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EICAS Flight Controls Indications (Flight Spoilers)
Figure 10−10−18
FLIGHT CONTROLS
Description
Vol. 2 10−10−26
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
CONTROLS AND INDICATORS (CONT'D)
EICAS Flight Controls Indications (Flaps)
Figure 10−10−19
FLIGHT CONTROLS
Description
Vol. 2 10−10−27
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
CONTROLS AND INDICATORS (CONT'D)
EICAS Flight Controls Indications (Trim)
Figure 10−10−20
FLIGHT CONTROLS
Description
Vol. 2 10−10−28
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
CONTROLS AND INDICATORS (CONT'D)
EICAS Flight Controls Indications (Aileron, Elevator, Rudder)
Figure 10−10−21
FLIGHT CONTROLS
Description
Vol. 2 10−10−29
REV 76, Jul 17/09
CL−604 Operating Manual
PSP 604−6
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/O CONFIG OK With engines running, and on ground, the aircraft is in takeoff configuration.
FLAPS MOTOR OVHT One flap motor is hot and has shut down.
STAB CH 1 INOP The respective pitch trim channel is off or failed, and the other channel is
STAB CH 2 INOP engaged and not failed.
FLIGHT CONTROLS
Description
Vol. 2 10−10−30
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
POWER SUPPLY AND CIRCUIT BREAKER SUMMARY
SYSTEM SUB-SYSTEM CB NAME BUS BAR
CB
PANEL
CB LOCATION NOTES
Flight Controls
Flaps
FLAP MOTOR 1 AC BUS 1 1 B5
FLAP MOTOR 2 AC BUS 2 2 B5
FLAP CONT 1 DC BUS 1 1 F3
FLAP CONT 2 DC BUS 2 2 F3
Trims
RUD TRIM DC BUS 1 1 F5
AIL TRIM DC BUS 2 2 F5
Stall Protection
STALL PROT R CH DC ESS 4 C5
STALL PROT LH
CH
DC BATT 1
N5
STALL PROT
STICK PUSH
N4
Stabilizer Trim
STAB CH 1 HSTCU DC BUS 2 2 F8
STAB CH 2 HSTCU DC ESS 4 B8
STAB CH 1 HSTA AC BUS 2 2 C5
STAB CH 2 HSTA AC ESS 3 A5
Ground Spoilers GND SPLR
DC BUS 1 1 F4
DC BUS 2 2 F4
Position Indication
FLAP TRIM IND DC BATT 1 N6
SURF POS IND L AC ESS 3 D4
SURF POS IND R AC BUS 2 2 D4
FLIGHT CONTROLS
SUMMARY
Vol. 2 10−20−1
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
FLIGHT CONTROLS
SUMMARY
Vol. 2 10−20−2
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
THIS PAGE INTENTIONALLY LEFT BLANK
DESCRIPTION
General 11−10−1
Electronic Flight Instrument System (EFIS) 11−10−1
Components and Operations 11−10−1
EFIS Comparator Monitor 11−10−4
Air Data System 11−10−10
Pitot-Static System 11−10−11
Temperature-Sensing System 11−10−12
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庞巴迪挑战者604操作手册 Operating Manual 4(13)
