CL_604-FLIGHT_CONTROLS庞巴迪挑战者飞行操纵

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CL_604-FLIGHT_CONTROLS
 
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Table of Contents For Training Purposes Only Sept 04 10-i P I LOT T R A I N I N G GU I D E FLIGHT CONTROLS Introduction .......................................................................................................................10-1 Primary Flight Controls................................................................................................10-1 Secondary Flight Controls...........................................................................................10-1 Primary Flight Controls .....................................................................................................10-2 Description ..................................................................................................................10-2 Components and Operation........................................................................................10-2 Ailerons .................................................................................................................10-2 Elevators ...............................................................................................................10-6 Rudder ..................................................................................................................10-8 Secondary Flight Controls............................................................................................... 10-10 Description ................................................................................................................ 10-10 Components and Operation...................................................................................... 10-10 Horizontal Stabilizer Trim .................................................................................... 10-10 Horizontal Stabilizer Trim Priority........................................................................ 10-11 Horizontal Stabilizer Trim Clacker....................................................................... 10-12 Mach Trim ........................................................................................................... 10-12 Aileron Trim......................................................................................................... 10-12 Rudder Trim ........................................................................................................ 10-12 Flaps ................................................................................................................... 10-14 Flight Spoilers ..................................................................................................... 10-16 Ground Spoilers .................................................................................................. 10-18 Stall Protection System................................................................................................... 10-20 Stick Pusher Disconnect ........................................................................................... 10-20 SPS Ground Testing ........................................................................................... 10-22 Controls and Indicators ................................................................................................... 10-23 Primary Flight Controls.............................................................................................. 10-24 Stab Trim, Aileron Trim, Rudder Trim ....................................................................... 10-25 Flaps, Spoilers .......................................................................................................... 10-26 Stall Protection System............................................................................................. 10-27 EICAS Messages...................................................................................................... 10-33 10-ii For Training Purposes Only May 03 FLIGHT CONTROLS P I LOT T R A I N I N G GU I D E Page Intentionally Left Blank List of Figures Graphic Title Figure For Training Purposes Only May 03 10-iii P I LOT T R A I N I N G GU I D E FLIGHT CONTROLS Flight Control Surfaces .....................................................................................................10-1 Roll Control - Schematic ...................................................................................................10-2 Pitch Control - Schematic .................................................................................................10-3 Yaw Control - Schematic ..................................................................................................10-4 Stab Trim Panel ................................................................................................................10-5 Stab Trim Indications ........................................................................................................10-6 Aileron/Rudder Trim Panel................................................................................................10-7 Aileron/Rudder Trim Indications........................................................................................10-8 Flap Schematic .................................................................................................................10-9 Flight and Ground Spoilers - Schematic ......................................................................... 10-10 Ground Spoilers Arming Logic ........................................................................................ 10-11 Stall Protection System - Schematic............................................................................... 10-12 Pitch, Roll and Yaw Controls .......................................................................................... 