub with a photogrammetry sensor to determine 3D locations of the photogrammetry targets; generating a wing root 3D surface profile for the at least one wing root interface surface and a wing stub 3D surface profile for the at least one wing stub interface surface by combining scans of a series of wing root inspection regions encompassing the at least one wing root interface surface and combining scans of a series of wing stub inspection regions encompassing the at least one wing stub interface surface, each wing root inspection region including at least two photogrammetry targets, each wing stub inspection region including at least two photogrammetry targets; and calculating a virtual fit between the aircraft wing and the aircraft body assembly that defines one or more gaps between the wing root 3D surface profile and the wing stub 3D surface profile; characterized in that the method further comprises: positioning at least three position sensors, wherein each position sensor is positioned within at least one of the wing root and the wing stub, wherein each position sensor is arranged to observe a distinct alignment pair of reference features (74, 76) for each position sensor, wherein each alignment pair of reference features (74, 76) includes a reference feature (74, 76) on the wing root and a reference feature (74, 76) on the wing stub; and aligning the aircraft wing to the aircraft body assembly to achieve a real fit consistent with the virtual fit using feedback from the at least three position sensors regarding relative positions of the reference features (74, 76) of each alignment pair of reference features (74, 76). positioning at least three position sensors, wherein each position sensor is positioned within at least one of the wing root and the wing stub, wherein each position sensor is arranged to observe a distinct alignment pair of reference features (74, 76) for each position sensor, wherein each alignment pair of reference features (74, 76) includes a reference feature (74, 76) on the wing root and a reference feature (74, 76) on the wing stub; and aligning the aircraft wing to the aircraft body assembly to achieve a real fit consistent with the virtual fit using feedback from the at least three position sensors regarding relative positions of the reference features (74, 76) of each alignment pair of reference features (74, 76).