Gulfstream G650ER Spoiler Interface and Control PDF

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL SPOILER INTERFACE AND CONTROL — SYSTEM DESCRIPTION 1. General A. Description The spoiler control system provides electrical and mechanical control of the spoilers, fault monitoring and annunciation. The spoilers are used for different flight control functi...

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL SPOILER INTERFACE AND CONTROL — SYSTEM DESCRIPTION 1. General A. Description The spoiler control system provides electrical and mechanical control of the spoilers, fault monitoring and annunciation. The spoilers are used for different flight control functions. Spoilers assist the ailerons in roll control and also provide speed brake and ground spoiler functions. See Figure 1. The spoiler system is part of the primary flight control system. The primary flight control system is an integrated three axis Fly-By-Wire (FBW) system that provides the following control: 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 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 Yaw control through the rudder control system. See Rudder Control, 27-20-00, System Description Conventional control wheels are used by the flightcrew to control spoiler surfaces but are primarily controlled by the speed brake handle. The FBW control system is designed with artificial feel in order to provide a conventional feel for the human controls interface. Dampers provide smooth operation and alleviate oscillations. The control wheels are mechanically linked during normal operation so they always move together. If a jam occurs with one of the control wheels, either pilot may override the other by exceeding and maintaining the breakaway force. Each control wheel is connected by the primary flight control cable to its associated pilot and copilot aileron and elevator control module. The aileron and elevator control modules are located below the cockpit floor. Spoiler surfaces are located forward of the flaps on the rear beam of the left and right wing. There are three separate spoiler panels located on each wing, as follows: Inboard Midboard Outboard Electrically controlled hydraulic actuators provide power for spoiler surface movement. Pilot and copilot control wheels provide the control inputs through aileron cockpit sensors. See Aileron Cockpit Sensors, 27-12-00, System Description for more details. The commanded spoiler position data is provided to the two Flight Control Computers (FCCs) and the Backup Flight Control Unit (BFCU). The BFCU only commands the outboard spoilers. The computers transmit the data on ARINC 429 digital data buses to the Remote Electronic Units (REUs) located at each spoiler actuator. The REUs command the hydraulic actuators that move the spoiler surfaces. NOTE: The BFCU commands are ignored by the REUs unless there is a total failure of both FCCs. The following two types of actuators are used to move the spoilers: EHSA - Ground and Inboard flight EBHA - Outboard flight 27-61-00 Page 1 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL The same REU fits all locations and is configured by pin programming. See Spoiler Actuation, 27-63-00, System Description for more details. 2. Component Location COMPONENT ATA QTY PER A/C LOCATION Inboard spoiler (ground) 27-61-01 2 Wing rear beam Inboard (ground) spoiler link 27-61-03 2 Between inboard spoiler and wing Midboard spoiler (inboard flight) 27-61-05 2 Wing rear beam Midboard (inboard flight) spoiler link 27-61-07 2 Between midboard spoiler and wing Outboard spoiler (outboard flight) 27-61-09 2 Wing rear beam Outboard (outboard flight) spoiler link 27-61-11 2 Between outboard spoiler and wing 3. Component Details A. Inboard Spoiler (Ground) The inboard spoilers are controlled by an EHSA actuator. Control signals are provided by the FCCs. The EHSA actuators have one R/T bus interface and one receive-only bus interface. If a total failure of the FCCs occurs, the BFCU provides control signals. B. Inboard (Ground) Spoiler Link The inboard spoiler link is a structural element between the spoiler panel and the wing structure. The spoiler links consist of two force members with spherical bearings. Spoiler links prevent the spoiler panels from picking up wing bending induced lateral loads. C. Midboard Spoiler (Inboard Flight) The midboard flight spoilers are controlled by an EHSA actuator. Control signals are provided by the FCCs. The EHSA actuators have one R/T bus interface and one receive-only bus interface. The BFCU only communicates to the EBHA REU. D. Midboard (Inboard Flight) Spoiler Link The midboard flight spoiler link is a structural element between the spoiler panel and the wing structure. The spoiler links are two force members with spherical bearings. Spoiler links prevent the spoiler panels from picking up wing bending induced lateral loads. E. Outboard Spoiler (Outboard Flight) The outboard spoilers are controlled by an EBHA actuator. Control signals are provided by the FCCs. The EBHA actuators are configured with two R/T bus interfaces. If a total failure of the FCCs occurs, the BFCU provides control signals. F. Outboard (Outboard Flight) Spoiler Link The outboard spoiler link is a structural element between the spoiler panel and the wing structure. The spoiler links are two force members with spherical bearings. Spoiler links prevent the spoiler panels from picking up wing bending induced lateral loads. 