10-13 TRIM Controls.................................................................................................................10-14 Flap and Spoiler Controls ............................................................................................... 10-15 Stall Protection System................................................................................................... 10-16 EICAS Flight Controls Indications (Ground Spoilers) ..................................................... 10-17 EICAS Flight Controls Indications (Flight Spoilers)......................................................... 10-18 EICAS Flight Controls Indications (Flaps)....................................................................... 10-19 EICAS Flight Controls Indications (Trim) ........................................................................ 10-20 EICAS Flight Controls Indications (Aileron, Elevator, Rudder) ....................................... 10-21 10-iv For Training Purposes Only May 03 FLIGHT CONTROLS P I LOT T R A I N I N G GU I D E Page Intentionally Left Blank FLIGHT CONTROLS For Training Purposes Only Sept 04 10-1 P I LOT T R A I N I N G GU I D E CHAPTER 10: FLIGHT CONTROLS Introduction The Challenger 604 has conventional flight controls organized on an advanced technology airfoil and a T-tail configuration empennage. The flight control surfaces are actuated by crew or autopilot inputs via mechanical connections to hydraulic Power Control Units (PCUs). Artificial control loading is provided at the individual control columns, control wheels and rudder pedals. The flight controls may be divided functionally into two categories: Primary and Secondary Flight Controls. Primary Flight Controls The primary flight controls are the ailerons, elevators and rudder. Each aileron and elevator is powered by two hydraulic systems. The rudder is powered by all three hydraulic systems. In the unlikely case of total electrical failure or double-engine failure, ACMP 3B can be electrically energized directly from the Air-Driven Generator (ADG). This ensures hydraulic power is available to the flight controls. Secondary Flight Controls The secondary flight controls include the trim systems, (aileron, rudder and horizontal stabilizer), flaps, flight spoilers and ground spoilers. The stall protection system (SPS) is also considered a function of the secondary flight control system. Flight Control Surfaces Figure 10-1 Rudder Elevators Aileron Flaps Ground Spoiler Flight Spoiler P604_10_001 FLIGHT CONTROLS 10-2 For Training Purposes Only May 03 P I LOT T R A I N I N G GU I D E Primary Flight Controls Description The primary flight controls are arranged conventionally with rudder pedals and a control wheel and column for both the pilot and copilot. Movement of the cockpit controls is transmitted mechanically via cable and/or pushrods to the aileron, elevator and rudder power control units (PCUs) which hydraulically move the control surfaces. Artificial control loading provides tactile feedback to the pilots at the individual control columns, control wheels and rudder pedals. Position indicators are located on the EICAS Flight Controls Synoptic Page. White triangles and position scales indicate relative deflection of the ailerons, elevators and rudder. Aileron and elevator flight control surfaces are each powered by two hydraulic systems, and the rudder is powered by all three systems. Flight control system design ensures that the loss of one hydraulic system will not prevent the operation of any control surface. Furthermore, should two hydraulic systems be lost, the remaining hydraulic system is sufficient to maintain safe aircraft control. Protection against cable jam/failure or PCU jam/failure is also provided for each axis. Gust damping is provided for all three sets of primary flight controls. When the aircraft is parked and the hydraulic systems are unpressurized, built-in valves in the aileron, elevator and rudder PCUs protect against rapid flight control surface movement. Components and Operation Ailerons Lateral (roll) control is provided by ailerons. Two separate control paths are provided from the pilot’s and copilot’s control wheels. The pilot’s side controls the left aileron and the copilot’s side controls the right aileron. Movement of both pilot’s and copilot’s controls is simultaneous when the controls are interconnected (Normal operation). Rotating either control wheel activates, via cables and pulleys, the PCUs (actuators) for the ailerons. Two actuators are used for each aileron. The left aileron PCUs use hydraulic pressure from systems 1 and 3, and the right aileron PCUs use hydraulic systems 2 and 3. A position transmitter linked to each aileron provides visual indication of the aileron deflection on the EICAS FLIGHT CONTROLS synoptic page. Aileron Disconnect In the event of a control cable jam or PCU malfunction, the left and right sides of the aileron control circuit can be isolated by pulling the ROLL DISCONNECT handle on the center pedestal. This disengages a locking pin on the interconnecting torque tube to FLIGHT CONTROLS For Training Purposes Only May 03 10-3 P I LOT T R A I N I N G GU I D E isolate the failed circuit. The aileron on the operable circuit provides roll control at a reduced roll rate. The ROLL DISCONNECT handle can be reset at any time, locking the two control circuits together again. Roll Control - Schematic Figure 10-2 1 3 3 2 FLUTTER DAMPER FLUTTER DAMPER Aileron (Position to EICAS Flight Controls Page) Aileron TRIM ACTUATOR TRIM POSITION TO EICAS PRIMARY (SEE FIG 10-8) M ROLL DISC FLIGHT CONTROLS FLAPS 30 AIL AIL EICAS FLIGHT CONTROLS SYNOPTIC PAGE (SECONDARY DISPLAY) Aileron Position Indicator PCU Valve Jam Symbol AUTOPILOT SERVO COMMANDS P604_10_002 I/C OFF R/T NOSEDN NOSEUP AP SC SYNCI/C OFF R/T NOSEDN NOSEUP AP SC SYNC L W D R W D AIL TRIM ROLL DISC FLIGHT CONTROLS 10-4 For Training Purposes Only Sept 04 P I LOT T R A I N