Abstract: A locking assembly of a lavatory door in an aircraft, comprising: a locking mechanism; and an occupancy indicator. The occupancy indicator is configured with a display that enables viewing of a status of the lavatory of availability or is occupancy. The position of the locking mechanism and occupancy indicator has been changed from a higher location on the lavatory door that approximates a line-of-sight from a standing position at the lavatory door to a lower location that approximates the line-of-sight from a seated position at the lavatory door. The display of the occupancy indicator is configured with a plurality of display angles to display the status comprising at least a first display angle to allow viewing from the line-of-sight in the standing position and at a second display angle to allow viewing from the line-of-sight in a seated lower position at the lavatory door.

Abstract: A lavatory door including an ashtray is disclosed herein. The lavatory door includes a door panel having a first side and an opposing second side and the ashtray disposed within the door panel. The ashtray includes a first outer panel disposed along the first side of the door panel and configured to move away from the door panel, a second outer panel, opposite the first outer panel, disposed along the second side of the door panel and configured to move away from the door panel, and a bottom surface extending from the first outer panel to the second outer panel.

Abstract: A lavatory door including an ashtray is disclosed herein. The lavatory door includes a door panel having a first side and an opposing second side and the ashtray disposed within the door panel. The ashtray includes a first outer panel disposed along the first side of the door panel and configured to move away from the door panel, a second outer panel, opposite the first outer panel, disposed along the second side of the door panel and configured to move away from the door panel, and a bottom surface extending from the first outer panel to the second outer panel.

Abstract: A waste system is disclosed. In some embodiments, the waste system includes a vacuum cell, a flexible waste container, and a vacuum source. The flexible waste container may have at least one flexible membrane at an interface between the flexible waste container and the vacuum cell. The vacuum source may be configured to suction air out of the vacuum cell to generate a negative pressure in the vacuum cell. The vacuum source discharge is generally odorless as it is separated from the waste. This odorless discharge can enter occupied aircraft compartments. The negative pressure in the vacuum cell acts on the flexible waste container to generate a (second) negative pressure in the flexible waste container. The negative pressure in the flexible waste container acts on an interface between a toilet and the flexible waste container to pull waste from the toilet into the flexible waste container.

Abstract: A waste system is disclosed. In some embodiments, the waste system includes a vacuum cell, a flexible waste container, and a vacuum source. The flexible waste container may have at least one flexible membrane at an interface between the flexible waste container and the vacuum cell. The vacuum source may be configured to suction air out of the vacuum cell to generate a negative pressure in the vacuum cell. The vacuum source discharge is generally odorless as it is separated from the waste. This odorless discharge can enter occupied aircraft compartments. The negative pressure in the vacuum cell acts on the flexible waste container to generate a (second) negative pressure in the flexible waste container. The negative pressure in the flexible waste container acts on an interface between a toilet and the flexible waste container to pull waste from the toilet into the flexible waste container.

Abstract: A waste system includes a vacuum cell, a flexible waste container, and a vacuum source. The flexible waste container may have at least one flexible membrane at an interface between the flexible waste container and the vacuum cell. The vacuum source may be configured to suction air out of the vacuum cell to generate a negative pressure in the vacuum cell. The vacuum source discharge is generally odorless as it is separated from the waste. This odorless discharge can enter occupied aircraft compartments. The negative pressure in the vacuum cell acts on the flexible waste container to generate a (second) negative pressure in the flexible waste container. The negative pressure in the flexible waste container acts on an interface between a toilet and the flexible waste container to pull waste from the toilet into the flexible waste container.

Abstract: A system for waste system pressure management is disclosed. In one or more embodiments, the system includes an electronically controlled valve and a controller communicatively coupled to the electronically controlled valve. The electronically controlled valve is coupled to a suction path of an aircraft waste system. The controller is configured to determine a pressure differential between an aircraft cabin and a vacuum source for the suction path. The controller is further configured to generate one or more signals to actuate the electronically controlled valve from a first position to a second position to regulate a pressure in the suction path when the pressure differential between the aircraft cabin and the vacuum source exceeds a threshold pressure differential. In embodiments, the electronically controlled valve is configured to allow more airflow through the electronically controlled valve in the second position than in the first position.

Abstract: A waste system is disclosed. In some embodiments, the waste system includes a vacuum cell, a flexible waste container, and a vacuum source. The flexible waste container may have at least one flexible membrane at an interface between the flexible waste container and the vacuum cell. The vacuum source may be configured to suction air out of the vacuum cell to generate a negative pressure in the vacuum cell. The vacuum source discharge is generally odorless as it is separated from the waste. This odorless discharge can enter occupied aircraft compartments. The negative pressure in the vacuum cell acts on the flexible waste container to generate a (second) negative pressure in the flexible waste container. The negative pressure in the flexible waste container acts on an interface between a toilet and the flexible waste container to pull waste from the toilet into the flexible waste container.

Abstract: A system for waste system pressure management is disclosed. In one or more embodiments, the system includes an electronically controlled valve and a controller communicatively coupled to the electronically controlled valve. The electronically controlled valve is coupled to a suction path of an aircraft waste system. The controller is configured to determine a pressure differential between an aircraft cabin and a vacuum source for the suction path. The controller is further configured to generate one or more signals to actuate the electronically controlled valve from a first position to a second position to regulate a pressure in the suction path when the pressure differential between the aircraft cabin and the vacuum source exceeds a threshold pressure differential. In embodiments, the electronically controlled valve is configured to allow more airflow through the electronically controlled valve in the second position than in the first position.

Abstract: A flexible hinge assembly for aircraft interior components and the like, including: a first structural component, wherein the first structural component includes a core material and one or more skin layers coupled to the core material; a second structural component, wherein the second structural component includes a core material and one or more skin layers coupled to the core material; wherein the one or more skin layers of the first structural component and the one or more skin layers of the second structural component are one or more of coupled together and integrally formed; and a flexure disposed between the first structural component and the second structural component, wherein the flexure is formed by the coupled together and/or integrally formed skin layers.

Abstract: A flexible hinge assembly for aircraft interior components and the like, including: a first structural component, wherein the first structural component includes a core material and one or more skin layers coupled to the core material; a second structural component, wherein the second structural component includes a core material and one or more skin layers coupled to the core material; wherein the one or more skin layers of the first structural component and the one or more skin layers of the second structural component are one or more of coupled together and integrally formed; and a flexure disposed between the first structural component and the second structural component, wherein the flexure is formed by the coupled together and/or integrally formed skin layers.

Abstract: An aircraft drain/fill fitting includes a housing adapted for being fitted into an opening between an aircraft interior and an aircraft exterior. The housing has an interior housing segment fluidly coaxially communicating with an exterior housing segment to define a liquid flow path therethrough, and a heater for applying heat to the interior housing segment. A hollow insert element is positioned in the interior housing segment in heat transfer contact with an inner wall of the interior housing segment. An elongate heat transfer probe is positioned in heat transfer contact with the hollow insert element and extends into the exterior housing segment to reduce the incidence of freezing of liquid in the exterior housing segment.

Abstract: An aircraft drain/fill fitting includes a housing adapted for being fitted into an opening between an aircraft interior and an aircraft exterior. The housing has an interior housing segment fluidly coaxially communicating with an exterior housing segment to define a liquid flow path therethrough, and a heater for applying heat to the interior housing segment. A hollow insert element is positioned in the interior housing segment in heat transfer contact with an inner wall of the interior housing segment. An elongate heat transfer probe is positioned in heat transfer contact with the hollow insert element and extends into the exterior housing segment to reduce the incidence of freezing of liquid in the exterior housing segment.