FLIGHT CONTROLS.pdf

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL FLIGHT CONTROLS — SYSTEM DESCRIPTION 1. General A. Description NOTE: The following paragraphs are used in conjunction with Figure 1. The aircraft uses a three axis Fly-By-Wire (FBW) system, which provides yaw, pitch and roll control in all phases of flight...

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL FLIGHT CONTROLS — SYSTEM DESCRIPTION 1. General A. Description NOTE: The following paragraphs are used in conjunction with Figure 1. The aircraft uses a three axis Fly-By-Wire (FBW) system, which provides yaw, pitch and roll control in all phases of flight. The Flight Control Computers (FCCs) are the FBW system central components. The FCCs receive and monitor data from various aircraft systems. The FCCs process and send data throughout the aircraft, including to Remote Electronic Units (REUs) and Motor Control Electronics (MCEs) at flight control surfaces. FCC data provided to REUs and backup MCEs controls the hydraulic manifolds. The manifolds supply hydraulic power to the ElectroHydraulic Servo Actuators (EHSAs) and the Electrical Backup Hydraulic Actuators (EBHAs), which move primary flight control surfaces. Flight controls are divided by function as follows: Primary Flight Control System (PFCS) Flap Actuation System (FAS) Horizontal Stabilizer Trim System (HSTS) (1) Primary Flight Control System The PFCS consist of ailerons, elevators, rudder and multi-function spoilers. Ailerons control aircraft roll around the longitudinal axis. Elevators control aircraft pitch around the lateral axis. The rudder controls aircraft yaw around the vertical axis. Spoilers assist ailerons in roll control and provide speed brake and ground spoiler functions. Spoilers decrease lift and increase drag in the following three operational modes: Outboard and midboard spoilers assist ailerons in aircraft roll control Ground spoilers (all spoilers) decrease lift and speed on landing roll, which increases braking effectiveness and shortens landing roll Speed brakes (all spoilers) decrease airspeed and increase descent rate during approach (2) Flap Actuation System The FAS includes the Flap Electronic Control Unit (FECU) and drive system. Flaps increase wing area as they extend aft and down, resulting in increased lift and drag. Flaps are used on takeoff to decrease ground run and on approach and landing to decrease stall speed, slow approach speed and shorten ground run. (3) Horizontal Stabilizer Trim System The HSTS includes the Horizontal Stabilizer Control Unit (HSCU) and Horizontal Stabilizer Trim Actuator (HSTA). Trim controls ease forces in all flight phases. 2. Subsystems Flight Control Computer, 27-01-00, System Description Backup Flight Control, 27-02-00, System Description Control System Interface, 27-03-00, System Description Aileron Control, 27-10-00, System Description Rudder Control, 27-20-00, System Description Elevator Control, 27-30-00, System Description Horizontal Stabilizer Control, 27-40-00, System Description Flap Control, 27-50-00, System Description 27-00-00 Page 1 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL Spoiler Control System, 27-60-00, System Description 3. Subsystem Details A. Flight Control Computer The FCCs provide control and monitoring for the aircraft FBW flight control system. The FBW system incorporates FCC redundancy with two fully functional FCC racks containing removable modules. The rack itself is also removable. One FCC rack is located in the LEER the other is located in the REER. See Figure 2. Each FCC consists of the following components: FCC FCC FCC FCC FCC FCC FCC channel A COM module channel A MON module channel B COM module channel B MON module fan module rack reset switch (pedestal location) Each FCC rack is comprised of two independent and redundant channels (A and B) each with dissimilar hardware. The FCCs provide 21 separate bidirectional ARINC 429 (A429) data buses and two separate standard A429 buses routed to actuation electronics at each control surface. B. Backup Flight Control The Backup Flight Control Unit (BFCU) provides limited, get home safe, flight control functions if FCC channels fail. The BFCU is located under the floor in the forward midcabin. If FCCs fail, the BFCU provides seven separate A429 data buses, which actuate REUs and associated MCEs. See Figure 3. C. Control System Interface Conventional pilot and copilot control wheels, columns and rudder pedals provide flight control data inputs using Rotary Variable Differential Transducer (RVDT) position sensors. The RVDTs provide commanded position data to FCCs and BFCU. Pilot and copilot aileron and elevator (lateral / longitudinal) control modules are located below the cockpit floor. The rudder control module is located forward of the pedestal. See Figure 4 and Figure 5. The trim control module is located in the aft section of the pedestal. See Figure 6. The trim control module contains aileron upper and lower ROLL trim switches, LWD / RWD and a ROLL MOTOR CONTROL switch. The ROLL MOTOR CONTROL switch disconnects roll trim motor power and sets FCC to accept data from ROLL trim switches. ROLL trim switches electronically bias