I N G GU I D E Aileron Power Control Unit Protection If a PCU is malfunctioning, a failure detection sensor will cause the EICAS to display a PCU Valve Jam symbol on the Flight Controls synoptic page (an amber half-circle above the aileron outline), and an amber AILERON PCU caution EICAS message to appear. Two sets of shear rivets on each aileron PCU provide additional protection against internal PCU linkage jams. If the linkage to one cylinder jams, the pilot can overpower the jammed condition, which will shear the rivets on that side and allow the other cylinder to operate the aileron. Flutter Damper A flutter damper is installed on each aileron. This prevents control surface flutter in flight in the event of a complete loss of hydraulic fluid at the PCU. A breakaway link provides jam protection in the case of flutter damper seizure. FLIGHT CONTROLS For Training Purposes Only May 03 10-5 P I LOT T R A I N I N G GU I D E Page Intentionally Left Blank FLIGHT CONTROLS 10-6 For Training Purposes Only Sept 04 P I LOT T R A I N I N G GU I D E Elevators Longitudinal (pitch) control is provided by elevators and supplemented by a movable horizontal stabilizer. Two separate control paths are provided through the pilot’s and copilot’s control columns. The pilot’s control column controls the left elevator and the copilot’s control column controls the right elevator. Movement of both pilot’s and copilot’s controls is simultaneous when the systems are interconnected (normal operations). Moving either control column activates, via cables and pulleys, the PCUs (hydraulic actuators) for the elevators. Two actuators are used for each elevator. The left elevator PCUs use hydraulic pressure from systems 1 and 3, and the right PCUs use systems 2 and 3. A position transmitter linked to each elevator provides visual indication of the elevator deflection on the EICAS FLIGHT CONTROLS synoptic page. If a differential of greater than 5° between each elevator position exists, an ELEVATOR SPLIT caution EICAS message will appear. Within the Elevator control mechanism, a stick shaker and stick pusher system can be activated via the Stall Protection System (SPS). The SPS is covered later in this chapter. Pitch Disconnect In the event of a control cable jam, or elevator system malfunction, the left and right elevator control circuits can be isolated by pulling the PITCH DISC handle on the center pedestal. This provides reduced pitch authority through the one elevator on the operable circuit. The PITCH DISC handle can be reset at any time, locking the two control circuits together again. Elevator PCU Protection An elevator PCU jam or failure can be overcome by integrated jam-tolerant input rods. These rods collapse or expand in the event of both PCUs on one side having no hydraulic pressure, and enable operation of the opposite side elevator. If one of the pair of on-side PCU control valves jams, the jam-tolerant input rod will allow operation of the adjacent PCU control valve. Flutter Dampers Two flutter dampers are installed on each elevator. These are identical in design and function to those installed on the ailerons. FLIGHT CONTROLS For Training Purposes Only May 03 10-7 P I LOT T R A I N I N G GU I D E Pitch Control - Schematic Figure 10-3 1 3 3 2 Artificial Feel According to Horizontal Stabilizer Position Elevator Flutter Dampers 2 Each Elevator Horizontal Stabilizer 0° to -9° PITCH DISC STICK SHAKER STICK SHAKER STICK PUSHER STALL PROTECTION SYSTEM STALL PROTECTION SYSTEM RUDDER ELEV ELEV EICAS FLIGHT CONTROLS SYNOPTIC PAGE (SECONDARY DISPLAY) Elevator Position Scale Autopilot Servo Commands P604_10_003 I/C OFF R/T NOSEDN NOSE UP AP SC SYNC I/C OFF R/T NOSEDN NOSE UP AP SC SYNC P I T C H D I S C FLIGHT CONTROLS 10-8 For Training Purposes Only Sept 04 P I LOT T R A I N I N G GU I D E Rudder Yaw control is provided by a hydraulically actuated rudder hinged on the rear spar of the vertical stabilizer. Two separate mechanical control paths are provided from the rudder pedals to three independent PCUs. Each PCU is powered by a separate hydraulic system. A position transmitter provides visual indication of rudder deflection on the EICAS flight control synoptic page. Both rudder pedal control systems have an anti-jam breakout mechanism. In the event of a jammed rudder control on one side, both pilot and copilot rudder pedals are capable of operating the remaining control system. Additional force on the rudder pedals is required to bypass the inoperative side, allowing rudder operation. A two-channel Yaw Damper system is installed and supplies small rudder corrections in response to reference signals from the IRUs through the FCCs. This is considered a function of the Automated Flight Control System (AFCS) system. Refer to Chapter 4 Automatic Flight Control System for additional information. FLIGHT CONTROLS For Training Purposes Only May 03 10-9 P I LOT T R A I N I N G GU I D E Yaw Control - Schematic Figure 10-4 ENGAGE YAW DAMPER DISC YD 1 YD 2 1 2 3 INTEGRATED AVIONICS PROCESSOR SYSTEM FCC 1 FCC 2 LOAD LIMITER RUDDER TRIM ACTUATOR YAW DAMPER ACTUATOR DC BUS 1 FORWARD QUADRANT WITH ANTI-JAM/ BREAKOUT RUDDER ELEV ELEV EICAS FLIGHT CONTROLS SYNOPTIC PAGE (SECONDARY DISPLAY) P604_10_004 Rudder Position Indicator NL RUD TRIM NR FLIGHT CONTROLS 10-10 For Training Purposes Only Sept 04 P I LOT T R A I N I N G GU I D E Secondary Flight Controls Description The secondary flight controls include the horizontal stabilizer, inboard and outboard flaps, flight and ground spoilers, and the associated trim systems. The horizontal stabilizer trim is electrically actuated via a jackscrew. Flaps are electrically powered and driven by flex cables and ballscrew actuators. Spoilers are hydraulically powered. Trim about all three axes is electrically controlled from the cockpit. Components and Operation Horizontal Stabilizer Trim Pitch trim is accomplished by varying