Abstract: A collapsible flap deployment system for an aircraft wing that includes a support beam pivotably connected to a carrier beam, which is connected to a wing flap. A rear spar fitting is connected to a wing rear spar by a first plurality of fasteners and a second plurality of fasteners connects the support beam to the rear spar fitting. A fuse pin connects a link to the rear spar fitting. The fuse pin is configured to shear upon the application of a first predetermined force. An impact load to the bottom of the support beam puts the link into compression applying a force to the fuse pin until the fuse pin shears releasing the link from the rear spar fitting. The impact load rotates the support beam and carrier beam causing the second plurality of fasteners to fail releasing the support beam and carrier beam from the wing rear spar.

Abstract: Aircraft wings having improved deflection control ribs are described. An example aircraft wing includes a rear spar, an outboard flap, a rear spar fitting, and a deflection control rib. The outboard flap is movable relative to the rear spar between a stowed position and a deployed position. The outboard flap includes a closure rib and a roller coupled to the closure rib. The rear spar fitting is coupled to the rear spar. The deflection control rib includes a primary arm and a catch. The primary arm is coupled to and extends rearward from the rear spar fitting proximate a lower surface of the aircraft wing. The catch is coupled to and extends rearward from the primary arm. The catch includes an opening to receive the roller of the outboard flap when the outboard flap is in the stowed position.

Abstract: A flap deployment apparatus and system for a wing of an aircraft that includes a support structure having a first aerodynamic surface. A nose fitting secures the support structure to a forward portion of an aircraft wing and an aft fitting secures the support structure to an aft portion of the wing. A carrier beam having a second aerodynamic surface is coupled to the support structure. The carrier beam is movable between a stowed position and a deployed position. Links guide the carrier between the positions. The first and second aerodynamic surfaces are configured to define a continuous aerodynamic surface when the carrier beam is in the stowed position. The apparatus includes a nose fairing having a third aerodynamic and a mid fairing cover having a fourth aerodynamic surface. The third and fourth aerodynamic surfaces also defines the continuous aerodynamic surface when the carrier beam is in the stowed position.

Abstract: Aircraft wing flaps having aerodynamic restoration doors are described. An example apparatus includes a door to be rotatably coupled to a closure rib of a flap of an aircraft wing. The door is to be moveable between a deployed position and a retracted position. The flap has a leading edge and a cutout formed in the leading edge. The door is to fill a portion of the cutout when the door is in the deployed position.

Abstract: A collapsible flap deployment system for an aircraft wing that includes a support beam pivotably connected to a carrier beam, which is connected to a wing flap. A rear spar fitting is connected to a wing rear spar by a first plurality of fasteners and a second plurality of fasteners connects the support beam to the rear spar fitting. A fuse pin connects a link to the rear spar fitting. The fuse pin is configured to shear upon the application of a first predetermined force. An impact load to the bottom of the support beam puts the link into compression applying a force to the fuse pin until the fuse pin shears releasing the link from the rear spar fitting. The impact load rotates the support beam and carrier beam causing the second plurality of fasteners to fail releasing the support beam and carrier beam from the wing rear spar.

Abstract: A flap deployment apparatus and system for a wing of an aircraft that includes a support structure having a first aerodynamic surface. A nose fitting secures the support structure to a forward portion of an aircraft wing and an aft fitting secures the support structure to an aft portion of the wing. A carrier beam having a second aerodynamic surface is coupled to the support structure. The carrier beam is movable between a stowed position and a deployed position. Links guide the carrier between the positions. The first and second aerodynamic surfaces are configured to define a continuous aerodynamic surface when the carrier beam is in the stowed position. The apparatus includes a nose fairing having a third aerodynamic and a mid fairing cover having a fourth aerodynamic surface. The third and fourth aerodynamic surfaces also defines the continuous aerodynamic surface when the carrier beam is in the stowed position.

Abstract: Aircraft wing flaps having aerodynamic restoration doors are described. An example apparatus includes a door to be rotatably coupled to a closure rib of a flap of an aircraft wing. The door is to be moveable between a deployed position and a retracted position. The flap has a leading edge and a cutout formed in the leading edge. The door is to fill a portion of the cutout when the door is in the deployed position.

Abstract: Aircraft wings having improved deflection control ribs are described. An example aircraft wing includes a rear spar, an outboard flap, a rear spar fitting, and a deflection control rib. The outboard flap is movable relative to the rear spar between a stowed position and a deployed position. The outboard flap includes a closure rib and a roller coupled to the closure rib. The rear spar fitting is coupled to the rear spar. The deflection control rib includes a primary arm and a catch. The primary arm is coupled to and extends rearward from the rear spar fitting proximate a lower surface of the aircraft wing. The catch is coupled to and extends rearward from the primary arm. The catch includes an opening to receive the roller of the outboard flap when the outboard flap is in the stowed position.