Abstract: An aircraft electrical system includes a controller system having a self-testing system configured to test an operability of a transient voltage suppression device. A single line communication bus is connected to a communications output of the controller. A first lightning protection device including the transient voltage suppression device is configured to protect the controller from transient voltages. An enable/disable circuit comprising a normally closed switch connects a low side of the lightning protection device to a neutral.

Abstract: A sensor interface includes a sensor circuit, a drive circuit connected to the sensor circuit with active and inactive states, and a back-bias circuit. The back-bias circuit is connected between the drive circuit and the sensor circuit. The back-bias circuit is arranged to allow current to flow from the drive circuit to the sensor circuit when the drive circuit is in the active state. The back-bias circuit is also arranged to limit current flow from the drive circuit to the sensor circuit when the drive circuit is in the inactive state. Sensor arrangements and open circuit detection methods are also described.

Abstract: An overvoltage protection arrangement includes a signal lead, a switch, and a comparator. The signal lead has a device segment and a bus segment. The switch is connected in series between the device segment and the bus segment. The comparator is operably connected to the switch to open the switch in response to sustained application of overvoltage to the bus segment of the signal lead. Aircraft electrical systems and methods of controlling voltage applied to electrical devices in electrical systems are also described.

Abstract: A sensor interface includes a sensor circuit, a drive circuit connected to the sensor circuit with active and inactive states, and a back-bias circuit. The back-bias circuit is connected between the drive circuit and the sensor circuit. The back-bias circuit is arranged to allow current to flow from the drive circuit to the sensor circuit when the drive circuit is in the active state. The back-bias circuit is also arranged to limit current flow from the drive circuit to the sensor circuit when the drive circuit is in the inactive state. Sensor arrangements and open circuit detection methods are also described.

Abstract: An aircraft electrical system includes a controller system having a self-testing system configured to test an operability of a transient voltage suppression device. A single line communication bus is connected to a communications output of the controller. A first lightning protection device including the transient voltage suppression device is configured to protect the controller from transient voltages. An enable/disable circuit comprising a normally closed switch connects a low side of the lightning protection device to a neutral.

Abstract: An overvoltage protection arrangement includes a signal lead, a switch, and a comparator. The signal lead has a device segment and a bus segment. The switch is connected in series between the device segment and the bus segment. The comparator is operably connected to the switch to open the switch in response to sustained application of overvoltage to the bus segment of the signal lead. Aircraft electrical systems and methods of controlling voltage applied to electrical devices in electrical systems are also described.