the angle of incidence of the horizontal stabilizer. The Horizontal Stabilizer Trim Control Unit (HSTCU) commands the actuation of the stabilizer leading edge with a jackscrew driven by two electric motors through a range of 0° to -9° at specific rates of movement. The HSTCU receives inputs from the pilot’s and copilot’s control wheel pitch trim switches, the autopilot, and the Mach Trim System. The HSTCU has two channels that are engaged by the CH 1 and CH 2 switch/lights on the STAB TRIM panel on the center pedestal. Normally, with both channels engaged, CH 1 is in command with CH 2 in standby. Operation of the horizontal stabilizer is continuously monitored by the HSTCU. In the event of a single-channel failure, the STAB CH 1(2) INOP status EICAS message will appear, and the remaining channel will provide control. If both channels fail, the STAB TRIM caution EICAS message appears, and stabilizer trim becomes inoperative. Horizontal stabilizer trim position is displayed on the EICAS primary page and the FLIGHT CONTROLS synoptic page. The normal trim setting for takeoff (-3 to -6 degrees) is depicted on the indicator as a green band. If stabilizer trim is not set in this range with the aircraft in the takeoff mode, a CONFIG STAB warning EICAS message will be displayed, and an aural “CONFIG TRIM” will sound. FLIGHT CONTROLS For Training Purposes Only May 03 10-11 P I LOT T R A I N I N G GU I D E Stab Trim Panel Figure 10-5 Stab Trim Indications Figure 10-6 Horizontal Stabilizer Trim Priority The stabilizer trim can be operated manually with the pilot’s and copilot’s control wheel pitch trim switches or automatically with the autopilot or the Mach Trim system. The order of priority and rate of movement are as follows: 1. Pilot Manual Trim - The pilot’s control wheel pitch trim switch is highest in the order of priority. The stabilizer rate of movement is 0.5°/sec. 2. Copilot Manual Trim - The copilot’s control wheel pitch trim switch is next highest in the order of priority. The stabilizer rate of movement is 0.5°/sec. 3. Autopilot Trim - The stabilizer rate of movement is 0.1°/sec. If a flap selection is made with the autopilot engaged, the rate of movement reverts to the higher rate of 0.5°/sec. during flap transition. 4. Mach Trim - The Mach Trim is lowest in the order of priority. The stabilizer rate of movement is between 0.03° and 0.06°/sec. STAB TRIM MACH TRIM ENGAGE ENGAGE/ DISENGAGE CH 1 CH 2 INOP P604_10_014 Horizontal Stabilizer Trim Gauge DN DN DN - GEAR - - FLAPS - STAB - TRIM - 20 NU ND 4.0 RUDDER AIL LWD RWD NL NR P604_10_015 FLIGHT CONTROLS 10-12 For Training Purposes Only Sept 04 P I LOT T R A I N I N G GU I D E Horizontal Stabilizer Trim Clacker If the horizontal stabilizer is in motion at a rate of more than 0.3°/sec. for more than 3 seconds, a clacker (“drumroll” sound) is activated to alert the pilot of a possible horizontal stabilizer trim runaway condition. In the event of a runaway stabilizer trim condition, both channels can be quickly disconnected by pressing the STAB TRIM DISC button on either outboard control wheel horn. Mach Trim The Mach Trim system, when engaged and active, compensates for the rearward shift of the aerodynamic center of pressure as Mach number increases. The Mach Trim system schedules inputs to the HSTCU to command movement of the horizontal stabilizer when hand-flying at speeds greater than Mach 0.4. Aileron Trim Aileron trim is accomplished by activation of the AIL TRIM switches on the center pedestal. Actuation of both switches provides arming and directional signals which bias the control circuits to actuate the PCUs and deflect the ailerons. Actuation of the aileron trim will cause the control wheels to deflect in the direction of trim input. Aileron trim position is indicated on the EICAS primary page. Rudder Trim Rudder trim is accomplished by turning the RUD TRIM switch. Rudder trim input is applied by the trim actuator into the yaw damper/trim mixer assembly and will supplement the primary rudder input as applicable. Actuation of the rudder trim does not cause rudder pedal deflection. The rudder trim position is indicated on the EICAS primary page. FLIGHT CONTROLS For Training Purposes Only May 03 10-13 P I LOT T R A I N I N G GU I D E Aileron/Rudder Trim Panel Figure 10-7 Aileron/Rudder Trim Indications Figure 10-8 L W D R W D AIL TRIM NL RUD TRIM NR P604_10_016 DN DN DN - GEAR - - FLAPS - STAB - TRIM - 20 NU ND 4.0 RUDDER AIL LWD RWD NL NR P604_10_017 Aileron Trim Gauge Rudder Trim Gauge FLIGHT CONTROLS 10-14 For Training Purposes Only Sept 04 P I LOT T R A I N I N G GU I D E Flaps Two double-slotted flap panels (inboard and outboard) are externally hinged on the trailing edge of each wing. A flap lever, located on the center pedestal, sends a signal to the Flap Control Unit (FCU) to initiate flap movement. When the FCU commands a change in flap position, the flap brakes are released, and two AC-powered motors mounted on a flap gearbox are energized. The gearbox rotates flex shafts which move the flap ballscrew actuators, extending or retracting the flaps. When the desired setting is reached, the motors are deenergized and the flap brakes are applied. The flaps are mechanically interconnected for simultaneous movement of the inboard and outboard flap sections. The flaps may be set to one of four positions: 0, 20, 30, and 45 degrees. A flap gate is incorporated within the flap lever 20-degree detent. This minimizes the possibility of accidental flap retraction to 0 degrees during a go-around procedure. Flap position is displayed on the EICAS Primary Page and the Flight Controls Synoptic Page in both analog (colored bar) and digital formats. The indications on the EICAS Primary Page are in view only if the flaps are extended, or if the landing gear is not up and locked. Flap position and condition is continuously monitored by the Flap Control Unit. In the