Gulfstream G650er Rudder Interface and Control PDF

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL RUDDER INTERFACE AND CONTROL — SYSTEM DESCRIPTION 1. General A. Description The rudder interface and control system provides the following: Rudder control Fault monitoring CAS notification The rudder system is part of the primary Flight Control System (FCS...

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL RUDDER INTERFACE AND CONTROL — SYSTEM DESCRIPTION 1. General A. Description The rudder interface and control system provides the following: Rudder control Fault monitoring CAS notification The rudder system is part of the primary Flight Control System (FCS). Conventional pilot and copilot rudder pedals are used to control aircraft yaw. The rudder pedals are mechanically linked, with no disconnect provided between the two pedal assemblies. The rudder control module is located above the floor, forward of and below the flight panel display units. See Figure 1. The primary FCS is an integrated three axis Fly-By-Wire (FBW) system. The FBW system has an artificial feel design for human factors operation. Dampers provide smooth operation and alleviate oscillations. The FBW system provides the following control: Yaw control through the rudder control system. See Rudder Control, 27-20-00, System Description Pitch control through the elevator control system. See Elevator Control, 27-30-00, System Description. The pitch control function is supported by the horizontal stabilizer control system. See Horizontal Stabilizer Control, 27-40-00, System Description Roll control through the aileron control system. See Aileron Control, 27-10-00, System Description. The roll control function is supported by the spoiler control system. See Spoiler Control System, 27-60-00, System Description 2. Component Location COMPONENT ATA QTY PER A/C LOCATION Rudder 27-21-03 1 Aft edge of vertical stabilizer 3. Component Details A. Rudder Interface Control During flight, the rudder provides aircraft yaw control through a single rudder surface in the vertical stabilizer. Electronically controlled hydraulic actuators provide power for rudder surface movement. Pilot and copilot rudder pedals provide control inputs through RVDT position sensors. Commanded position data from RVDT position sensors is provided to two Flight Control Computers (FCCs) and the Backup Flight Control Unit (BFCU). The BFCU commands are ignored by REUs unless a total failure of both FCCs occurs. The FCCs transmit data on digital data buses to Remote Electronic Units (REUs) located at each rudder actuator. The REUs command hydraulic actuators that move the rudder surface. See Figure 2 and Rudder Cockpit Sensors, 27-22-00, System Description. Two bidirectional ARINC 429 (A429) buses to rudder REUs are provided by FCC No. 1. One standard A429 bus is provided to rudder REUs by FCC No. 2. Bus selection is done at the REU level. The rudder surface is actuated by one EBHA and one EHSA actuator. The EBHA is configured with two R/T bus interfaces. The EHSA has one R/T bus and one receive-only bus interface. 27-21-00 Page 1 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL The rudder trim function uses two separate and independent switches located in the trim control module. The trim control panel is located on the pedestal. Simultaneously actuating both switches in a left or right direction causes the nose to trim to the selected direction. See Figure 3. When the RUDDER trim switch is actuated, the FCCs command the rudder surface to move in the requested direction. An AUTO CENTER pushbutton is provided on the trim control module. When selected, the AUTO CENTER pushbutton returns rudder trim to a neutral position. NOTE: The rudder trim switches are directly read by the FCC for electronic trim function. 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. 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 data required by the flightcrew is shown on the main displays as CAS messages and synoptic page data. 27-21-00 Page 2 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL 5. Operation A. Rudder Interface and Control The pilot and copilot use conventional rudder pedals to control rudder movement as follows: Left rudder pedal moves the rudder trailing edge left (aircraft nose left) Right rudder pedal moves the rudder trailing edge right (aircraft nose right) The REU controlled hydraulic actuators provide power for rudder surface movement. Rudder movement is left (trailing edge left) and right (trailing edge right), causing aircraft to yaw nose left or nose right around the vertical axis. Rudder deflection is ±25° ±1° left and right. 27-21-00 Page 3 August 15/14