Gulfstream G650ER Elevator Cockpit Sensors PDF

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL ELEVATOR COCKPIT SENSORS — SYSTEM DESCRIPTION 1. General A. Description Multiple dedicated position sensors are connected to the control columns, control wheels and rudder pedals for each pilot station. These cockpit sensors generate electronic commands to...

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL ELEVATOR COCKPIT SENSORS — SYSTEM DESCRIPTION 1. General A. Description Multiple dedicated position sensors are connected to the control columns, control wheels and rudder pedals for each pilot station. These cockpit sensors generate electronic commands to the Flight Control Computers (FCCs) and Backup Flight Control Unit (BFCU). The commands are based on the cockpit control displacement produced either by the pilot, copilot or Autopilot (AP) system servos. See Figure 1 andFigure 2. Cockpit sensors provide data to the following: FCCs BFCU AP system FDR The FCCs and BFCU provide excitation signals to both the force sensor and the RVDT cluster. They receive voltage signals back that are proportional to the applied force. The voltage change indicates the position and force commands. When changes occur, the FCCs or BFCU command Remote Electronic Units (REUs) to energize actuators. This moves the elevators to the commanded position. NOTE: The BFCU commands are ignored by the REUs unless there has been a total failure of both FCCs. The applied force on each control column is measured by its own force sensor located below the column mount. The force sensors provided data to the FCCs. The FCCs send commands to the AP and the Modular Avionics Units (MAUs). The AP uses the force information to automatically disconnect and return manual control. The MAUs send the force information to the FDR. The force sensor is a two channel strain gauge type, with one channel connected to FCC No. 1 and the other channel connected to FCC No. 2. The FCCs provide an excitation signal to the transducer, then receive a voltage signal back that is proportional to the applied force. Control column movement is sensed by five RVDT sensors contained within the RVDT cluster on the top left of the aileron and elevator control module assembly. The RVDT sensors translate mechanical movement into electronic signals provided to the FCCs. The FCCs interpret the electronic signals from the RVDTs and sends commands to the REU elevator actuators. 2. Component Location COMPONENT ATA QTY PER A/C LOCATION Elevator force sensor 27-32-01 2 Below cockpit floor, between control column and aileron and elevator control module assembly Elevator control module RVDT 27-32-03 2 On top left of aileron and elevator control module assembly 27-32-00 Page 1 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL 3. Component Details A. Elevator Force Sensor The elevator force sensor is installed as part of a pushrod assembly that runs from the base of the column to the aileron and elevator control module. The force sensor provides information to satisfy FAA / EASA flight data recording requirements. Force sensors are installed on each column assembly to detect pilot / copilot action to override the servos. Each force sensor is a two channel strain gauge that connects as follows: One channel connects to FCC No. 1 One channel connects to FCC No. 2 NOTE: The FCCs provide an excitation signal to the sensors and receive a voltage signal back that is proportional to the applied force. Control wheel force information is used by the AP system and the FDR. The FCCs use an ARINC 429 (A429) digital data to send the information to the MAUs, where the AP modules reside. The AP uses the force information to automatically disconnect and return manual control. The MAUs use an A429 bus to send the force information to the FDR. B. Elevator Control Module RVDT The aileron and elevator control module assemblies contain a longitudinal position sensor that uses five RVDTs. The sensor canister is referred to as the RVDT cluster. The RVDT is a replaceable component but the individual transducers are not replaceable. The pilot / copilot control column position is measured by the RVDTs. Each position sensor contains a common shaft along the vertical center line that simultaneously drives all five RVDTs. The RVDTs are located radially around the main shaft of the cluster. The pilot / copilot control column drives the RVDTs using the force sensor pushrod. The force sensor pushrod extends from the wheel / column assembly to the aileron and elevator control module assembly. The RVDTs provide electrical inputs to the flight computers as follows: Two sensors provide data to FCC No. 1 Two sensors provide data to FCC No. 2 One sensor provides data to the BFCU Each FCC interfaces with one sensor on each column. The commanded position information is provided to the two FCCs and the BFCU. The two FCCs and the BFCU use control laws to determine what action to take. The FCCs send electronic signals to the REUs associated with each actuator to move the elevators to the commanded position. For each column assembly, the position sensors share a common attachment point to the wheel torque tube. If a mechanical disconnect with the column occurs, the RVDT cluster will center if the cluster main shaft is sheared. 4. Controls and Indications A. Circuit Breakers The system is protected by the following circuit breakers: NOMENCLATURE PANEL LOCATION POWER SOURCE L ELEV HA LEER A8 L ESS 28VDC L ELEV EBHA PRI REER B3 UPS 28VDC 27-32-00 Page 2 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL NOMENCLATURE PANEL LOCATION POWER SOURCE R ELEV EBHA PRI REER B4 UPS 28VDC L ELEV EBHA SEC REER B8 R MAIN 28VDC R ELEV HA REER B8 R ESS 28VDC R ELEV EBHA SEC REER C8 L MAIN 28VDC L ELEV EBHA PWR N/A EBHA PDB (tail compartment) EBHA BUS 28VDC R ELEV EBHA PWR N/A EBHA PDB (tail compartment) EBHA BUS 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. 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 Vref. Retrim Left Wing Down Amber Retrim left wing down. Retrim Right Wing Down Amber Retrim right wing down. L-R Elevator Fail Amber Both REUs 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. AP inhibit-manual trim is active. 27-32-00 Page 3 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL MESSAGE COLOR 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: MESSAGE DESCRIPTION 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 Cockpit Sensors The elevator cockpit sensors provide pilot / copilot command information to the FCCs. The FCCs use control laws to determine the appropriate action based on the pilot / copilot commands and sends digital data signals to the elevator REUs. The REUs activate hydraulic actuators to move the elevator control surfaces. The elevator uses the following two different types of actuators: EHSA - Outboard actuator EBHA - Inboard actuator The two actuators operate in an active / active configuration. During normal operation both actuators are hydraulically pressurized and actively moving the control surface. 27-32-00 Page 4 August 15/14