event of failure or overheat of a single flap motor (indicated by a FLAPS MOTOR OVHT status EICAS message) the remaining motor can operate the flaps at half speed. Complete failure of the flap system, including an asymmetry of > 2.75°, will generate a FLAPS FAIL caution EICAS message as well an amber symbol on the EICAS FLIGHT CONTROLS synoptic page. If the flaps are not set at 20° with the aircraft in takeoff mode, a CONFIG FLAPS warning EICAS message and aural warning will be displayed/sounded. Maximum Flap Speeds To prevent damage, maximum indicated airspeeds for each flap setting must not be exceeded. These are placarded on the instrument panel. (See Airplane Flight Manual for current airspeeds.) Flap Setting Maximum Airspeed 20 degrees 231 kias 30 degrees 197 kias 45 degrees 189 kias NOTE FLIGHT CONTROLS For Training Purposes Only Sept 04 10-15 P I LOT T R A I N I N G GU I D E Flap Schematic Figure 10-9 FLAP CONTROL UNIT MOTOR RELAYS MOTOR RELAYS FLAP POSITION DIFF. CLUTCH GEAR MOTOR 1 & BRAKE MOTOR 2 & BRAKE TORQUE LIMITER TORQUE LIMITER OVHT OVHT AC BUS 1 AC BUS 2 RPM RPM DET. BRAKE DET. BRAKE DC BUS 1 DC BUS 2 FLAP MOTOR OVHT FLAP MOTOR OVHT FLAP FAIL CONFIG FLAPS INPUTS FROM OTHER SYSTEMS MASTER WARNING “CONFIG FLAPS” EICAS DCU EICAS EICAS DCU DCU EICAS FLIGHT CONTROLS SYNOPTIC PAGE (SECONDARY DISPLAY) Flap Position Indicator P604_10_005 0 20 30 45 0 20 30 45 FLAPS FLIGHT CONTROLS AIL RUDDER ELEV ELEV AIL FLAPS MOTOR OVERHEAT FLAPS 30 FLIGHT CONTROLS 10-16 For Training Purposes Only Sept 04 P I LOT T R A I N I N G GU I D E Flight Spoilers These provide lift dumping and speed control when airborne, and reduce ground roll during landing and rejected takeoffs. Each flight spoiler panel is hydraulically operated by two identical PCUs, powered by hydraulic systems 1 and 2. The flight spoilers are mechanically controlled by the flight spoiler control lever on the center pedestal and can be deployed up to a maximum of 40° in flight or on the ground. The flight spoiler control lever travels through nine detents, allowing the pilot to select variable amounts of flight spoiler deployment. Spoiler position is indicated on both the EICAS Status and FLIGHT CONTROLS synoptic pages, using white arrows which move upward toward lines, indicating relative extension (for the flight spoilers only), and full extension (for both flight and ground spoilers). When the flight and ground spoilers are fully retracted, all EICAS spoiler icons and position arrows disappear. An amber FLT SPLR DEPLOY caution EICAS message appears if the flight spoilers are deployed in flight and: • the aircraft radio altitude between 10 and 300 feet AGL, or • the left or right engine N1 is greater than 79%, or • if radio altitude is not available, at any time the landing gear is extended If the flight spoilers are not stowed with the aircraft in takeoff mode, a CONFIG SPOILERS warning EICAS message and aural warning will be displayed/sounded. 20° Detent Mechanism A 20° detent mechanism prevents asymmetrical deployment of the flight spoilers in the event of a disconnected input linkage. The PCU control valves are spring-loaded retracted, but the detent mechanism will apply force to hold a mid-position if the spoiler has been deployed to greater than 20°. When on the ground with hydraulic pressure available, a sensor on each detent mechanism will generate a FLT SPLRS caution EICAS message, and cause the appropriate flight spoiler outline to turn amber on the Flight Control Synoptic page, if the spoiler position does not correspond to the detent position. FLIGHT CONTROLS For Training Purposes Only May 03 10-17 P I LOT T R A I N I N G GU I D E Flight and Ground Spoilers - Schematic Figure 10-10 FLIGHT CONTROLS FLAPS 30 AIL AIL EICAS FLIGHT CONTROLS SYNOPTIC PAGE (SECONDARY DISPLAY) Flight Spoiler Position Indicator 1 2 1 2 FLIGHT SPOILER FLIGHT SPOILER GROUND SPOILER GROUND SPOILER PROXIMITY SENSOR ELECTRONIC UNIT PROXIMITY SENSOR ELECTRONIC UNIT SUBSYSTEM A SUBSYSTEM B GROUND SPOILER SOLENOID VALVE 1 BATT BUS BATT BUS SPLR UP SPLR UP LH THROTTLE AT IDLE RH THROTTLE AT IDLE LH THROTTLE ABOVE MIN TAKEOFF RH THROTTLE ABOVE MIN TAKEOFF DC BUS 2 DC BUS 1 SYSTEM INPUTS 1 MECHANICAL INPUT P604_10_006 Ground Spoiler Indicator L ARMED EMER STOW OFF R ARMED OFF GND SPOILERS THRUST REVERSER ARM AUTO DISARM UNLK UNLK L R FLIGHT SPOILER 1/4 0 RETRACT 1/2 3/4 MAX FLIGHT CONTROLS 10-18 For Training Purposes Only Sept 04 P I LOT T R A I N I N G GU I D E Ground Spoilers The inboard spoiler panels on each wing are the ground spoilers. The ground spoilers have only two positions: retracted or fully deployed to 45°. A single actuator powered by hydraulic system 1 operates each ground spoiler. After touchdown or during a rejected takeoff, the ground spoilers extend to dump lift and increase drag to assist in aircraft braking. Ground spoiler deployment is normally automatic but can be activated manually by the pilot. In the automatic or manual modes, arming, deployment and retraction is controlled by the Proximity Sensor Electronic Unit (PSEU). The PSEU monitors inputs from the following: • ground spoiler arming switch • thrust lever position microswitches • ground spoiler surface position • flight spoiler lever position switch • anti-skid control unit (wheel speed) In the event of a malfunction or failure of the automatic arming and disarming logic, the ground spoiler system may be manually armed or disarmed through the GND SPOILERS panel, located on the center pedestal. Spoiler position is indicated on both the EICAS Status and FLIGHT CONTROLS synoptic pages, using white arrows which move upward toward lines, indicating relative extension (for the flight spoilers only), and full extension (for both flight and ground spoilers). When the flight and ground spoilers are fully retracted, all EICAS spoiler icons and position arrows disappear. Ground Spoiler Arming Logic The