RUDDER SYSTEM ELECTRONICS.pdf

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL RUDDER SYSTEM ELECTRONICS — SYSTEM DESCRIPTION 1. General A. Description The rudder control system provides electrical and mechanical control of the rudder, fault monitoring and annunciation. In normal operation, the rudder surface is electrically controll...

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL RUDDER SYSTEM ELECTRONICS — SYSTEM DESCRIPTION 1. General A. Description The rudder control system provides electrical and mechanical control of the rudder, fault monitoring and annunciation. In normal operation, the rudder surface is electrically controlled by two actuators in active / active configuration. Both actuators are simultaneously pressurized and active. The upper actuator is an EHSA actuator. The lower rudder actuator is an EBHA actuator. The EBHA is powered by the 28 Vdc Uninterruptible Power Supply (UPS) bus and receives hydraulic pressure from the right hydraulic system. See Figure 1 and Figure 2. The Flight Control Computers (FCCs) provide mode and position command data to the Remote Electronics Units (REUs). The FCC No. 1 provides two bidirectional ARINC 429 (BD429) buses to each REU. The FCC No. 2 provides one bidirectional bus to the EBHA REU and one unidirectional bus to the EHSA REU. Bus selection is done at the REU level. The EHSA has one R/T bus interface and one R-only bus interface. The EBHA is configured with two R/T bus interfaces. When the EBHA is commanded into active mode with normal hydraulic power, the REU and Motor Control Electronics (MCE) energize a torque motor that moves the twoposition solenoid operated valve into the active position. 2. Component Location COMPONENT ATA QTY PER A/C LOCATION Rudder remote electronics unit 27-25-01 2 Vertical stabilizer rear beam Rudder motor control electronics 27-25-03 1 Vertical stabilizer rear beam Rudder damper 27-25-05 2 Rudder pedal assembly 3. Component Details A. Rudder Remote Electronics Unit The REU is installed as part of the rudder actuation systems 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 EHSA manifold and receives electrical power from a single circuit breaker on the right essential dc bus. The EHSA REU receives surface position commands from the FCCs on two separate and independent BD429 data buses. One bus is from FCC No. 1 and the other from FCC No. 2. The EHSA REU is mounted on its associated hydraulic manifold. The REU processes the FCC signals and initiates electrical commands to the Mode Select Valve (MSV) solenoid and the ElectroHydraulic Servo Valve (EHSV), the main control valve. 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 BD429 data buses. One bus is from FCC No. 1 and the other from FCC No. 2. The 27-25-00 Page 1 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL EBHA REU processes the FCC signals and initiates electrical commands to the following components, which control the flow of hydraulic fluid that moves the actuator in the desired direction: MSV solenoid in the HA manifold Power select valve solenoid in the EB manifold EHSV in the EB manifold B. Rudder Motor Control Electronics The MCE is mounted to the EB manifolds below 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 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. If both the EBHA REU and EHSA REU are invalid, the MCE has a limited capability to control the electrical motor and actuator on its own. In that condition, the MCE receives the surface command signals directly from FCC No. 2, provided the command is valid, using the FCC No. 2 MCE standard ARINC 429 bus. C. Rudder Damper Rudder pedal damping is provided by two dampers connected to the pilot and copilot pedal assemblies. The rudder damper is installed as part of the center rudder control module assembly. Dampers are installed along each of the roll, pitch and yaw control axes. Dampers provide smooth operation and alleviate oscillations. 4. Controls and Indications A. Circuit Breakers The system is protected by the following circuit breakers: NOMENCLATURE PANEL LOCATION POWER SOURCE RUD EBHA PRI REER B1 UPS 28VDC RUD EBHA SEC REER B2 UPS 28VDC RUD HA REER B7 R ESS 28VDC RUD 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 Yaw Trim Auto Center Blue Yaw trim automatic centering feature is active. No action is needed if this is desired condition. Yaw Trim Nose Left Limit Blue Yaw trim has reached its capacity in nose left direction. Yaw Trim Nose Right Limit Blue Yaw trim has reached its capacity in nose right direction. Rudder Steering Fail Amber Rudder steering failed. 27-25-00 Page 2 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL MESSAGE COLOR MESSAGE DESCRIPTION Rudder Steering Off Amber Rudder steering is off. Rudder Single Actuator Amber Single rudder actuator failed. Notify maintenance for corrective action. Attempt FLT CTRL RESET. Rudder Fail Amber Both REUs failed or loss of rudder command. Continue flight within flight envelope limitations. Attempt FLT CTRL RESET. Yaw Authority Limit Amber Rudder approaching maximum displacement. Adjust flight condition as necessary. Yaw Damper Fail Amber Yaw damper has failed. Continue flight within flight envelope limitations. NOTE: The FCC status information required by the flightcrew is shown on the main displays as CAS messages and synoptic page data. 5. Operation A. Rudder System Electronics During flight, aircraft yaw control is accomplished through a single rudder surface in the vertical tail. The pilot / copilot use conventional rudder pedals to control rudder movement as follows: Left rudder pedal moves the rudder trailing edge left (yaw aircraft nose left) Right rudder pedal moves the rudder trailing edge right (yaw aircraft nose right) The commanded position information is measured by RVDT sensors located in the rudder control module. The RVDT sensors send digital data to the FCCs and the backup flight control unit. The FCCs send the commanded position to the rudder REUs using BD429 digital data buses. The REUs activate the EBHA and EHSA actuators to move the rudder surface to the commanded position. If the REUs fail, the MCE controls the electrical motor and actuator using command signals received directly from FCC No. 2 to move the rudder surface provided FCC commands to the MCE are valid. 27-25-00 Page 3 August 15/14