An aircraft door drainage system includes a precipitation receptacle disposed longitudinally along an upper edge of an aircraft door opening. The receptacle is mounted along the upper edge of the door opening by a plurality of brackets that connect the receptacle to an inside ceiling panel of the aircraft. The receptacle protrudes outward from the upper edge of the door opening into a path followed by precipitation falling off of an outer peripheral surface of a fuselage of the aircraft from locations above, forward, and aft of the door opening into the door opening when the aircraft door is in an open position. The receptacle remains clear of the aircraft door when the aircraft door is closed into the door opening. Drain hoses are connected at first and second ends of the receptacle to direct precipitation collected in the receptacle to an outside of the aircraft.

A drain mast is provided that includes a unitary structure having a first housing, a second housing, and a plurality of tubes extending between the first housing and the second housing. The unitary structure is configured to provide a plurality of fluid paths through the drain mast, each fluid path extending through the first housing, one of the plurality of tubes, and the second housing.

An assembly is provided for an aircraft propulsion system. A first seal wedge is configured with a first wedge-shaped cross-sectional geometry when viewed in a reference plane. A first aperture extends along a first axis within the first seal wedge. A second seal wedge is configured with a second wedge-shaped cross-sectional geometry when viewed in the reference plane. A second aperture extends along a second axis within the second seal wedge. A first drain tube supports the first seal wedge and is fluidly coupled with the first aperture. A second drain tube supports the second seal wedge and is fluidly coupled with the second aperture. A manifold is configured with an outlet. The manifold supports the first drain tube and the second drain tube. The manifold fluidly couples the first drain tube and the second drain tube in parallel with the outlet.

The invention relates to the field of aeronautical propulsion, and more specifically to an emptying and monitoring device and method for emptying and monitoring a fluid drained from an aircraft engine. The emptying and monitoring device comprises at least one first intake passage for receiving, directly from the aircraft, fluid drained from the engine, and a first quality sensor assembly for detecting at least one quality parameter of the fluid drained from the engine, having been admitted through the first intake passage.

An assembly is provided for an aircraft propulsion system. A first seal wedge is configured with a first wedge-shaped cross-sectional geometry when viewed in a reference plane. A first aperture extends along a first axis within the first seal wedge. A second seal wedge is configured with a second wedge-shaped cross-sectional geometry when viewed in the reference plane. A second aperture extends along a second axis within the second seal wedge. A first drain tube supports the first seal wedge and is fluidly coupled with the first aperture. A second drain tube supports the second seal wedge and is fluidly coupled with the second aperture. A manifold is configured with an outlet. The manifold supports the first drain tube and the second drain tube. The manifold fluidly couples the first drain tube and the second drain tube in parallel with the outlet.

An assembly is provided for an aircraft propulsion system. This assembly includes a first drain tube, a second drain tube, a container and a gas tube. The container fluidly couples the first drain tube to the second drain tube. The container is configured to receive fluid from the first drain tube. The gas tube is fluidly coupled with the container. The gas tube is configured to direct gas into the container for propelling the fluid received within the container into the second drain tube.

Systems and methods for managing waste (including liquid, solid, and mixed waste) without using a sink, worktop, or countertop disposal feature. Specific examples provide particular use in connection with an aircraft or other vehicle galley, lavatory, or any other location in which waste that requires disposal is generated. The disclosed embodiments may be installed in an initial galley or lavatory, or they may be used to retrofit an existing environment, such that an entire new disposal system or new sink footprint is not required.

A drain mast is provided that includes a unitary structure having a first housing, a second housing, and a plurality of tubes extending between the first housing and the second housing. The unitary structure is configured to provide a plurality of fluid paths through the drain mast, each fluid path extending through the first housing, one of the plurality of tubes, and the second housing.

A drainage system for an aircraft is taught herein. The drainage system includes a drain tube defining an orifice. The drainage system further includes a cover movable between a first cover position and a second cover position. The cover is configured to overlay the orifice when the cover is in the first cover position. The cover is configured to expose the orifice when the cover is in the second cover position. The cover is configured to move between the first cover position and the second cover position in the presence of air pressure.

Drainage devices intended to prevent the reentry of drained fluids, the devices including a base having a contact surface for mounting over a drainage opening in an aerodynamic surface, a mast portion connected to the base and extending away from the contact surface of the base, and a top portion connected to the end of the mast portion, the top portion having a periphery that is greater than the periphery of the mast portion and including an exit port. The top portion may include a cantilevered fence portion extending upstream relative to the aerodynamic surface, and the drainage devices may be part of a system including a first opening and a second opening in the aerodynamic surface, the second opening upstream from the first opening, where a drainage device is mounted over the first opening and the cantilevered fence portion of the drainage device extends upstream toward the second opening.