ground spoiler circuit must be armed before deployment can take place. The ground spoilers are armed or disarmed by the three-position GND SPOILERS switch, located on the center pedestal next to the Flight Spoiler Control Lever. The ground spoiler system can be armed either automatically or manually as follows: FLIGHT CONTROLS For Training Purposes Only Sept 04 10-19 P I LOT T R A I N I N G GU I D E Ground Spoilers Arming Logic Figure 10-11 P604_10_018 Automatic Arming • GND SPOILERS Switch in the AUTO position, and • L and R Thrust Min Takeoff Setting, and • Wheel Speed > 16 kts > Manual Arming • GND SPOILERS Switch in the AUTO position, and • Flight Spoiler Lever > 1/4 detent OR • GND SPOILERS Switch in the ARM position Deploy Logic • L and R Thrust Lever at IDLE AND • Main Landing Gear Weight-on-Wheels OR • Wheel Speed > 16 kts Automatic Retract • L or R Thrust Lever > IDLE (goaround), OR • L or R Thrust Lever < Min required for Takeoff, and • Inboard and Outboard Wheel Speed < 16 kts, and • Deploy Logic (airplane on the ground for at least 3 seconds) Manual Retract • GND SPOILERS Switch in the DISARM position OR • Flight Spoiler Lever < 1/4 detent (if spoilers were manually armed using the Flight Spoiler Lever and the GND SPOILERS Switch at AUTO) L ARMED EMER STOW OFF R ARMED OFF GND SPOILERS THRUST REVERSER ARM AUTO DISARM UNLK UNLK L R GROUND SPOILER PANEL FLIGHT CONTROLS 10-20 For Training Purposes Only Sept 04 P I LOT T R A I N I N G GU I D E Stall Protection System The Stall Protection System (SPS) provides the flight crew with aural, visual and tactile (stick shaker) indications of an impending stall and, if no corrective action is taken, will activate a stick pusher to prevent the aircraft from entering a full stall. A dual-channel SPS computer monitors the following inputs: • angle of attack - LH, RH Angle-of-Attack vanes • lateral acceleration - Inertial Reference System (IRS) • flap position • pressure altitude - Air Data Computers (ADCs) The SPS uses these inputs to continuously calculate Angle-of-Attack (AOA) trip points while in flight. The AOA trip points are biased with the lateral accelerometers (sideslip and skid), flap position and pressure altitude. As the trip point is approached, continuous ignition is activated. If the AOA continues to increase, the stick shaker activates and the autopilot disengages. If the AOA still continues to increase, the stick pusher activates, along with red flashing STALL and Master Warning lights on the glareshield and a warbler aural warning. The stick pusher only activates when the signals from both channels of the SPS computer are in agreement. The crew should initiate approved recovery techniques at the first indications of an impending stall (i.e., recognition of proximity of low-speed cue, at airframe buffet, at autoignition, or any time the stick shaker or pusher activates). In the event of an AOA increase rate greater than 1 degree per second, the SPS computer lowers the AOA trip points to activate the aural, visual and tactile indications at a lower AOA. This prevents the aircraft’s pitching momentum from carrying it through the stall warning/stick pusher sequence into the stall. Stick Pusher Disconnect The stick pusher subsystem is armed when both STALL PROT PUSHER switches, located on the pilot and copilot side panels, are ON. An acceleration switch will disconnect the stick pusher, to prevent an unusual attitude, if less than +0.5 ‘G’ is reached during pusher operation. The pusher may also be disabled momentarily by pushing the AP/SP DISC button on the pilot’s or copilot’s control wheels. This will disconnect the pusher only as long as either button is held in. In the event of a malfunction, the stick pusher may be deactivated by switching either STALL PROT NOTE FLIGHT CONTROLS For Training Purposes Only May 03 10-21 P I LOT T R A I N I N G GU I D E PUSHER switch to OFF (located on the side panels). To enable pusher operation, both switches must be returned to the ON position. Stall Protection System - Schematic Figure 10-12 SPS TEST INDICATOR SPS TEST INDICATOR STALL PROTECTION COMPUTER AOA TRANSDUCER LH (ANGLE OF ATTACK) AOA TRANSDUCER RH (ANGLE OF ATTACK) ADC 1 (ALTITUDE) ADC 2 (ALTITUDE) FLAP POSITION LH FLAP POSITION RH LATERAL ACCELERATION LATERAL ACCELERATION WOW 1 WOW 2 WOW FAIL CB4-C5 0 STALL PROT RH CHAN CB1-N4 0 STALL PROT STICK PUSH 28 VDC ESS BUS BATT BUS CB1-N5 0 STALL PROT LH CHAN 28 VDC ESS BUS PILOT'S SIDE PANEL COPILOT'S SIDE PANEL RH CONTROL COLUMN OFF ON G-SWITCH STICK PUSHER STICK SHAKER RH STICK SHAKER LH AUTOIGNITION (CONTINUOUS) AP/SP DISCONNECT G-SWITCH TEST CHANNEL 1 CHANNEL 2 AUTOIGNITION SIGNAL 1 AUTOIGNITION SIGNAL 2 AUTOPILOT DISCONNECT 1 AUTOPILOT DISCONNECT 2 SHAKER SIGNAL HORN SIGNAL PUSH SIGNAL HORN SIGNAL SHAKER SIGNAL PUSH SIGNAL STALL PROTECTION TEST INDICATOR STALL PROTECTION TEST INDICATOR TEST IN TEST IN WARBLER WARBLER DCU DCU STALL STALL FLASHER FLASHER TEST #2 TEST #1 WOW WOW P604_10_007 I/C OFF R/T NOSEDN NOSEUP AP SC SYNC STALL PROT PUSHER ON OFF STALL PROT PUSHER ON OFF FLIGHT CONTROLS 10-22 For Training Purposes Only Sept 04 P I LOT T R A I N I N G GU I D E The stick shaker is always armed. The STALL PROT PUSHER switches affect only the stick pusher function. SPS Ground Testing Preflight testing of the system is accomplished by SPS TEST switches on the Miscellaneous Test Panel located on the center pedestal. Either the L (R) SPS TEST switch will cause the system to progressively sweep through the AOA range from no stall to full stall, as indicated on the SPS Test Indicator, activating ignition (blue arc) and shaker/autopilot disconnect (yellow arc). This is followed by red flashing STALL lights on the glareshield and an aural warbler warning. If both switches are activated simultaneously, the stick pusher will activate (red arc). Pusher disconnects can then be tested by pushing, in sequence, the pilot’s