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.

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.

A drain configured to evacuate leaks of fluid, such as fuel, from a leak collecting system of an aircraft, the drain comprising a rigid tube secured to a plate, the plate being configured to be attached to an external wall of the aircraft, a flexible pipe configured to join the collecting system to the rigid tube, one end of the flexible pipe being received within the rigid tube. The rigid tube comprises a channel, the channel being configured to allow separation of the rigid tube from the plate at the location of the channel.

A drainage valve comprising a through hole, a seat around the through hole, a shutter comprising an end face and movable in a longitudinal direction between a first position in which the end face of the shutter is away from the seat and a second position in which the end face of the shutter is pressed against the seat and blocks the through hole, and an elastic element configured to keep the shutter in the first position. The shutter has a recess, emerging at its end face, configured to introduce therein a part of a tool in order to temporarily secure the part of the tool and the shutter in order to displace it in two directions longitudinally.

There is provided a drainage system of an aircraft which discharges moisture having entered inside horizontal tails, which are structures of an airframe of an aircraft, toward the rear end of a fuselage, the drainage system including: a drainage channel which includes an introduction end and a discharge end, and by a capillary action delivers moisture introduced from the introduction end toward the discharge end; and a heater which heats and dries the moisture delivered through the drainage channel. The drainage channel of the present invention is preferably composed of a paper drainage material. It is also preferable that the introduction end of the drainage channel is provided in a lowermost region in the vertical direction within an area in which moisture can accumulate inside the horizontal tails while the aircraft is parked.

A drain for expelling fluids from an interior of an aircraft to an exterior of the aircraft, the drain including a drain tube disposed at the interior of the aircraft having a first end disposed in fluid communication with an aircraft equipment to be drained and an opposite second end, wherein the drain tube terminates at the second end at a location within the interior of the aircraft, a seal which extends between the second end of the drain tube and an outer skin of the aircraft, delimiting a drainage cavity, and a drainage pathway extending from the cavity through the outer skin to the exterior of the aircraft.

In some examples, a drain pan comprises a composite material forming a reservoir and a drain. The composite material comprises a polymeric resin and a reinforcing fiber. The reservoir is to catch a liquid from an engine and to support a step load. The drain is to drain the liquid from the reservoir. In some examples, a method comprises attaching a drain pan to an aircraft proximate an engine. The drain pan comprises a composite material forming a reservoir and a drain. The method further comprises catching a liquid from the engine in the reservoir of the drain pan and draining the liquid from the reservoir through the drain. In addition, the method comprises supporting a step load on the reservoir of the drain pan.

To provide a fuel pipe of an aircraft that makes it possible to maintain temperature of fuel in the fuel pipe at appropriate temperature while giving consideration to reliability that is constantly required for the aircraft. A fuel pipe provided in an airframe of the aircraft includes: an inner pipe defining a flow path through which fuel flows; and an outer pipe surrounding an outer periphery of the inner pipe. A gap is provided between the outer periphery of the inner pipe and an inner periphery of the outer pipe. The inner pipe is made of a rubber material, and the outer pipe is made of a metal material.

A drain mast that releases fluid into an airstream includes two fairing bodies, with each fairing body having an outer wall, an inner wall opposite of the outer wall, a drain cavity extending through the inner wall, a mounting portion, and a drain portion opposite of the mounting portion. The two fairing bodies are joined together at their inner walls such that the two mounting portions are adjacent, such that the drain cavities form a mast cavity, and such that the drain portions are adjacent to each other and together form a foot. The foot includes a drain outlet connected to the mast cavity, and a post-exit stage positioned downstream of the drain outlet with the post-exit stage being located closer to the mounting portions than the drain outlet.

According to an embodiment, an aircraft comprises a fuselage including composite skin; an enclosure located inside the fuselage; a rechargeable battery disposed inside the enclosure; and a ventilation conduit extending from the enclosure to an opening in the composite skin, the ventilation conduit including: a first portion having a first end coupled to the enclosure and a second end spaced from the composite skin, and a second portion extending between the composite skin and the second end of the first portion, the second portion comprising an electrically non-conductive material.