Gulfstream G650ER Rudder Control System Description Manual PDF

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

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL RUDDER CONTROL — SYSTEM DESCRIPTION 1. General A. Description The rudder control system provides the following: Rudder control Fault monitoring CAS notification The rudder system is part of the primary Flight Control System (FCS). Rudder control surface is located vertically on trailing edge of vertical stabilizer. During flight, the rudder FCS provides aircraft yaw control. Rudder movement is left (trailing edge left) and right (trailing edge right), causing aircraft to yaw nose left or nose right around vertical axis. Rudder deflection is ±25° ±1° left and right. 2. Subsystems Rudder Rudder Rudder Rudder Interface and Control, 27-21-00, System Description Cockpit Sensors, 27-22-00, System Description Hydraulic Actuation, 27-23-00, System Description System Electronics, 27-25-00, System Description 3. Subsystem Details A. Rudder Interface and Control Conventional pilot and copilot rudder pedals provide inputs to the rudder RVDT position sensors. The RVDT position sensors then provide data to the Flight Control Computers (FCCs) and the Backup Flight Control Unit (BFCU). The FCCs send data on Bidirectional ARINC 429 (BD429) digital data buses to the Remote Electronic Units (REUs) located at each rudder actuator. The REUs command the hydraulic actuators to move the rudder. Rudder pedals are mechanically linked, with no disconnect provided between the two pedal sets. The rudder control module is located above the floor, forward of the pedestal. Both pilot and copilot rudder pedals are connected to the rudder control module. See Figure 1. B. Rudder Cockpit Sensors Rudder movement is sensed by five RVDT sensors contained in the RVDT cluster on top of the rudder control module. The RVDT sensors translate mechanical movement into electronic signals provided to the FCCs. The FCCs and BFCU provide excitation voltage signals to the sensors and receive voltage signals back that indicate rudder pedal displacement. When changes occur, the FCCs or BFCU command REUs to energize actuators that move flight surface to commanded position. The RVDT sensors provide data to the following: FCCs BFCU Autopilot system Flight data recorder NOTE: The BFCU commands are ignored by the REUs unless there has been a total failure of both FCCs. 27-20-00 Page 1 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL C. Rudder Hydraulic Actuation The FCCs provide position signals to the REUs in order to operate the rudder hydraulic actuators. Hydraulic pressure to the actuators passes through the hydraulic manifolds and is controlled by the REUs. The actuators are powered by the left and right hydraulic system engine-driven pumps during normal operation. Rudder is controlled by the following two separate and independent actuators: EHSA - Upper actuator EBHA - Lower actuator The EBHA actuator consists of an EHSA-type hydraulic part, combined with local Motor Control Electronics (MCE) to drive the hydraulic cylinder / piston in backup mode. The EBHA REU is mounted directly to the hydraulic actuator manifold. The MCE is mounted directly to the electrical backup hydraulic manifold. The associated actuator is located between the hydraulic actuator manifold and electrical backup manifold. The EBHA actuator has the following dual power source: Hydraulic Electric The EBHA has an hydraulic cylinder / piston assembly and the following two hydraulic manifolds: HA EB D. Rudder System Electronics In normal operation rudder surface is electrically controlled by two actuators in active / active configuration. Both actuators are simultaneously pressurized and active. The EBHA is powered by the 28 Vdc uninterruptible power supply bus and receives hydraulic pressure from the right hydraulic system. The FCCs provide data to REUs to activate actuators. The REUs provide position loop closure and actuator monitoring. For integrity control the REU has two dissimilar hardware lanes, one for command and one for monitoring. The FCC 1 provides two BD429 buses to REUs, whereas FCC 2 provides one bus. Bus selection is done at the REU level. 4. Operational Summary A. Rudder Control Rudder moves left and right to control aircraft yaw around vertical axis. The pilot / copilot control rudder surface using rudder pedals. Rudder pedals are depressed left (trailing edge left , yaw nose left), or right (trailing edge right, yaw nose right). The rudder trim switches are directly read by the FCC for electronic trim function. The rudder trim function uses two separate and independent switches located in the trim control module. The trim control module is located on the pedestal. Simultaneously actuating both switches in a left or right direction causes the nose to trim left or right. See Figure 2. When RUDDER trim switch is actuated, FCCs command rudder surface to move in requested direction. An AUTO CENTER pushbutton is provided on the trim control module. When selected, the AUTO CENTER pushbutton returns rudder trim a neutral position. 27-20-00 Page 2 August 15/14