control wheels using the aileron trim actuator in the control module. Biasing control wheels visually indicates to the pilot the amount of trim input sent to the control surface. With control wheels biased, RVDT output data to FCCs is biased, thereby altering data to control surfaces.. The trim control module contains two separate and independent elevator BACKUP PITCH trim switches, NOSE DOWN and NOSE UP. Simultaneously actuating both switches in a NOSE DOWN or NOSE UP direction trims nose down or up. The trim control module contains two separate and independent RUDDER trim switches, NOSE L and NOSE R. Simultaneously actuating switches in left or right direction trims nose left or right. A RUDDER AUTO CENTER pushbutton is provided on the trim control module. When pressed, the AUTO CENTER pushbutton returns rudder trim to neutral position. The control system interface includes the following components: 27-00-00 Page 2 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL Trim control module Aileron and elevator control module assembly (pilot) Aileron and elevator control module assembly (copilot) Rudder control module assembly D. Aileron Control The aileron control system provides electrical and mechanical control of ailerons, fault monitoring and annunciation. Ailerons and spoilers are located along rear beam station on each wing. REUs control hydraulic powered actuators that move aileron surfaces. Aileron deflection is 11° ±1° down and 19° ±1° up. See Figure 4 and Figure 7. Aileron control includes the following components: Aileron control wheel Cockpit flight control cable Cockpit flight control cable retaining pin Aileron control cable pulleys Aileron control override pushrod Aileron Aileron trim interconnect pushrod Aileron trim centering bungee Aileron force sensor Aileron control module RVDT Aileron EHSA actuator Aileron EBHA actuator Aileron EHSA manifold Aileron EB manifold Aileron HA manifold Aileron REU Aileron MCE Aileron damper Aileron trim actuator Aileron autopilot servo E. Rudder Control The rudder control system provides electrical and mechanical control of rudder, monitoring and annunciation. The rudder control surface is located on vertical stabilizer trailing edge. REUs control hydraulic powered actuators that move rudder surface. Rudder deflection is ±25° ±1° left and right. See Figure 5 and Figure 8. Rudder control includes the following components: Rudder Rudder Rudder Rudder Rudder Rudder Rudder Rudder Rudder Rudder Rudder force sensor control module RVDT EHSA actuator EBHA actuator EHSA manifold EB manifold HA manifold REU MCE damper 27-00-00 Page 3 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL F. Elevator Control The elevator control system provides electrical and mechanical control, fault monitoring and annunciation. Elevator control surfaces are located on the left and right trailing edge of the horizontal stabilizer. A Linear Variable Differential Transducer (LVDT) at elevator outboard provides surface location data to the FCCs. Elevator REUs control hydraulic powered actuators that move elevator surfaces. Elevator deflection is -24° ±1° up and +13° ±1° down. See Figure 4 and Figure 7. Elevator control includes the following components: Control column Elevator control override pushrod Elevator Elevator force sensor Elevator control module RVDT Elevator EHSA actuator Elevator EBHA actuator Elevator EHSA manifold Elevator EB manifold Elevator HA manifold Elevator LVDT Elevator REU Elevator MCE Elevator damper Elevator autopilot servo Stick shaker motor G. Horizontal Stabilizer Control Horizontal stabilizer control works in conjunction with flap selection to counter aircraft tendency to pitch nose up and down with extension and retraction of flaps. The horizontal stabilizer is mounted in a T-configuration on top of the vertical stabilizer and pivots to change the angle of incidence as flaps are extended or retracted. The horizontal stabilizer receives data from the Horizontal Stabilizer Control Unit (HSCU) and adjusts horizontal trim using the Horizontal Stabilizer Trim Actuator (HSTA). Horizontal Stabilizer control includes the following components: Horizontal stabilizer actuator Horizontal stabilizer actuator motor Horizontal stabilizer position resolver HSCU H. Flap Control The Flap Control System (FCS) is a conventional system that provides electrical and mechanical flap control, fault monitoring and annunciation. Flaps increase wing aerodynamic lift and drag, which improves takeoff, approach and landing performance. The Flap Control Handle (FCH) has four distinct detent positions that adjust flap surfaces to UP (0°), 10°, 20° (T/O APP) and DOWN (39°). See Figure 9 and Figure 10. Flap control includes the following components: Flap A track flap rollers B track flap rollers C track flap rollers 27-00-00 Page 4 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL D track flap rollers D track flap down load catch Flap Power Drive Unit (PDU) Flap PDU motor Flap torque shafts Flap pillow blocks Flap actuator (inboard) Flap actuator (outboard) Flap position resolver Flap control module FECU Flap hydraulic control module I. Spoiler Control System Three separate spoilers (inboard, midboard