AP/SP DISC, the copilot’s AP/SP DISC and the G-switch. See the Airplane Flight Manual for full testing procedures. Ignition is activated during the test and may pose a hazard in enclosed areas. NOTE CAUTION FLIGHT CONTROLS For Training Purposes Only May 03 10-23 P I LOT T R A I N I N G GU I D E Controls and Indicators Primary and secondary flight controls and indicators are accessible from both pilot seats. Warning, caution, advisory, and status messages are presented on the Primary Flight Display (PFD) and primary and status pages of the Engine Indication and Crew Alerting System (EICAS). FLIGHT CONTROLS 10-24 For Training Purposes Only May 03 P I LOT T R A I N I N G GU I D E Primary Flight Controls Pitch, Roll and Yaw Controls Figure 10-13 ROLL DISC P I T C H D I S C I/C OFF R/T NOSEDN NOSE UP AP SC SYNC Pitch Disconnect Handle Separates left and right elevator inputs Roll Disconnect Handle Separates left and right aileron inputs COPILOT'S CONTROL WHEEL (PILOT'S OPPOSITE) Rudder Pedals Incorporate an anti-jam/ breakout mechanism. Mechanism activated by applying additional force on rudder pedal. EICAS FLIGHT CONTROLS SYNOPTIC PAGE (SECONDARY DISPLAY) FLIGHT CONTROLS FLAPS 30 FLAPS MOTOR OVERHEAT AIL AIL RUDDER YAW DAMPER STAB TRIM CH1 INOP ELEV ELEV P604_10_009 FLIGHT CONTROLS For Training Purposes Only May 03 10-25 P I LOT T R A I N I N G GU I D E Stab Trim, Aileron Trim, Rudder Trim TRIM Controls Figure 10-14 STAB TRIM MACH TRIM ENGAGE ENGAGE/ DISENGAGE CH 1 CH 2 INOP L W D R W D AIL TRIM NL RUD TRIM NR AILERON/RUDDER TRIM CONTROL PANEL STABILIZER TRIM & MACH TRIM CONTROL PANEL COPILOT'S CONTROL WHEEL (MIRROR OF PILOTS) P604_10_010 AILERON TRIM Switches (springloaded to center) LWD - Commands left wing down aileron trim RWD - Commands right wing down aileron trim Note: Both switches must be pushed fully left or right to activate trim. RUDDER TRIM Switch (springloaded to center) NL - Commands nose left rudder trim NR - Commands nose right rudder trim Stabilizer Trim Switches (spring-loaded to center) NOSE UP - Activates nose up trim NOSE DN - Activates nose down trim Note: Both switches must be pushed fully up or down to activate trim. Stabilizer Trim Disconnect Switch (momentary-action) Press - Disconnects stabilizer trim (Both CH 1 and CH 2) NOTE: Mach trim function will also disengage when switch is actuated MACH TRIM Switch/Light (momentary-action) INOP Light Press - Alternately engages or disengages the Mach trim function Illuminated - Indicates Mach trim function is inoperative/disengaged STAB TRIM CH1, CH2 Switches (momentary-action) Press - Engages respective channel of the Horizontal Stabilizer Trim Control Unit (HSTCU) I/C OFF R/T NOSE DN NOSE UP AP SC SYNC FLIGHT CONTROLS 10-26 For Training Purposes Only May 03 P I LOT T R A I N I N G GU I D E Flaps, Spoilers Flap and Spoiler Controls Figure 10-15 0 20 30 45 0 20 30 45 FLAPS GND SPOILERS ARM AUTO DISARM FLIGHT SPOILER 1/4 0 RETRACT 1/2 3/4 MAX FLIGHT SPOILER LEVER FLAP SELECTOR LEVER FLAP Selector Lever Sets flap position 0° - Taxiing, flight 20° - Takeoff 30° - Approach 45° - Landing THRUST REVERSER/ SPOILER CONTROL PANEL P604_10_011 GND SPOILERS Switch ARM AUTO DISARM - Manually arms the ground spoilers for deployment - Arms the ground spoilers for automatic deployment - Disarms the ground spoilers in the event of an inadvertent deployment or failure of automatic system FLIGHT SPOILER Lever - Positions flight spoilers to selected detent - 0, 1/4, 1/2, 3/4, MAX detents : Four additional detented positions are possible between the above indicated positions. NOTE FLIGHT CONTROLS For Training Purposes Only May 03 10-27 P I LOT T R A I N I N G GU I D E Stall Protection System Stall Protection System Figure 10-16 TEST TEST TEST TEST TEST WARN TEST FIRE DET 1 2 APU BOTTLE FAIL L R G SWITCH SPS TEST FIREX MONITOR AURAL WARN TEST LAMP TEST OVSP TEST 1 2 1 2 1 2 ENG BOTTLE STALL PROT PUSHER ON OFF SPS TEST INDICATOR STALL PROT PUSHER ON OFF SPS TEST INDICATOR LH ENG FIRE PUSH GPWS TERR INHB MASTER WARNING BOTTLE 1 ARMED PUSH TO DISCH STALL MASTER CAUTION PULL UP GND PROX ATS N2 SYNC ATS N1 TO FAIL ATS N1 TO FAIL APU FIRE PUSH RH ENG FIRE PUSH GPWS TERR INHB MASTER BOTTLE 2 WARNING ARMED PUSH TO DISCH BOTTLE ARMED PUSH TO DISCH STALL MASTER CAUTION PULL UP GND PROX STALL PROT PUSHER Switch ON - Stick pusher is armed OFF - Stick pusher is disabled NOTE: Both pilot's and copilot's PUSHER switches must be ON to arm the stick pusher. SPS TEST Indicator Blue Sector - Continuous ignition is activated Yellow Sector - Stick shaker operates Red Sector - Aural stall warning and stick pusher operates STALL PROTECTION PANEL (PILOT'S SIDE) STALL PROTECTION PANEL (COPILOT'S SIDE) I/C OFF R/T NOSE DN NOSE UP AP SC SYNC PILOT’S SIDE COPILOT’S SIDE STALL Lights Illuminated Flashing - Indicate AOA has reached stick pusher trip point (during flight or an SPS test) COPILOT’S CONTROL WHEEL (MIRROR OF PILOT’S) AP/SP (Autopilot/Stick Pusher Disconnect) Button Press - Disengages autopilot and deactivates stick pusher NOTE: When released, stick pusher system is immediately reactivated. P604_10_012 L and R SPS TEST Switches (spring-loaded off) TEST - Tests respective channel of Stall Protection System (SPS) Computer SPS TEST G Switch (spring-loaded off) TEST - Deactivates stick pusher during SPS preflight test MISCELLANEOUS TEST PANEL FLIGHT CONTROLS 10-28 For Training Purposes Only May 03 P I LOT T R A I N I N G GU I D E EICAS Flight Controls Indications (Ground Spoilers) Figure 10-17 P604_10_019 FLIGHT CONTROLS AIL AIL FLAPS 30 Description Symbol Condition Ground spoilers are fully extended Note: Indicators are not displayed when ground spoilers are retracted or input data is invalid. Ground Spoiler Position Indicators SPOILERS EICAS STATUS PAGE EICAS FLIGHT CONTROLS SYNOPTIC PAGE (SECONDARY DISPLAY) Maximum Spoiler Deployment Mark Ground Spoiler Position Indicators Ground Spoiler