A canopy for an aircraft includes a pivot assembly including a first hinge and a second hinge opposite from the first hinge. The first hinge includes a first pivot slot having a first length. The first pivot slot is configured to retain a first aft pin of a fuselage of the aircraft. The second hinge includes a second pivot slot having a second length. The second pivot slot is configured to retain a second aft pin of the fuselage of the aircraft. The first length differs from the second length.

An aircraft windshield wiper system includes a wiper arm, a wiper blade coupled to a first end of the wiper arm, and an output shaft coupled to a second end of the wiper arm. The wiper blade includes a fluid dispensing system including nozzles, a fluid control unit, fluid lines, fluid source, and a user interface. The wiper blade with the fluid dispensing system is configured to dispense a variety of fluids directly from the wiper blade onto the windshield of an aircraft.

An assembly provided with a panel glued by a glue joint to a support, the assembly facilitating the detachment of the panel from the support, the glue joint being interposed between an internal environment and an external environment. The assembly comprises at least one tunnel, each tunnel passing all the way through the glue joint along a transverse axis and connecting the internal environment and the external environment, each tunnel being reversibly blocked by a stopper.

The present invention relates to aircraft engine shield placed over the front of the jet turbines and across the wind shield, made up of heavy duty metal or other suitable material to prevent bird strikes, having small air gaps which not only prevents birds from entry but also prevents any other external particle either small or large to enter the wind shield or front turbines which in turn protects the air craft from any problem,

A windshield assembly (110) comprises a support panel (102), a windshield (112), and a frame (140), surrounding the windshield (112). The frame comprises a frame inboard leg (142), which is in contact with an inboard windshield surface (114). A hinge (160) pivotally couples a frame-inboard-leg top portion (148) of the frame inboard leg (142) to the support panel (102) and has a pivot axis. A channel (161) is provided in the support panel (102). At least a portion of the frame-inboard-leg bottom portion (150), at least a portion of the frame-inboard-leg first lateral portion (152), and at least a portion of the frame-inboard-leg second lateral portion (154) are located in the channel (161). The channel (161) comprises a channel base leg (162). A seal (180) is located in the channel (161) between the channel base leg (162) and the frame inboard leg (142).

A coated transparency includes: a transparency; a base layer on the transparency, the base layer comprising at least one selected from an organic compound, an organosilicon compound, and a polysiloxane compound; a metal layer physically contacting the base layer; and a metal oxide layer on the metal layer, the metal oxide layer comprising aluminum doped zinc oxide (AZO).

The present disclosure provides a system for an aircraft. The system includes a rail having a bottom surface, and a first and a second sidewall extending from the bottom surface. The first sidewall, the second sidewall, and the bottom surface define a channel. The rail also includes blind holes, located in the bottom surface. The system also includes spacers, each comprising a stem and a top portion, extending substantially perpendicular to the stem. The stem of each of the spacers is configured to be positioned in a respective one of the blind holes such that a longitudinal axis of the top portion of each of the spacers is parallel to a longitudinal axis of the channel. The system also includes a structural component, a portion of which is configured to be positioned into the channel such that the structural component rests on the top portion of each of the spacers.

An ejection seat for an aircraft is disclosed. In various embodiments, the ejection seat includes a seat frame; and a moveable headrest attached to the seat frame, the moveable headrest including a first piercer assembly configured for fracturing a canopy.

An aircraft windshield wiper system includes a wiper arm, a wiper blade coupled to a first end of the wiper arm, and an output shaft coupled to a second end of the wiper arm. The wiper blade includes a fluid dispensing system including nozzles, a fluid control unit, fluid lines, fluid source, and a user interface. The wiper blade with the fluid dispensing system is configured to dispense a variety of fluids directly from the wiper blade onto the windshield of an aircraft.

The integration of a hinged door with a door leaf in a non-pressurized aircraft. The non-pressurized aircraft includes a canopy frame with a canopy frame cross-section profile. The canopy frame cross section profile has first and second canopy frame faces that are arranged at a predetermined angle relative to each other, and a third canopy frame face that is arranged between the first and second canopy frame faces. The non-pressurized aircraft further includes a hinge that is entirely arranged within the outline of the non-pressurized aircraft and pivotally mounts the door leaf to the third canopy frame face.