ENHANCED RIG CHECK AND LEAK DETECTION OF AIRCRAFT DOORS
FIG6 is a side view of the leak testing device in an illustrative embodiment
FIG6 is a side view of a leak testing device 600 in an illustrative embodiment. As shown in this example, components of the leak testing device 600, including the structural frame 310 and the crossbars 320, may be shaped or oriented to correspond with or match the curvature of the external surface of the aircraft 100. Each of the suction cups 340 may be attached to a bottom side 602 of the structural frame 310 via a t-bar 610 and a pivot joint 620. The bottom side 602 is generally the aircraft-facing side of the structural frame 310 and the crossbars 320 that is opposite to the top side 604. The t-bar 610 extends perpendicularly from the crossbar 320 and mechanically couples the suction cup 340 with the crossbar 320 and structural frame 310. The pivot joint 620 enables rotation of the suction cup 340 about the t-bar 610 to orient a suctioning surface 622 of the suction cup 340 according to the surface curvature of the aircraft door 150, thereby facilitating secure engagement for pulling the aircraft door 150.
side view
150
aircraft door aircraft doors
620
pivot joint
634
engagement surface
600
leak testing device
610
t-bar
632
spring
604
top side
602
bottom side
630
floating mount floating mounts
340
suction cups suction cup
410
gasket channel gasket channels
622
suctioning surface
['1. An apparatus (300, 400, 500, 600) for leak testing a seal (270) between an aircraft door (150) and a fuselage (130) of an aircraft (100), the apparatus comprising: a structural frame (310) including: a suction cup (340) configured to suction an outer surface (202) of an aircraft door (150); and legs (330) configured to contact an outside of a fuselage and to extend in length to push the structural frame (310) away from the fuselage (130) and cause the suction cup (340) to pull the aircraft door (150) toward an outside of the aircraft (100) to tighten the seal (270) between the aircraft door (150) and the fuselage (130) of the aircraft (100).', '2. The apparatus of claim 1 wherein: the structural frame (310) further including: a crossbar (320) sized to straddle the aircraft door (150) outside the aircraft (100), wherein the crossbar couples with the legs (330) at either end of the crossbar, and wherein the crossbar couples with the suction cup (340) at a location between the legs; and a gasket channel (410) on a bottom side of the structural frame (310), the gasket channel being sized to correspond with an outer periphery of the aircraft door (150) and configured to fluidly couple with the seal (270) between the aircraft door and the fuselage (130).', '9. The apparatus of claim 1 wherein: the structural frame (310) including: one or more floating mount supports (630) attached to a bottom side (602) of the structural frame, the one or more floating mount supports having springs (632) to provide a spring contact force between the aircraft door (150) and the structural frame to facilitate alignment of the structural frame with respect to the aircraft door while the suction cup pulls the aircraft door.']