Gulfstream G650ER Aileron Cockpit Sensors PDF

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

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL AILERON COCKPIT SENSORS — SYSTEM DESCRIPTION 1. General A. Description Multiple dedicated position sensors are connected to the control wheels, control columns and rudder pedals for each pilot station. Cockpit sensors generate electronic signals and sends the data to the Flight Control Computers (FCCs) and Backup Flight Control Unit (BFCU). Commands are based on cockpit control displacement produced either by the pilot, copilot or Autopilot (AP) system servos. See Figure 1 and Figure 2. Cockpit sensors provide data to the following: FCCs BFCU AP system FDR The FCCs and BFCU provide excitation signals to RVDT and force sensors and receives voltage signals back that are proportional to the applied force and position. Voltage change indicates position and force commands. When changes occur, the FCCs or BFCU command Remote Electronic Units (REUs) to energize actuators to move flight control surfaces to the commanded position. NOTE: The BFCU commands are ignored by the REUs unless there has been a total failure of both FCCs. Applied force on each control wheel is measured by its own force transducer located below the column mount. Transducers provided data to the FCCs. The FCCs then send commands to the AP and Modular Avionics Units (MAUs). The AP uses force data to automatically disconnect and return manual control. The MAUs send force data to the FDR. The force sensor is a two channel strain gauge type. One channel connects to FCC No. 1 and the other channel connects to FCC No. 2. The FCCs provide an excitation signal to the transducer, then receives a voltage signal back that is proportional to applied force. Control wheel movement is sensed by five RVDT sensors contained within the RVDT cluster on top of the aileron and elevator control module. The RVDT sensors translate mechanical movement into electronic signals to the FCCs. The FCCs interpret the electronic signals from the RVDTs and sends commands to the REU aileron actuators. 2. Component Location COMPONENT ATA QTY PER A/C LOCATION Aileron force sensor 27-12-01 2 Forward right side of aileron and elevator control module Aileron control module RVDT 27-12-03 2 Top of aileron and elevator control module, right side 3. Component Details A. Aileron Force Sensor The aileron force sensor is installed along the roll feel system load path for the pilot and copilot as part of the wheel control cable input sectors. The force sensor provides data to satisfy FAA / EASA flight data recording requirements. The force sensors are installed to detect pilot and copilot actions 27-12-00 Page 1 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL to override the AP servos. One sensor is located in the pilot aileron and elevator control module. The other sensor is in the copilot aileron and elevator control module. Each 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 data is used by the AP system and the FDR. The FCCs provide the data on an ARINC 429 data bus to the MAUs, where the AP modules reside. The AP uses the force data to automatically disconnect and return manual control. The MAUs transmit the force data on a digital data bus to the FDR. B. Aileron Control Module RVDT The pilot and copilot aileron and elevator control module assemblies contains a lateral position sensor that uses five RVDTs. The sensor canister is referred to as the RVDT cluster. The RVDT cluster is replaceable component but the individual transducers are not replaceable. The pilot and copilot control wheel 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 concentrically around the shaft. The pilot and copilot control wheel drives the RVDTs using the primary flight control cable and mechanical linkage. The primary flight control cable extends from the wheel / column assembly to the 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 wheel. The commanded position data 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 in order to move the flight control surface to the commanded position. For each wheel assembly, the position sensors share a common attachment point to the wheel pushrod. The RVDT cluster returns to neutral only if the RVDT main cluster shaft is sheared off. 4. Controls and Indications A. Circuit Breakers The system is protected by the following circuit breakers: NOMENCLATURE PANEL LOCATION POWER SOURCE L AIL HA LEER A9 L ESS 28VDC L AIL EBHA SEC LEER B9 L MAIN 28VDC L AIL EBHA PRI REER A3 UPS 28VDC R AIL EBHA PRI REER A4 UPS 28VDC R AIL HA REER A6 R ESS 28VDC R AIL EBHA SEC REER C7 R MAIN 28VDC 27-12-00 Page 2 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL NOMENCLATURE PANEL LOCATION POWER SOURCE L AIL EBHA PWR N/A EBHA PDB (tail compartment) EBHA BUS 28VDC R AIL EBHA PWR N/A EBHA PDB (tail compartment) EBHA BUS 28VDC B. Solid State Power Controllers The system is protected by the following solid state power controller: NOMENCLATURE IDENTIFICATION NUMBER POWER SOURCE ROLL TRIM 2702 R ESS 28VDC C. CAS Messages The CAS messages for the system are shown in the following table: MESSAGE COLOR MESSAGE DESCRIPTION FCS Maintenance Required Blue Flight control system maintenance is required. Notify maintenance for corrective action. Roll Control Miscompare Amber Pilot and copilot control wheel positions are different. Continue flight within flight envelope limitations. Aircraft roll response with respect to control wheel input may be reduced. Pilot L-R Brake Pedal Fail Amber Pilot left and right brake pedals failed. Copilot L-R Brake Pedal Fail Amber L-R Inboard Brake Fail Amber Left and right inboard brakes failed. L-R Outboard Brake Fail Amber Left and right outboard brakes failed. Uncommanded Brake Amber Brakes are not commanded. Brake By Wire Fail Amber Brake-by-wire has failed. Retrim Left Wing Down Amber Retrim left wing down. Retrim Right Wing Down Amber Retrim right wing down. L-R Aileron Fail Amber Both REUs failed or loss of aileron command to both ailerons. Continue flight within flight envelope limitations. Attempt FLT CTRL RESET. Roll Authority Limit Amber Roll axis flight control surfaces approaching maximum displacement. Adjust flight condition as necessary. Lateral Coupling Data Invalid Amber Copilot left and right brake pedals failed. Lateral coupling data a invalid. 27-12-00 Page 3 August 15/14