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steering actuator to turn the nose gear. Hydraulic pressure will move the rack, which in turn engages and rotates the pinion
gear on the steering cuff. Mechanical torque links transmit the movement of the steering cuff to the nose landing gear axle.
Nosewheel feedback is sent to the SCU from transducers mounted on the steering actuator. The SCU continuously monitors
the NWS. Fault detection results in steering system shutdown. Any faults detected are annunciated as CAS messages. When
the steering system is shutdown or disarmed, the SCU reverts the nosewheel steering to free-castering mode.
WARNING: - Prior to taxi, ensure that the nosewheel assembly is clear of personnel and towing equipment
before selecting the nosewheel steering to the on position.
The system is operable when:
- Left hydraulic system is pressurized
- Nose landing gear is down
- The locked and a weight-on-wheels signal is present
- NWS selected on
REV 1
LANDING GEAR
Volume 2 Flight Crew Operating Manual Sep 13/2004
15-01-16 CSP 100-6 REV 1
STEERING CONTROL SYSTEM
OFF
NWS
STEERING
ACTUATORS
NOSE WHEEL
ASSEMBLY
LEFT HYDRAULIC
SYSTEM
STEERING MAINFOLD
STEERING TO EICAS
CONTROL UNIT
WOW
NOSE LANDING
GEAR DOWN
AND LOCKED
PSEU
RUDDER PEDALS
NOSEWHEEL
STEERING SWITCH
STEERING HANDWHEEL
PILOT'S SIDE PANEL
P
O
S
I
T
I
O
N
S
E
N
S
O
R
S
CFO1501002_020
REV 1
LANDING GEAR
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 15-01-17
LANDING GEAR INDICATIONS
The EICAS landing gear indications provide the pilots increased situational awareness regarding the position and condition
of the landing gear.
LANDING GEAR DOWNLOCKED “SAFE”:
ONE OF THE TWO REDUNDANT DOWNLOCK SENSORS DETECTS THAT THE
GEAR IS DOWN AND LOCKED
LANDING GEAR UP:
UPLOCK SENSOR DETECTS GEAR UP AND BOTH DOWNLOCK
SENSORS DETECT GEAR NOT DOWNLOCKED
GEAR UP AND NO GEAR WARNING AND EITHER NO GEAR
DISAGREE OR GEAR DISAGREE WITH HANDLE UP
GEAR UP AND NO GEAR WARNING AND GEAR DISAGREE
AND GEAR HANDLE NOT UP
GEAR UP AND GEAR WARNING
LANDING GEAR IN TRANSIT:
UPLOCK AND DOWNLOCK SENSORS DETECT GEAR IS NOT LOCKED
GEAR IN TRANSIT AND NO GEAR DISAGREE AND NO GEAR WARNING
GEAR IN TRANSIT AND GEAR DISAGREE AND NO GEAR WARNING
GEAR IN TRANSIT AND GEAR WARNING
DATA FROM BOTH PSS SUBSYSTEMS NOT AVAILABLE OR INVALID
UP
UP
DN
UP
CFO1501002_021
REV 1
LANDING GEAR
Volume 2 Flight Crew Operating Manual Sep 13/2004
15-01-18 CSP 100-6 REV 1
CONTROLS AND INDICATIONS
DESCRIPTION
Flight deck controls activate normal gear extension and retraction, emergency extension, nosewheel steering, and warning
horn mute.
The EICAS presents indications of landing gear operation.
OFF OFF OFF
OFF
TAWS WARN
GS FLAPS TERRAIN
NWS
LANDING GEAR
UP
VLO 200
VLO 250 VLE 250
DN
CFO1501002_007
REV 1
LANDING GEAR
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 15-01-19
CONTROLS AND INDICATIONS (Cont)
LANDING GEAR (UP)
CFO1501002_031
HYDRAULIC PRESSURE (P)
HYDRAULIC RETURN (R)
HYDRAULIC BYPASS
MECHANICALLY CONNECTED CABLES
LEGEND
TAWS WARN
NWS
LANDING GEAR
GS FLAPS TERRAIN
UP
VLO 250 VLE 250
OFF OFF OFF
OFF
PARK/EMER
BRAKE
PARK/EMER
BRAKE
NLG DRAG
BRACE
UNLOCK
NLG
RETRACTION
ACTUATOR
SEQUENCING
CANISTER
RESTRICTOR
UP
GEAR
UP
DOWN LOCK UNLOCK LOCK UNLOCK
LOCK UNLOCK
GEAR
DOWN
DOWN UP
GEAR
DOWN
DOWN UP
RH MLG
UPLOCK
RH SIDE
BRACE
ACTUATOR
LH MLG
UPLOCK
LH SIDE
BRACE
ACTUATOR
R P
AND DUMP VALVE
PSEU
LANDING GEAR
CONTROL HANDLE
LANDING GEAR
SELECTOR VALVE
SEL A UP SEL B DOWN
DOWN UP
P
P
R
R
R
P
P R
DOWN
UP
P
HYDRAULIC
SYSTEM
(EDP & DCMP)
LEFT
HYDRAULIC
SYSTEM
(PTU)
LEFT
HYDRAULIC
SYSTEM
RIGHT
MANUAL
RELEASE
SYSTEM
MECHANICAL
LINK
DUMP
VALVE
GEAR
DOWN
GEAR
DOWN
AUXILIARY
EXTEND
ACTUATOR (LH)
AUXILIARY
EXTEND
ACTUATOR (RH)
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Bombardier_Challenger_Global_00-Landing_Gear(8)
