An aircraft proximity sensor system includes a control module in communication with a transceiver module and an aircraft proximity sensor module, the control module operable to disable transmission by the transceiver module in response to the aircraft proximity sensor module.

Method and apparatus for detecting an operational state of an aircraft comprising conducting passive measurements including measuring an electromagnetic frequency at a location. Measuring a magnetic flux density at the location. Determining that the aircraft is in a powered state when criteria are met, wherein the criteria include the measured electromagnetic frequency is between 370 Hz and 1 kHz and the measured magnetic flux density is between 9 nT and 9200 nT.

A system is described that includes a controllable component of an engine configured to regulate fuel flow to the engine, a digital control unit configured to control the engine by at least communicating with the controllable component of the engine, and a protection component configured to disable communication between the digital control unit and the controllable component of the engine. The system further includes an analog control unit configured to control the engine by at least communicating with the controllable component of the engine in response to the protection component disabling communication between the digital control unit and the controllable component of the engine.

A system is described that includes a controllable component of an engine configured to regulate fuel flow to the engine, a digital control unit configured to control the engine by at least communicating with the controllable component of the engine, and a protection component configured to disable communication between the digital control unit and the controllable component of the engine. The system further includes an analog control unit configured to control the engine by at least communicating with the controllable component of the engine in response to the protection component disabling communication between the digital control unit and the controllable component of the engine.

A computer-implemented method for charging an electronic device on an aircraft is provided. The method includes monitoring a charging station on the aircraft by a charging control module, determining whether the electronic device has been connected to the charging station and receiving, via the charging control module, an indication that operation of the electronic device should be restricted to airplane mode. The method also includes transmitting a command by the charging control module through charging station to the electronic device to instruct the electronic device to operate in airplane mode and determining whether the electronic device is operating in airplane mode. Based on a determination that the electronic device is operating in airplane mode, the method includes activating the charging station. Based on a determination that the electronic device is not operating in airplane mode, the method includes disabling the charging station.

A computer-implemented method for charging an electronic device on an aircraft is provided. The method includes monitoring a charging station on the aircraft by a charging control module, determining whether the electronic device has been connected to the charging station and receiving, via the charging control module, an indication that operation of the electronic device should be restricted to airplane mode. The method also includes transmitting a command by the charging control module through charging station to the electronic device to instruct the electronic device to operate in airplane mode and determining whether the electronic device is operating in airplane mode. Based on a determination that the electronic device is operating in airplane mode, the method includes activating the charging station. Based on a determination that the electronic device is not operating in airplane mode, the method includes disabling the charging station.