The C-14D assembly consist of the gyro synchronizer and base assemblies. The compass system uses the horizontal component of the earth’s magnetic field to provide a continuous magnetic heading reference for the aircraft navigation. The basic compass system consist of the directional gyro, a flux valve, and an annunciator. The C-14D gyro contains a dc static inverter in the base assembly that provides ac inputs to the gyro synchronizer. The C-14D synchronizer provides gyro stabilized heading reference for the system. The C-14D is an electrically driven element that is processed to the magnetic heading reference of the flux valve by the output of an internal slaving amplifier acting through a precession torque motor. The C-14D receives an input from the flux valve through the flux valve control transformer (FVCT) units in the C-6 indicator units. The output from the FVCT is tuned to 800Hz and applied to the slaving amplifier. The slaving amplifier output is then applied to the precession coils in the C-14D gyro and to the annunciator. The precession coils located on the outer C-14D gyro gimbal receive the error signal from the slaving amplifier. The current through theses coils creates a field which reacts with the permanent magnets located on the inner C-14D gyro gimbal. The C-14D gyro is maintained in a level position by a leveling torque motor located on the outer gimbal case. The leveling torque motor is operated by controlling voltages routed through a split ring leveling switch located on the inner gimbal. The leveling torque motor is geared to the gimbal so that the torque is applied to maintain the gyro wheel level with respect to the C-14D gyro case. The power requirements for the C-14D are 125W starting and 100W operational.