Gulfstream G650ER Elevator System Electronics PDF

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL ELEVATOR SYSTEM ELECTRONICS — SYSTEM DESCRIPTION 1. General A. Description The elevator control system provides electrical and mechanical control of the elevator, fault monitoring and annunciation. Pilot and copilot control columns provide the control inpu...

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL ELEVATOR SYSTEM ELECTRONICS — SYSTEM DESCRIPTION 1. General A. Description The elevator control system provides electrical and mechanical control of the elevator, fault monitoring and annunciation. Pilot and copilot control columns provide the control inputs through RVDT position sensors. The commanded position information is provided to the two Flight Control Computers (FCCs) and the backup flight control unit. The computers transmit the information on digital data buses to the Remote Electronic Units (REUs) located at each actuator. The REUs command the hydraulic actuators that move the elevator surfaces. See Figure 1 and Figure 2. 2. Component Location COMPONENT ATA QTY PER A/C LOCATION Elevator remote electronics unit 27-35-01 2 Horizontal stabilizer rear beam Elevator motor control electronics 27-35-03 2 Horizontal stabilizer rear beam Elevator damper 27-35-05 2 Forward side of control column base, below floor 3. Component Details A. Elevator Remote Electronics Unit The REU is installed as part of the elevator actuation system at each instance of an EBHA or EHSA actuator. The REU provides positional control loop closure and failure management functions for the EBHA / EHSA. The REU contains level A software per DO-178B. The EHSA REU electronics box is mounted directly to the hydraulic manifold and receives electrical power from a single circuit breaker on the right essential dc bus for the right elevator and on the left essential dc bus for the left elevator. The EHSA REU receives surface position commands from the FCCs on two separate and independent bidirectional ARINC 429 (A429) data buses. One bus is from FCC No. 1 and the other from FCC No. 2. The REU is mounted on its associated hydraulic manifold. It processes the FCC signals and initiates electrical commands to the Mode Select Valve (MSV) solenoid and the Electro-Hydraulic Servo Valve (EHSV). The MSV and EHSV control the flow of hydraulic fluid to move the actuator in the desired direction. The EBHA REU electronics box is mounted directly to the HA hydraulic manifold and receives electrical power from two separate circuit breakers, both located on the UPS 28 Vdc bus. Two circuit breakers are provided to allow separate wire routes from each breaker through the engine and APU rotor burst zones. The EBHA REU receives surface position commands from the FCCs on two separate and independent bidirectional A429 data buses. The LVDT is separately mounted outboard of EHSA manifold and provides independent surface position to FCC via EHSA REU for redundancy. One bus is from FCC No. 1 and the other from FCC No. 2. The REU processes the FCC signals and initiates electrical commands to the MSV solenoid in the HA manifold the power select valve solenoid and EHSV in the EB manifold. Those components control the flow of hydraulic fluid to move the actuator in the desired direction. B. Elevator Motor Control Electronics The Motor Control Electronics (MCE) is an electronics box that is mounted to the EB manifolds alongside the EBHA actuators. During backup operation with an operational REU, the MCE receives a velocity command from the EBHA REU and in turn provides motor phase current 27-35-00 Page 1 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL corresponding to the velocity error. The velocity error is the difference between the commanded velocity and the actual velocity of the motor. The MCE interfaces with a resolver installed within the motor to determine the position and velocity of the motor. In backup mode following an REU failure, the MCE accepts commands from the FCC and an internal controller provides rate and direction commands to the EB manifold. C. Elevator Damper Elevator control column damping is provided by a damper connected to the base of each control column. Dampers provide smooth operation and alleviate oscillations. Dampers are installed at six locations such that damping is provided along the roll, pitch and yaw control axes. 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 R ELEV EBHA PRI REER B4 UPS 28VDC R ELEV HA REER B8 R ESS 28VDC L ELEV EBHA SEC REER B8 UPS 28VDC R ELEV EBHA SEC REER C8 UPS 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. 27-35-00 Page 2 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL MESSAGE COLOR 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. 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. 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 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 System Electronics Based on the pilot / copilot control column displacement, RVDT position sensors generate electrical commands to the FCCs. The FCCs process the RVDTs electrical commands and send augmented, shaped and scaled digital commands via a data bus to each elevator REU. Based on the FCCs commands, each REU provides electrical commands to its associated actuator, causing the elevator surface to move as commanded. In normal operation, each elevator surface is controlled by two actuators (one EHSA, one EBHA). The two actuators are simultaneously pressurized and active (i.e., active / active configuration). The left and right inboard actuators are EBHAs and the left and right outboard actuators are EHSAs. 27-35-00 Page 3 August 15/14