Electrically activated latch for aircraft stowage bins

An overhead stowage bin module electronic latching system for an aircraft having an aircraft electrical system, comprising:

• an overhead stowage bin module including a stationary support structure and a movable stowage bin portion cooperatively connected to the stationary support structure for movement in relation to said stationary support structure, said movable stowage bin portion being movable downward and upward with respect to said stationary support structure between an open position and a closed position, and said movable stowage bin portion forming an enclosure with said stationary support structure for stowage of items in said closed position;
• a stowage bin latch mechanism connected to said overhead stowage bin module and configured to latch said movable stowage bin portion in the closed position and to unlatch said movable stowage bin portion to be released to said open position;
• a stowage bin activation switch connected to said stowage bin latch mechanism and configured operate the stowage bin latch mechanism;
• and
• electrical wiring connected to the aircraft electrical system and said stowage bin activation switch and configured to receive electrical power from the aircraft electrical system, said electrical wiring including a first electrical wiring circuit and a second electrical wiring circuit separate from the first electrical wiring circuit, said first electrical wiring circuit being configured to transmit power and including a closed position contact point, said second electrical wiring circuit being configured to transmit power and including an open position contact point, and said electrical wiring being configured to receive electrical power from an aircraft electrical system, wherein said stowage bin activation switch is configured to receive the electrical power via the electrical wiring from the aircraft electrical system for operation of the stowage bin latch mechanism, wherein said electrical wiring is configured to transmit a fasten seat belt status signal to said stowage bin activation switch, and wherein said electrical power and said fasten seat belt status signal are conducted through said electrical wiring through at least one of the closed position contact point and the open position contact point to the stowage bin activation switch, and wherein said stowage bin activation switch comprises a touch pad switch including a lens and a lighting system adjacent to the lens, the lighting system being configured to provide cabin emergency illumination during a loss of aircraft power, or in response to a command to provide emergency illumination.