Abstract: Systems and methods are provided for assembling an airframe of an aircraft, including receiving a half barrel section of fuselage, advancing the half barrel section in a process direction across multiple stations to separately and simultaneously perform work on the half barrel sections, and subsequently joining the half barrel segments to form a section of the airframe. Each pair of half barrel sections, such as upper and lower half barrels, are progressed through assembly line processes to be delivered to a joining station for joining the half barrels together to form a circumferential section of the fuselage. Multiple joined circumferential sections are joined together to form an elongated extent of the fuselage. Indexing features are provided in the assembly process to monitor and control the progression of the half barrel sections in the work stations of the assembly line process.

Abstract: Systems and methods are provided for aircraft assembly. The method includes receiving a half barrel section of fuselage in an assembly line having a plurality of serially arranged work stations; advancing the half barrel section in a process direction through the assembly line such that the half barrel section extends across at least a portion of the work stations; and performing work on the half barrel section with the portion of the work stations simultaneously.

Abstract: Systems are provided for fabricating a preform for a fuselage section of an aircraft. The system includes advancing a series of arcuate mandrel sections in a process direction through an assembly line, laying up fiber reinforced material onto the arcuate mandrel sections via layup stations, uniting the series of arcuate mandrel sections into a combined mandrel; and splicing the fiber reinforced material laid-up onto the arcuate mandrel sections.

Abstract: Systems and methods are provided for inspecting a wing panel. Some methods include advancing a wing panel through a Non-Destructive Inspection (NDI) station, and inspecting the wing panel with inspection heads at the NDI station. The wing panel may be suspended beneath a strongback during inspection and/or advancement, such as by using vacuum couplers and/or adjustable-length pogos of the strongback, and suspending may include enforcing a contour to the wing panel using the vacuum couplers and/or pogos. Other methods include receiving a wing panel at an NDI station and inspecting a portion thereof during movement through the NDI station. Some systems include a track, a strongback to suspend a wing panel beneath it and to advance along the track, and an NDI station disposed at the track to inspect the wing panel while suspended.

Abstract: Systems and methods are provided for fabricating a preform for a fuselage section of an aircraft. The method includes advancing a series of arcuate mandrel sections in a process direction through an assembly line, laying up fiber reinforced material onto the arcuate mandrel sections via layup stations, uniting the series of arcuate mandrel sections into a combined mandrel; and splicing the fiber reinforced material laid-up onto the arcuate mandrel sections.

Abstract: Systems and methods are provided for assembling an aircraft. The method includes receiving an upper half barrel section of fuselage that is in a crown up orientation and installing a crown module into the upper half barrel section.

Abstract: A method for fabricating a preform for a portion of an aircraft includes acquiring a sheet of broad good fiber reinforced material, trimming the sheet to form layup pieces having boundaries, placing the boundaries into alignment, arranging the layup pieces in a layup pattern to form a ply, performing a placement operation that transports the layup pattern onto a layup mandrel, and shaping the layup pattern into conformance with a contour of the layup mandrel.

Abstract: Systems and methods are provided for fabricating a preform for a fuselage section of an aircraft. The method includes advancing a series of arcuate mandrel sections in a process direction through an assembly line, laying up fiber reinforced material onto the arcuate mandrel sections via layup stations, uniting the series of arcuate mandrel sections into a combined mandrel; and splicing the fiber reinforced material laid-up onto the arcuate mandrel sections.

Abstract: Systems and methods are provided for assembling an airframe of an aircraft, including receiving a half barrel section of fuselage, advancing the half barrel section in a process direction across multiple stations to separately and simultaneously perform work on the half barrel sections, and subsequently joining the half barrel segments to form a section of the airframe. Each pair of half barrel sections, such as upper and lower half barrels, are progressed through assembly line processes to be delivered to a joining station for joining the half barrels together to form a circumferential section of the fuselage. Multiple joined circumferential sections are joined together to form an elongated extent of the fuselage. Indexing features are provided in the assembly process to monitor and control the progression of the half barrel sections in the work stations of the assembly line process.

Abstract: Systems and methods are provided for fabricating a part on a mandrel. The system includes a series of stations divided into at least two groups of stations, wherein each group of stations performs fabrication operations on a particular zone of the mandrel.

Abstract: Systems and methods are provided for aircraft assembly. The method includes receiving a half barrel section of fuselage in an assembly line having a plurality of serially arranged work stations; advancing the half barrel section in a process direction through the assembly line such that the half barrel section extends across at least a portion of the work stations; and performing work on the half barrel section with the portion of the work stations simultaneously.

Abstract: Systems and methods are provided for inspecting aircraft fuselages. Non-Destructive Inspection (NDI) stations inspect sections of a fuselage via pulsed-line assembly techniques. After each pulse, a section of fuselage is moved by less than its length, and one or more NDI stations disposed at different portions of the section to inspect the section of fuselage for out-of-tolerance conditions. A method for inspecting a structure for inconsistencies which includes advancing a structure along a track in a process direction through a Non-Destructive Inspection (NDI) station, indexing the structure to the NDI station and inspecting the structure with the NDI station.

Abstract: Systems and methods are provided for inspecting a wing panel. Some methods include advancing a wing panel through a Non-Destructive Inspection (NDI) station, and inspecting the wing panel with inspection heads at the NDI station. The wing panel may be suspended beneath a strongback during inspection and/or advancement, such as by using vacuum couplers and/or adjustable-length pogos of the strongback, and suspending may include enforcing a contour to the wing panel using the vacuum couplers and/or pogos. Other methods include receiving a wing panel at an NDI station and inspecting a portion thereof during movement through the NDI station. Some systems include a track, a strongback to suspend a wing panel beneath it and to advance along the track, and an NDI station disposed at the track to inspect the wing panel while suspended.

Abstract: Systems and methods are provided for assembling an aircraft. The method includes receiving a lower half barrel section of fuselage that is inverted to a keel-up orientation; and installing a floor grid into the lower half barrel section while inverted.