Abstract: An electrical bonding test device, including a test system circuit configured to generate a current pulse for ground bonding testing of subject units, a first test system connector configured to provide an electrical connection between a first unit connector shell of a first unit of the subject units and the test system circuit and to pass the current pulse to the first unit connector shell during the ground bonding testing, and a second test system connector configured to provide an electrical connection between a second unit connector shell of a second unit of the subject units and a first node of the test system circuit. The test system circuit is further configured to provide an indication indicating whether a bonding path through the subject units is a conductive path having a resistance below a resistance threshold.

Abstract: An embodiment device including a current pulse source, a first connector having a first connector shell connected to the current pulse source, a second connector having a second connector shell, an amplifier electrically connected to the first connector shell and the second connector shell, and a comparator connected to an output of the amplifier.

Abstract: A test system for testing a sensor system includes a high-impedance resistor for forming a voltage divider with any corrosion or foreign substance that might be present between a signal conductor and a ground conductor. While a voltage is applied across the voltage divider, the voltage can be measured across the high-impedance resistor for determining whether an undesirable amount of conductance exists between the signal wire and ground. The test system also includes switching means for switching between any number of signal wires of a system undergoing testing.

Abstract: A test system for testing a sensor system includes a high-impedance resistor for forming a voltage divider with any corrosion or foreign substance that might be present between a signal conductor and a ground conductor. While a voltage is applied across the voltage divider, the voltage can be measured across the high-impedance resistor for determining whether an undesirable amount of conductance exists between the signal wire and ground. The test system also includes switching means for switching between any number of signal wires of a system undergoing testing.

Abstract: A transducer test system for testing accelerometers or velocity transducers includes a signal conditioner and a shaker that can be used in a field environment, for example by an avionics technician at an aircraft. A test transducer and a reference transducer, which is a known-good version of the test transducer, are mounted onto the shaker and electrically connected to the signal conditioner. The technician shakes the two transducers simultaneously by manually shaking the shaker. The signal conditioner receives and compares the signals output from the test and reference transducer in order to determine the operating condition of the test transducer.

Abstract: A transducer test system for testing accelerometers or velocity transducers includes a signal conditioner and a shaker that can be used in a field environment, for example by an avionics technician at an aircraft. A test transducer and a reference transducer, which is a known-good version of the test transducer, are mounted onto the shaker and electrically connected to the signal conditioner. The technician shakes the two transducers simultaneously by manually shaking the shaker. The signal conditioner receives and compares the signals output from the test and reference transducer in order to determine the operating condition of the test transducer.

Abstract: An ice management system is configured for an aircraft having at least one rotor, each rotor having a plurality of blades. The system has an electrical power supply adapted to be carried by the aircraft remote from the rotor, and at least one heater is carried by the rotor for heating at least a portion of the rotor. A solid-state control relay is carried by the rotor and conductively coupled between the power supply and each heater for selectively controlling the flow of electrical power from the power supply to each heater. In addition, the system may incorporate a solid-state feed relay carried by the aircraft remote from the rotor and conductively coupled between the power supply and the control relay for selectively controlling the flow of electrical power to the control relay.