Outline Respective hydraulic manifold and PSEU are operative. Respective hydraulic manifold and PSEU are inoperative. Invalid data Ground Spoiler Outline FLIGHT CONTROLS For Training Purposes Only May 03 10-29 P I LOT T R A I N I N G GU I D E EICAS Flight Controls Indications (Flight Spoilers) Figure 10-18 P604_10_020 FLIGHT CONTROLS AIL AIL FLAPS MOTOR OVERHEAT FLAPS 30 Description Symbol Condition Indicates relative position of respective spoiler Note: Indicators are not displayed when respective spoiler is retracted or input data is invalid Flight Spoiler Position Indicators SPOILERS EICAS STATUS PAGE EICAS FLIGHT CONTROLS SYNOPTIC PAGE (SECONDARY DISPLAY) Maximum Spoiler Deployment Mark Mid Spoiler Deployment Mark Flight Spoiler Outline Respective flight spoiler detent mechanism and associated surface position are valid Abnormal condition of flight spoiler detent mechanism and associated surface position Invalid data Flight Spoiler Outline Flight Spoiler Position Indicator FLIGHT CONTROLS 10-30 For Training Purposes Only May 03 P I LOT T R A I N I N G GU I D E EICAS Flight Controls Indications (Flaps) Figure 10-19 P604_10_021 FLIGHT CONTROLS AIL AIL FLAPS MOTOR OVERHEAT FLAPS 30 Description Symbol Condition Indicates in degrees, the position of the LH an RH flaps Notes: The flap information is removed from display whenever the landing gear and flaps are fully retracted Flap Position Readout EICAS PRIMARY PAGE EICAS FLIGHT CONTROLS SYNOPTIC PAGE (SECONDARY DISPLAY) Flap Position Readout Flaps are operating normally Flaps are operating at half speed due to a single flap motor overheat Invalid data Flap Outline Flap Outline DN DN DN - GEAR - - FLAPS - C ALT STAB RATE - TRIM - P 3200 200 -0.5 30 NU ND 4.0 RUDDER AIL LWD RWD NL NR Flaps failed or both flap motors overheated Invalid data FLAPS 30 FLAPS _ _ FLIGHT CONTROLS For Training Purposes Only May 03 10-31 P I LOT T R A I N I N G GU I D E EICAS Flight Controls Indications (Trim) Figure 10-20 P604_10_022 Description Symbol Condition Stabilizer position is within the takeoff trim range (3° to 8°) NU - Nose Up (Top tick mark - 9°) ND - Nose Down (Bottom tick mark - 0°) Stabilizer Trim Pointer and Readout Stabilizer position is outside of the takeoff trim range Aileron Trim Pointer Stabilizer Trim Scale Rudder Trim Pointer Indicates aileron trim displacement LWD - Left Wing Down RWD - Right Wing Down Indicates rudder trim displacement NL - Nose Left NR- Nose Right STAB NU ND 4.0 STAB NU ND 4.0 AIL LWD RWD RUDDER NL NR Aileron Trim Pointer Rudder Trim Pointer EICAS PRIMARY PAGE DN DN DN - GEAR - - FLAPS - C ALT STAB RATE - TRIM - P 3200 200 -0.5 20 NU ND 4.0 RUDDER AIL LWD RWD NL NR Stabilizer Trim Pointer and Readout FLIGHT CONTROLS 10-32 For Training Purposes Only May 03 P I LOT T R A I N I N G GU I D E EICAS Flight Controls Indications (Aileron, Elevator, Rudder) Figure 10-21 FLIGHT CONTROLS AIL RUDDER ELEV ELEV AIL FLAPS MOTOR OVERHEAT FLAPS 30 P604_10_023 Description Symbol Condition Indicates relative position of respective aileron Top tick mark – 20.8° Center tick mark – 0° Bottom tick mark – -21.3° Aileron Position Indicator EICAS FLIGHT CONTROLS SYNOPTIC PAGE (SECONDARY DISPLAY) Aileron PCU Valve Jam Mechanical jam of PCU control valve is detected Symbol PCU Valve Jam Symbol Elevator Position Indicator Aileron Position Indicator Aileron Outline Elevator Outline Elevator Position Indicator Rudder Position Indicator AIL AIL ELEV ELEV RUDDER Indicates relative position of respective aileron Top tick mark – 23.6° Center tick mark – 0° Bottom tick mark – -18.4° Indicates relative position of rudder Left tick mark – - 25° Center tick mark – 0° Right tick mark – 25° FLIGHT CONTROLS For Training Purposes Only May 03 10-33 P I LOT T R A I N I N G GU I D E EICAS Messages MESSAGE MEANING AURAL WARNING (IF ANY) CONFIG FLAPS Flaps are not set at 20° with the aircraft in takeoff mode. “CONFIG FLAPS” CONFIG SPOILERS Spoilers are not stowed with the aircraft in takeoff mode. “CONFIG SPOILERS” CONFIG STAB Pitch trim is not set in the green band with the aircraft in takeoff mode. “CONFIG TRIM” AILERON PCU One or both ailerons have a jammed power control unit. ALT COMP FAIL The left or right altitude compensation circuit of the stall protection computer has failed. ELEVATOR SPLIT Indicates > 5 degrees difference between left and right elevator surface position. FLAPS FAIL Either both flap motors are overheated or the flaps have failed. FLT SPLR DEPLOY Flight spoilers are deployed with either the radio altitude between 10’ - 300’ or engine N1 > 79% or, with the radio altimeter inoperative, the gear is extended. FLT SPLRS Left and/or right detent mechanism has failed (displays on ground only, unless there is a loss of system 1 and 2 hydraulic pressure). GND SPLRS Ground spoilers are inoperative. GND SPLRS DEPLOY Ground spoilers are not stowed and the radio altitude is greater than 10’. GND SPLRS NOT ARMED The ground spoilers are not armed with the aircraft in either takeoff mode or in the landing mode. MACH TRIM Mach trim is disengaged or failed. STAB TRIM Both pitch trim channels are off or failed. STALL FAIL One or both channels of the stall protection system have failed, resulting in the stick pusher system becoming inoperative. AILERON MON OK All four aileron PCU failure detection sensors are functioning properly. T/0 CONFIG OK With engines running, and on ground, the aircraft is in takeoff configuration. FLAPS MOTOR OVHT One of the flap motors is hot and has shut down. STAB CH 1 INOP The respective pitch trim channel is off or failed, and the other channel is engaged and STAB CH 2 INOP not failed. EICAS Messages Table 10-1 10-34 For Training Purposes Only May 03 FLIGHT CONTROLS P I LOT T R A I N I N G GU I D E Page Intentionally Left Blank

f214216709 发表于 2010-5-18 10:31:55

非常感谢楼主哦

buaawu 发表于 2016-3-22 14:28:36

谢谢啦多谢

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