Attitude Heading Reference System 姿態(tài)航向基準(zhǔn)系統(tǒng)
The AHRS-3000 is a dual system that senses the aircraft attitude, heading and three-axis rate/ accelerations. The pilot's and copilot's systems are identical. Each system contains a computer (with compensation module) and a flux detector. The Attitude Heading Computer (AHC) is installed in a precisely leveled mount. The unit replaces a conventional vertical gyro, three rate gyros and three linear accelerometers. The AHC provides attitude and heading parameters to the EFIS displays, the flight guidance computers and the IAPS. The External Compensation Unit (ECU) contains offset adjustments that electrically cancel flux detector alignment error and magnetic effects caused by the airframe. The flux detector unit is mounted in the aircraft's wing tip and provides magnetic flux measurements to the AHC for computing the aircraft's heading.

Flight Guidance System 飛行引導(dǎo)系統(tǒng)
The Category II and RVSM-capable Flight Control System (FCS-3000) provides fail-passive* autopilot and flight guidance functions. The FCS has two identical computers, one autopilot control panel and three primary servos. The two Flight Guidance Computers (FGC-3000) provide independent flight guidance functions and operate together to provide three-axis autopilot, pitch trim, yaw damping and rudder boost functions. The Flight Control Panel (FCP) is located in the center of the glareshield and contains controls to engage the autopilot/yaw damper, select turbulence mode and select left or right flight guidance input into the autopilot. The primary servos are mounted near the aircraft elevator, aileron and rudder control surfaces. When engaged, the FGC applies differential drive to each servo. The servo motors then run to position the aircraft control surfaces in response to the autopilot command.

*Notes: Fail Passive System System which, in the event of a failure, causes no significant deviation of aircraft.

Radio Sensor System 無(wú)線電感應(yīng)系統(tǒng)
The RSS is a dual digital communication and navigation system. The communication portion of the system has dual VHF COMM transceivers and dual Mode-C transponders. The navigation portion of the system has dual VHF NAV receivers, dual DME transceivers, a single ADF receiver and a single radio altimeter. A single integrated control head provides on-side COMM/NAV/PULSE radio tuning and control.