AILERON SYSTEM ELECTRONICS.pdf

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL AILERON SYSTEM ELECTRONICS — SYSTEM DESCRIPTION 1. General A. Description The aileron Flight Control System (FCS) provides the following: Aileron control Fault monitoring CAS notification The aileron system is part of the primary FCS. Conventional pilot an...

GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL AILERON SYSTEM ELECTRONICS — SYSTEM DESCRIPTION 1. General A. Description The aileron Flight Control System (FCS) provides the following: Aileron control Fault monitoring CAS notification The aileron system is part of the primary FCS. Conventional pilot and copilot controls provide inputs to the RVDT position sensors. The RVDT position sensors provide data to the Flight Control Computers (FCCs) and the Backup Flight Control Unit (BFCU). The FCCs send data on digital data buses to the Remote Electronic Units (REUs) located at each aileron actuator. The REUs command the hydraulic actuators that move the ailerons. The ailerons are located horizontally on the outer trailing edge of each wing. During flight, ailerons provide aircraft roll control. Aileron movement is up and down, causing the aircraft to roll left or right around the longitudinal axis. See Figure 1, Figure 2, Figure 3, Figure 4 and Figure 5. 2. Component Location COMPONENT ATA QTY PER A/C LOCATION Aileron remote electronics unit 27-15-01 4 EHSA and HA manifold on wing rear beam Aileron motor control electronics 27-15-03 2 EB manifold on wing rear beam Aileron damper 27-15-05 2 Right lower side of aileron and elevator control module Aileron trim actuator 27-15-07 1 Left aft side of pilot aileron and elevator control module 3. Component Details A. Aileron Remote Electronics Unit The REU is installed 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 is mounted directly to the hydraulic manifold. Each REU receives 28 Vdc electrical power from two separate circuit breakers. The EHSA REU receives surface position commands from FCCs on two separate and independent Bidirectional ARINC 429 (BD429) data buses. One bus is from FCC No. 1, the other is from FCC No. 2. The REU processes FCC signals and initiates electrical commands to the Mode Select Valve (MSV) solenoid and Electro-Hydraulic Servo Valve (EHSV). The MSV and EHSV control the hydraulic fluid flow that moves the actuator in the commanded direction. The EBHA REU is mounted directly to the HA hydraulic manifold and receives 28 Vdc electrical power from one circuit breaker. 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 FCCs on two separate and independent BD429 data buses. One bus is 27-15-00 Page 1 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL from FCC No. 1, the is other from FCC No. 2. The REU processes FCC signals and initiates electrical commands to the HA manifold MSV solenoid, the power select valve solenoid and the EB manifold EHSV. These components control the hydraulic fluid flow that moves the actuator in the commanded direction. B. Aileron Motor Control Electronics The MCE is mounted to the EB manifold adjacent to the EBHA actuators. In backup mode with an operational REU, the MCE receives velocity commands from the EBHA REU. The MCE provides motor phase current corresponding to the velocity error. Velocity error is the difference between commanded velocity and actual motor velocity. The MCE interfaces with a resolver installed within the motor to determine motor position and velocity. In backup mode following an REU failure, the MCE accepts FCC commands and an internal controller provides rate and direction commands to the EB manifold. C. Aileron Damper The aileron damper is installed as part of the aileron and elevator control modules. The damper is installed below the autopilot servo motor on both the pilot and copilot control modules. This damper provides wheel damping. Dampers are installed at six locations to provide damping for aileron, elevator and rudder control. Dampers provide smooth operation and alleviate oscillations. D. Aileron Trim Actuator The aileron roll trim actuator is installed only on pilot side control module assembly. The roll trim actuator positions the ground centering crank arm in the feel mechanism. This causes control wheels to center at positions determined by trim actuator position. The aileron trim actuator imposes a 50% maximum roll control command. 4. Controls and Indications A. Circuit Breakers The system is protected by the following circuit breakers: NOMENCLATURE PANEL LOCATION POWER SOURCE L AIL HA LEER A9 L ESS 28VDC L AIL EBHA SEC LEER B9 L MAIN 28VDC L AIL EBHA PRI REER A3 UPS 28VDC R AIL EBHA PRI REER A4 UPS 28VDC R AIL HA REER A6 R ESS 28VDC R AIL EBHA SEC REER C7 R MAIN 28VDC L AIL EBHA PWR N/A EBHA PDB (tail compartment) EBHA BUS 28VDC R AIL EBHA PWR N/A EBHA PDB (tail compartment) EBHA BUS 28VDC 27-15-00 Page 2 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL B. Solid State Power Controllers The system is protected by the following solid state power controllers: NOMENCLATURE IDENTIFICATION NUMBER POWER SOURCE ROLL TRIM 2702 R ESS 28 Vdc C. CAS Messages The CAS messages for the system are shown in the following table: MESSAGE COLOR MESSAGE DESCRIPTION FCS Maintenance Required Blue Flight control system maintenance is required. Notify maintenance for corrective action. Roll Control Miscompare Amber Pilot and copilot control wheel positions are different. Continue flight within flight envelope limitations. Aircraft roll response with respect to control wheel input may be reduced. Pilot L-R Brake Pedal Fail Amber Pilot left and right brake pedals failed. Copilot L-R Brake Pedal Fail Amber L-R Inboard Brake Fail Amber Left and right inboard brakes failed. L-R Outboard Brake Fail Amber Left and right outboard brakes failed. Uncommanded Brake Amber Brakes are not commanded. Brake By Wire Fail Amber Brake-by-wire has failed. Retrim Left Wing Down Amber Retrim left wing down. Retrim Right Wing Down Amber Retrim right wing down. L-R Aileron Fail Amber Both REUs failed or loss of aileron command to both ailerons. Continue flight within flight envelope limitations. Attempt FLT CTRL RESET. Roll Authority Limit Amber Roll axis flight control surfaces approaching maximum displacement. Adjust flight condition as necessary. Lateral Coupling Data Invalid Amber Copilot left and right brake pedals failed. Lateral coupling data is invalid. 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. Speed Brake Fail Amber Speed brake control failed. Notify maintenance for corrective action. 27-15-00 Page 3 August 15/14 GULFSTREAM G650ER SYSTEM DESCRIPTION MANUAL MESSAGE COLOR MESSAGE DESCRIPTION FCS Test Fail Amber Flight control system built-in test failed. Notify maintenance for corrective action. 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 data required by the flightcrew is shown on the main displays as CAS messages and synoptic page data. 5. Operation A. Aileron System Electronics Ailerons, flight spoilers and the aileron trim switch provide aircraft roll control during normal operating conditions. The aircraft roll command is initiated when either control wheel is rotated. The motion is converted by the aileron and elevator control module assembly into an electronic signal and data is sent to the FCCs. The FCCs interpret the data and sends commands through BD429 data buses to REUs in the wing. The REUs control actuators that move the aileron and flight spoiler surfaces to comply with the requested commands. 27-15-00 Page 4 August 15/14