Duct assembly and method of forming a duct assembly, the method including providing a duct having an outer surface and an inner surface, the outer surface defining a periphery and the inner surface defining a first fluid passageway, covering at least a portion of the outer surface with at least a portion of a sacrificial body, depositing a metal layer over an exposed surface of the sacrificial body, and removing the sacrificial body.

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 for an aircraft for discharge of water from the aircraft interior with a line which extends in a line direction from a connector end to a discharge end. The connector end can connect to another line in the interior of the aircraft, through which further line water flows into the drain mast. The discharge end can discharge water into a surrounding area of the aircraft. The line includes a plastic, into which a conductive material is embedded, by which the line can be heated electrically, by a heating current being conducted through the conductive material. A proportion of the embedded conductive material in the line increases in the line direction per length unit from the connector end of the line towards the discharge end such that the heating power which is introduced into the line per length unit increases from the connector end towards the discharge end.

An embodiment fluid recovery structure includes a body having an interior cavity, ports integrally joined to first walls of the body and having port walls that extend away from the body, with each of the ports having a port opening that is contiguous with the interior cavity, and a drain structure integrally joined to a second wall of the body and having a drain hole that extends from the interior cavity through the drain structure.

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.

An integrated drain mast structure for use in draining fluids emanating from aircraft components, such as turbine engines and fuselages, for facilitating the detection of fluids leaking from said components. A self-supporting tube section including a plurality of generally aligned fluid passages each having a peripheral wall, at least a portion of which is common with at least a portion of another aligned adjacent fluid passage is connected to one or more of these aircraft components. An aerodynamic fairing includes a plurality of fairing fluid passages each connected to a respective fluid passage of the tube section and having respective fluid outlets. The tube section and fairing section can comprise a single integral structure.

A drain grommet with integrated fire shield. In one embodiment, the drain grommet includes a drain tube configured to extend through a drain, and to pass fluid through the drain via an opening into a hollow channel of the drain tube. The drain grommet further includes a fire shield integrally coupled with the drain tube via a standoff, wherein the standoff supports the fire shield at a vertical distance above the opening of the drain tube, and wherein the fire shield is larger than the opening of the drain tube in a horizontal plane.

An aircraft pipe coupling includes a first pipe end and a second pipe end connected to each other by a fastener. A locking collar restricts the rotational movement of the first pipe end, the second pipe end, and the fastener with respect to one another. The locking collar includes a first engagement portion and a second engagement portion, one of the engagement portions includes a resiliently deformable engagement surface. The first engagement portion is located over and engaged with the fastener, and the second engagement portion is located over and engaged with the second pipe end.

Apparatus, method for draining fluid, and method of fabricating a drainage apparatus for drainage of fluid through an exterior of an aircraft are disclosed. The apparatus includes a drain element having an aft end portion and an annular connector, wherein the annular connector is to be disposed within a drain port in an exterior panel of the aircraft. The drain element includes a forward end portion with a contoured protrusion disposed over the annular connector, and a drain opening at the aft end of the contoured protrusion. The contoured protrusion enables fluid to flow from the drain port through the annular connector and out the drain opening. An airflow across the contoured protrusion creates a reduced pressure region external to the drain opening relative to the pressure at the annular connector and drain port, so as to induce fluid flow through the annular connector in the drain port and out the drain opening.

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.