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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

非常感谢楼主哦

buaawu

谢谢啦  多谢