Abstract: A panel for use in the construction of a galley of an aircraft is disclosed. The panel comprises a frame, at least one insulation panel, and a cover panel. The frame comprises first and second opposing faces and one or more edge faces, and each edge face extends between the first and second faces. The cover panel has first and second opposing faces and each insulation panel has first and second opposing faces. One or more of the edge faces of the frame define a housing aperture and the frame is fixed to the cover panel with the first face of the frame adjacent to the second face of the cover panel.

Abstract: A panel for use in the construction of a galley of an aircraft is disclosed. The panel comprises a décor panel and at least one insulation panel. The décor panel has first and second opposing faces, and a housing aperture extends through the décor panel between the first and second faces. The housing aperture is of substantially the same configuration as the insulation panel or the insulation panels collectively when arranged side by side or when stacked. The housing aperture is configured to receive the at least one insulation panel, and the or each insulation panel is located in the housing aperture.

Abstract: A trolley retainer for an aircraft galley, the aircraft galley comprising an aircraft galley structure and a trolley, the trolley retainer comprising: a retainer connector configured to connect the trolley retainer to the aircraft galley structure; a front portion configured to extend across a front of the trolley to retain the trolley in the aircraft galley when the trolley retainer is in a retaining position; and a side portion configured to extend from the retainer connector to the front portion across a side of the trolley when the trolley retainer is in the retaining position.

Abstract: A latching mechanism for an aircraft galley, the aircraft galley comprising a door and a frame, the latching mechanism comprising: a latch bolt movable between a retracted position and an extended position; and an actuator configured to maintain the latch bolt in the retracted position, the actuator configured to move the latch bolt to the extended position on closing the door in the frame, wherein the latch bolt is receivable by a latch striker to latch the aircraft galley door when the door is closed and the latch bolt is in the extended position.

Abstract: A system for cooling an aircraft galley trolley. The system includes a trolley cooling compartment for stowing an aircraft galley trolley; and a heat exchanger to provide cold air to the trolley cooling compartment. The trolley cooling compartment defines an inlet proximal to the base of the trolley cooling compartment for receiving the cold air. The trolley cooling compartment cools the aircraft galley trolley through the transfer of heat to the cold air. The transfer of heat to the cold air heats the cold air to produce warmer air.

Abstract: There is provided herein an aircraft galley insert including a beverage making apparatus configured to dispense beverage singularly and independently, wherein the aircraft galley insert is sized to fit within a standard envelope size, so as to be interchangeable with alternative galley inserts.

Abstract: A crank assembly for extracting an inner galley trolley from a galley bay is provided. The crank assembly comprises an output shaft configured to rotate about an axis of rotation A for actuating a trolley extraction mechanism to extract an inner galley trolley from a galley trolley bay; a crank arm configured to rotate about the axis of rotation A; a handle connected to the crank arm for rotating the crank arm about the axis of rotation A; and a clutch mechanism. The clutch mechanism is operable to selectively couple the crank arm to the output shaft to selectively transfer rotational movement of the crank arm into rotational movement of the output shaft.

Abstract: A chiller assembly for a galley having one or more rectangular galley compartments defined by a back wall, a floor, a top wall and two opposing side walls, the chiller assembly comprising a chiller system comprising a heat exchanger configured to be located in use in a space adjacent a side wall of a compartment external to the compartment, and a blower duct connected to receive chilled air from the heat exchanger, the blower duct arranged to extend adjacent the top wall or the floor of the compartment, the blower duct having vents to blow chilled air into the compartment via the top wall or the floor, the chiller system further comprising a return duct arranged adjacent the other of the floor or the top wall of the compartment to suck air from the compartment and return it to the heat exchanger.

Abstract: A retainer suitable for use on an aircraft is disclosed. The retainer comprises a first retainer part and a second retainer part. The first retainer part comprises a catch and a damper; in which the catch comprises one or more magnetic elements. The damper comprises a damping material, the damping material damps shock impulses; and the catch is supported on the damper.

Abstract: An aircraft wall assembly comprises a panel comprising a ballistic protection layer configured to deform to absorb energy during a projectile impact; and a barrier, wherein the ballistic protection layer comprises a constrained portion, wherein deformation of the ballistic protection layer is constrained at the constrained portion such that the energy absorbed by the constrained portion during the projectile impact is reduced; wherein the barrier is configured to deflect projectile material that passes through the constrained portion of the panel during the projectile impact.

Abstract: A retainer suitable for use on an aircraft is disclosed. The retainer comprises a first retainer part and a second retainer part. The first retainer part comprises a catch and a damper; in which the catch comprises one or more magnetic elements. The damper comprises a damping material, the damping material damps shock impulses; and the catch is supported on the damper.

Abstract: A bump strip includes first and second end caps and an intermediate part that, together, define a length of the bump strip. The end caps having an end part and a connecting part, and whereby one or more fastening holes is provided through the end cap connecting parts and the intermediate part such that a single fastener passing through the fastening hole of an end cap and the intermediate part secures the bump strip to a surface to be protected.

Abstract: A crank assembly for extracting an inner galley trolley from a galley bay is provided. The crank assembly comprises an output shaft configured to rotate about an axis of rotation A for actuating a trolley extraction mechanism to extract an inner galley trolley from a galley trolley bay; a crank arm configured to rotate about the axis of rotation A; a handle connected to the crank arm for rotating the crank arm about the axis of rotation A; and a clutch mechanism. The clutch mechanism is operable to selectively couple the crank arm to the output shaft to selectively transfer rotational movement of the crank arm into rotational movement of the output shaft.

Abstract: A floor module for a power generation system may comprise: a housing including a flexible top plate; a plurality of generator assemblies disposed within the housing, each generator in the plurality of generator assemblies comprising: a moveable portion disposed adjacent to the flexible top plate, the moveable portion including a shaft extending away from the flexible top late; and a piezoelectric transducer aligned with the shaft, the piezoelectric transducer configured to compress in response to the moveable portion translating toward the piezoelectric transducer from a force on the flexible top plate.