27-61-00 Page 2 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL 4. Controls and Indications A. Circuit Breakers The system is protected by the following circuit breakers: NOMENCLATURE PANEL LOCATION POWER SOURCE R INBD SPLR HA LEER A6 L ESS 28VDC L INBD SPLR HA LEER A7 L ESS 28VDC R OUTBD SPLR EBHA SEC LEER B6 L MAIN 28VDC L OUTBD SPLR EBHA SEC LEER B7 L MAIN 28VDC L MID SPLR HA PRI REER B5 R ESS 28VDC R MID SPLR HA PRI REER B6 R ESS 28VDC L OUTBD SPLR EBHA PRI REER C1 UPS 28 VDC R OUTBD SPLR EBHA PRI REER C2 UPS 28VDC L MID SPLR HA SEC REER C5 R ESS 28VDC R MID SPLR HA SEC REER C6 R ESS 28VDC L OUTBD SPLR EBHA PWR N/A EBHA PDB (tail compartment) EBHA BUS 28VDC R OUTBD SPLR 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 Ground Spoiler Unarm Blue Ground spoiler system is not armed with landing gear extended. Select GND SPOILER to ARMED if desired. Speed Brake Extended Blue Speed brakes are extended, throttles at idle. Retract speed brakes if this is not the desired flight condition. Speed Brake Extended Amber Speed brakes (flight spoilers) are deployed with throttles above idle. Retract speed brakes or reduce thrust as desired. Speed Brake Fail Amber Speed brake control failed. Notify maintenance for corrective action. Amber REU failure or loss of spoiler command to any spoiler panel. Continue flight within flight envelope limitations. NOTE: Symmetric spoiler on opposite wing will be rendered inoperative for speed brake and ground spoiler; however, still operative for roll control. Spoiler Panel Fail 27-61-00 Page 3 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL MESSAGE COLOR MESSAGE DESCRIPTION Speed Brake Auto Retract Amber Speed brakes (flight spoilers) automatically retracted with speed brake handle not in RETRACTED position and TLA =90% or angle of attack limiting encountered. Place speed brake handle at RETRACTED position. If unable, speed brakes will be unavailable while message is displayed. Ground Spoiler Red Failure of ground spoiler component or deployed ground spoiler panel. Select ground spoiler switch OFF and perform appropriate procedures. 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. Spoiler Interface and Control (1) Spoiler Control One actuator controls each spoiler. Each of the two FCCs provides four bidirectional ARINC 429 buses to the spoiler REUs. Bus selection is done at the REU level. In normal operation the following occurs: FCC No. 1 controls the outboard EBHAs and inboard EHSAs FCC No. 2 controls the midboard EHSAs If FCC No. 1 fails, FCC No. 2 controls the following: Outboard flight EBHAs secondary input (R/T) Ground EHSAs secondary input (receive only) If FCC No. 2 fails, FCC No. 1 controls the following: Inboard flight EHSAs secondary input (receive only) (2) Ground Spoilers Ground spoiler deployment is controlled by the FCCs. Provided the ground spoiler deployment conditions are satisfied, automatic deployment of all three pairs of spoilers occurs at landing, touchdown or in a rejected takeoff. The two primary pilot inputs for ground spoiler deployment are as follows: Throttle at idle GND SPOILER switch set to ARMED The GND SPOILER armed switch is the primary pilot control for system operation. For automatic ground spoiler deployment, the switch shall be placed in the ARMED position. The GND SPOILER switch is located on the pedestal switch panel. Additionally, the FCC looks at combinations of indications to determine if the appropriate conditions are met for ground spoiler deployment from the following sensors: Main landing gear WOWs Wheel speed Radio altimeter (3) Spoilers 27-61-00 Page 4 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL Spoiler operation is controlled by the FCCs. The outboard and midboard spoiler panel are used for roll augmentation. The two spoilers on the downward moving wing are extended to assist the ailerons with roll. With speed brakes extended, spoilers on the downward moving wing are extended farther than those on the upward moving wing. Spoiler commands are derived from the same control wheel RVDT sensor inputs to the FCC that command the ailerons. The amount of spoiler deflection is determined by the particular flight conditions and the commanded rate of roll. The FCC control law determines the required spoiler angular deflection for any particular turn, with 55° being the maximum. To ensure adequate roll performance when the speed brakes are deployed, a mixing law for simultaneous roll and speed brake commands is implemented. 27-61-00 Page 5 August 15/14