and outboard) are located on each wing. The REUs control hydraulic powered actuators that move the spoilers. See Figure 1. Spoilers provide the following functions: Assist ailerons in roll control Speed brakes Ground spoilers Spoiler control includes the following components: Inboard (ground) spoiler Inboard (ground) spoiler link Midboard (inboard flight) spoiler Midboard (inboard flight) spoiler link Outboard flight spoiler Outboard flight spoiler link Inboard (ground) spoiler EHSA actuator Midboard (inboard flight) spoiler EHSA actuator Outboard flight spoiler EBHA actuator Spoiler EHSA manifold Spoiler EB manifold Spoiler HA manifold Speed brake control module Ground spoiler arm switch Ground spoiler flap override switch Spoiler REU Spoiler MCE 4. Operational Summary A. Flight Controls Flight controls on the FBW system are controlled by pilot / copilot commands. Command data is sent to FCCs, which apply control laws and send digital signals to REUs located near the control surfaces. REUs control hydraulic powered actuators that move control surfaces. (1) Flight Control Computer The FCC system provides FBW control for the following: Ailerons (2) Spoilers (6) 27-00-00 Page 5 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL Elevators (2) Rudder HSCU The FCCs are the central components of the FBW system. The FCCs receive sensor data from various aircraft systems, including control inputs from cockpit sensors. The FCCs process data and transmit commands, based on control laws, to actuation electronics located at each control surface. (2) Backup Flight Control The BFCU is a simple controller with a direct interface to essential flight control REUs. The BFCU provides limited flight control functions if all FCCs fail. The REUs are connected to MCEs that supply hydraulic power to the primary flight control surfaces. The intent of the BFCU is to allow passengers, crew and aircraft to arrive safely at their destination if a malfunction occurs during a flight. When activated, the BFCU provides digital commands to the following: Ailerons Spoilers (outboard only) Elevators Rudder (3) Control System Interface The FCCs and BFCU control the PFCS using actuators. In normal operation, flight control surfaces are moved by the following two different types of actuators: EHSA EBHA Both types of actuators are active. Each actuator is locally controlled and monitored by an REU, which receives control data from the FCCs and BFCU. In standard operation the REU receives data from the FCCs and activates the EHSA manifold. The EHSA manifold supplies hydraulic pressure to the EHSA actuator to move the flight surface. If an EHSA system failure occurs, a dedicated MCE is activated. The EBHA Electrical Backup (EB) portion activates the EB manifold. The EB manifold maintains sufficient hydraulic fluid to supply pressure to the EBHA actuator to move the flight surface. (4) Aileron Control During flight, aircraft roll control (longitudinal axis) is accomplished by movement of the ailerons and spoilers. In addition to supporting roll control, spoilers also provided speed brake and ground spoiler functions. Flight spoilers are described in detail in the spoiler system description and its related subsystems. (5) Rudder Control During flight, the rudder provides aircraft yaw control (vertical axis) through a single rudder surface in the vertical stabilizer. Rudder movement is left and right (rudder trailing edge left, rudder trailing edge right), causing the aircraft to yaw nose left or nose right around the vertical axis. (6) Elevator Control During flight, aircraft pitch control (lateral axis) is accomplished by elevator surface movement, as well as by movement of the horizontal stabilizer. Left and right elevators move 27-00-00 Page 6 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL in unison. When elevator trailing edges goes up, the nose goes down. When elevator trailing edges goes down, the nose goes up. (7) Horizontal Stabilizer Control The horizontal stabilizer is controlled and monitored by the HSCU. In normal mode, the HSCU receives rate commands from the FCCs. In all other modes, the stabilizer is manually commanded using trim switches located on the trim control module in the pedestal. Horizontal stabilizer modes are related to the FCC mode. If there is normal communication between the FCCs and the HSCU, the stabilizer remains in normal mode. The HSCU moves the stabilizer at a constant predetermined rate. (8) Flap Control Flap control actuators move flaps to provide increased lift during approach and takeoff. Flap position is controlled by the FCH. The pilot manually adjusts the FCH to position the left and right flap surfaces as needed. (9) Spoiler Control System Ground spoiler deployment is controlled by the FCCs. The ground spoiler function is the automatic deployment of all six spoiler panels to reduce roll out and braking distance. Deployment occurs during landing touchdown or after an aborted takeoff. During deployment spoilers are extended to their maximum angular deflection of 55°. Each spoiler is moved by one actuator, EHSA on inboard and midboard panels and EBHA on outboard panels. 27-00-00 Page 7 August 15/14