Gulfstream G650ER Elevator Autopilot System PDF

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL ELEVATOR AUTOPILOT SYSTEM — SYSTEM DESCRIPTION 1. General A. Description The Autopilot (AP) system consists of two servo actuators. One AP servo is attached to each of the aileron and elevator control modules. One motor is attached to each column / wheel a...

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL ELEVATOR AUTOPILOT SYSTEM — SYSTEM DESCRIPTION 1. General A. Description The Autopilot (AP) system consists of two servo actuators. One AP servo is attached to each of the aileron and elevator control modules. One motor is attached to each column / wheel assembly. A mechanical interconnect allows either motor to drive the movement of both controls. This arrangement allows continuous operation if one side becomes jammed. See Figure 1 and Figure 2. 2. Component Location COMPONENT ATA QTY PER A/C LOCATION Elevator autopilot servo 27-36-01 2 Left side of aileron and elevator control module assembly 3. Component Details A. Elevator Autopilot Servo The AP interface to the flight control system is through AP servo actuators that connect to the cockpit controls. The AP inputs are supplied through an electric AP servo motor that connects to the flight control mechanical input sector. The AP servo motor is mounted in each aileron and elevator control module. The servos move the columns and wheels. Either pilot may override the AP system with sufficient wheel force to override the servo and disconnect the AP. The pilot servo motor is controlled by Automatic Flight Control System (AFCS) No. 1 located in Modular Avionics Unit (MAU) No. 1. The copilot servo motor is controlled by AFCS No. 2 in MAU No. 2. The servo motors are used to directly move the control wheels. There is no direct signal from the AFCS system to the Flight Control Computer (FCC) for aircraft control. Instead, the motors control the aircraft by moving the controls in the same manner as the flightcrew in manual control. This method has the benefit of providing the flightcrew visual feedback of what the AFCS system is doing to control the aircraft. 4. Controls and Indications A. Circuit Breakers The system is protected by the following circuit breakers: NOMENCLATURE PANEL LOCATION POWER SOURCE AP PITCH SERVO 1 Pilot D2 L ESS 28VDC AP PITCH SERVO 2 Copilot D2 R ESS 28VDC B. CAS Messages The CAS messages for the system are shown in the following table: MESSAGE COLOR MESSAGE DESCRIPTION Stall Reference Speed Increase Blue Stall protection speed increased because of wing anti-ice fail and possible ice accretion on wings. Verify increased landing reference speed and increased landing distance. 27-36-00 Page 1 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL MESSAGE COLOR MESSAGE DESCRIPTION AP Trim Fail Blue AP trim has failed. AP Inhibit-Stall Blue AP inhibit-stall is active. Pitch Trim Nose Down Limit Blue Pitch trim at nose down limit. Adjust pitch trim as necessary. Pitch Trim Nose Up Limit Blue Pitch trim at nose up limit. Adjust pitch trim as necessary. Stick Shaker 1-2 Fail Blue Stick shaker 1 and 2 have failed. AP Inhibit-Manual Trim Active Blue Go Around Pitch Blue Go around pitch is active. Stall Protection Active Amber Angle of Attack (AOA) limiting mode is active. Adjust flight condition as necessary. Stall Protection Unavailable Amber AOA data unavailable or flight control mode other than normal. Continue flight within flight envelope limitations, minimum airspeed velocity reference. Retrim Left Wing Down Amber Retrim left wing down. Retrim Right Wing Down Amber Retrim right wing down. L-R Elevator Fail Amber Both remote electronics units failed or loss of elevator command to both elevators. Continue flight within flight envelope limitations. Attempt FLT CTRL RESET. Elevator Single Actuator Amber Single elevator actuator failed. Notify maintenance for corrective action. Attempt FLT CTRL RESET. Vertical Coupling Data Invalid Amber Pitch Authority Limit Amber Pitch axis flight control surfaces approaching maximum displacement. Adjust flight condition as necessary. Amber Pilot and copilot pitch control column positions are different. Continue flight within flight envelope limitations. Aircraft pitch response with respect to control column input may be reduced. Pitch Control Miscompare NOTE: AP inhibit-manual trim is active. Vertical coupling data is invalid. The FCC status information required by the flightcrew is shown on the main displays as CAS messages and synoptic page data. 5. Operation A. Elevator Autopilot System The pilot and copilot activate the AP system by selecting the AP switch on the flight guidance panel. When activated, the AP function directly controls the pilot and copilot control wheel and column. Servo motors drive the wheel and column to the desired position for autoflight. 27-36-00 Page 2 August 15/14