A waste compartment system for an aircraft can include a motor operated door and a proximity sensor configured to sense an object near the door or approaching the door. The system can include a control module operatively connected to the proximity sensor and configured to open the door in response to the proximity sensor sensing an object near the door. The control module can be configured to close the door after a preset time after the proximity sensor senses an object.

A method, apparatus, and system for monitoring a vehicle. Optical signals are sent into a fiber optic mesh covering a region of the vehicle. Response optical signals occurring in response to optical signals sent into the fiber optic mesh are detected. Sensor data is generated from the response optical signals detected. A determination is made as to whether a group of nonconformances is present in the vehicle using the sensor data. A group of actions is performed when the group of nonconformances is present.

An aircraft including at least one turbine engine and a monitoring device associated with the turbine engine, the turbine engine being linked firstly to circuits including fluid circuits and electric circuits, and secondly to sensors for monitoring the turbine engine and the circuits, the sensors including at least one fire sensor and sensors for monitoring the fluid circuits, sensors for monitoring the electric circuits and sensors for monitoring the operation of the turbine engine, the monitoring device being linked to the sensors and including a central processing unit to generate a signal indicating the occurrence of a fire on the turbine engine only if a fire sensor and a sensor for monitoring a fluid circuit or an electric circuit or the operation of the turbine engine transmit a signal indicating an anomaly.

Disclosed is an optical fiber overheat detection testing apparatus. The apparatus includes an optical fiber having a first end and a second end, the optical fiber having a predetermined length associated with a predetermined attenuation based on an overheat detection instrument loop. The apparatus includes a first fiber Bragg grating disposed on the optical fiber having a first wavelength spectrum based on a first temperature detection apparatus. The apparatus includes a second fiber Bragg grating disposed on the optical fiber having a second wavelength spectrum based on at least one of a plurality of overheat detection apparatuses.

The present invention is directed to multifunctional surfacing films each comprising: (a) a single layer of curable polymer composition having opposing first and second surfaces: (b) a peelable porous sheet disposed at or beneath the second surface; and (d) at least one porous sheet of functional material disposed within the single layer of curable polymer composition and positioned between the first surface and the peelable porous sheet, and methods of making and using such multifunctional surfacing films.

A transport element clamp system comprising a lower portion, an upper portion, and a channel system. The lower portion has a first number of cutouts and the upper portion has a second number of cutouts. The lower portion is configured to bridge a gap between two support structures in an aircraft. The upper portion is configured to interlock with the lower portion. The channel system is formed by the first number of cutouts and the second number of cutouts. The channel system is configured to receive a number of transport elements when the upper portion and the lower portion are coupled to each other. The transport element clamp system electrically isolates the number of transport elements from the two support structures.

An aircraft including a fuselage defining a cabin and baggage bay, engine compartments for receiving engines, an auxiliary power unit compartment for receiving an auxiliary power unit, and a fire suppression system including first and second reservoirs containing a fire suppressant. The reservoirs are each connected to all of the engine compartments for distribution of the fire suppressant thereto. The first reservoir is connected to only one of the auxiliary power unit compartment and baggage bay, and the second reservoir is connected to only the other of the auxiliary power unit compartment and baggage bay. A fire suppression system for an aircraft and a method of connecting a fire suppression system of an aircraft are also discussed.

A gas turbine engine includes an engine core having a compressor, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. A core nacelle is disposed radially outward of the engine core. A cavity is disposed between an inner surface of the core nacelle and an outer surface of the engine core. The cavity includes a vent disposed at an aft end. The vent includes at least one flap configured to be maintained in an unrestricted position and in a restricted position. An actuator is configured to control the position of the at least one flap.

A system configured to monitor temperature in a plurality of zones of an aircraft includes an optical fiber with first and second ends, first and second connectors, and a first interrogator. The optical fiber includes a plurality of fiber Bragg gratings disposed in the optical fiber. The first connector is disposed on the first end of the optical fiber and the second connector is disposed on the second end of the optical fiber. The first interrogator is connected to the first connector and includes an optical switch. The optical switch is in optical communication with the first connector of the optical fiber and is configured to selectively block transmission of the optical signal to the optical fiber.

A multi-layer liner material for use as a thermal and acoustical insulator which is lightweight, breathable, hydrophobic, oleophobic and fire-resistant. A central insulation core layer is contacted on a first surface by a first highly breathable layer and on a second surface by a second highly breathable layer, such that these three layers are resistant to water or oil penetrating the insulation core layer causing the liner to gain weight. The first and second highly breathable layers are preferably made from inherently flame resistant fibers and treated with a fluorocarbon surface treatment for water repellency, UV resistance and mold/mildew resistance. The first highly breathable layer is adjacent a facing layer while the second highly breathable layer is adjacent a backing layer. At least one surface of one of the first or second highly breathable layers, or facing or backing layers may include a carbon printing pattern to provide ESD protection.