The embodiments relate to reducing condensate precipitate on inner surfaces of an outer skin of an aircraft and adjacent components. The condensate precipitate is reduced by supplying dry air to an upper region of an air gap which extends between the upper region and a lower region and is disposed between the outer skin of an aircraft and an insulation arranged between a cabin wall and the outer skin of an aircraft. The dry air may be obtained with low effort and at low cost by sucking it off from the lower region of the air gap and conducted in one or more lines to the upper region of the air gap, where it is allowed to re-enter the air gap. The lines are connected to fans which create a pressure difference in the lines, which moves the dry air from the inlet opening or openings to the outlet openings.

A moisture control system includes an anode coupled to an insulation blanket that is positioned between an inner wall and an outer wall of an aircraft fuselage, a cathode coupled to an interior surface of the outer wall, and a power control unit coupled to the anode and the cathode to apply voltage across the anode and the cathode. When the voltage is applied across the anode and the cathode, moisture is drawn away from the anode and toward the cathode on the interior surface of the outer wall and guided along a drainage path provided via structural members disposed between the inner wall and the outer wall toward a drainage port.

An apparatus for securing a raceway assembly within an aircraft, which includes a clip assembly associated with the raceway assembly, which secures the raceway assembly to a seat rail. The apparatus further includes a floor panel positioned in overlying relationship to the raceway assembly and the clip assembly.

An internal cladding part for cladding a fuselage structure of an aircraft is disclosed having a first cover layer that extends in a planar manner, a second cover layer that extends in a planar manner, a core layer which is disposed between the first and the second cover layer and is connected to the first and the second cover layer and defines a receptacle cavity, and an insulation structure having a porous insulation core and an evacuated film sheath that encases the insulation core in a gas-tight manner. The insulation structure is disposed in the receptacle cavity between the first and the second cover layer.

A condensation-controlling insulation system includes an interior insulation layer for application to a cold surface. The system may further include an exterior absorption layer adapted to retain condensation during a first environmental condition and to release the condensation as a vapor during a second environmental condition.

A simple and lightweight system for discharging water that can flow out through an orifice in an insulation blanket lining the walls of a fuselage of a transport vehicle such as an aircraft. The blanket has an impermeable collection plate having at least partially the shape of a channel, container or the like for collecting and discharging condensation water under the effect of gravity through an orifice.

An insulation component to be attached to a fuselage structure of an aircraft. The insulation component extends in a planar manner, and at least one peripheral recess, running transversely to the at least one longitudinal recess, is formed in a first surface of the insulation component configured to receive a respective associated peripheral support of the fuselage structure.

A cabin module for an aircraft comprises a section which has an upward-facing surface in an installed state of the cabin module, wherein the upward-facing surface of the section comprises an integrated drainage channel. An aircraft furthermore comprises at least one such cabin module.

An apparatus for securing a raceway assembly within an aircraft, which includes a clip assembly associated with the raceway assembly, which secures the raceway assembly to a seat rail. The apparatus further includes a floor panel positioned in overlying relationship to the raceway assembly and the clip assembly.

A method and system of moisture control for a cabin of an aircraft comprising an expandable sleeve receivable over a structural member. The expandable sleeve has a material with moisture absorbing properties and elastic properties. The expandable sleeve is configured to absorb moisture flowing down the structural member. The sleeve is easily installed by stretching the sleeve to its expanded state to fit over the structural member and returning the sleeve to its contracted state to fit snugly around the structural member such that moisture flowing down the structural member does not seep into the cabin of the aircraft. Moisture is wicked and/or absorbed into the sleeve, dries, and then the process repeats when needed. No use of heat is required.