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centering cams as the oleo extends.
The ECU continuously monitors the nosewheel steering system. Any faults detected
are annunciated on EICAS. Fault detection will result in steering system shutdown.
When the steering system is shut down due to fault, or manually disarmed, nosewheel
steering reverts to the free-castering mode (which allows nosewheel deflection up to
NOTE
LANDING GEAR / BRAKES
For Training Purposes Only
Sept 04
15-15
P I LOT T R A I N I N G GU I D E
99 degrees either side of center), and the STEERING INOP caution EICAS message is
displayed.
ENSURE THAT THE NOSEWHEEL ASSEMBLY IS CLEAR OF
PERSONNEL AND TOWING EQUIPMENT BEFORE
SELECTING THE NOSEWHEEL STEERING SWITCH TO THE
ARMED POSITION.
Steering Tiller
Figure 15-7
WARNING
5.0
STEERING INOP
ELECTROHYDRAULIC
SERVOVALVE
ELECTRONIC
CONTROL
UNIT
NOSE LANDING
GEAR DOWN
AND LOCKED
WOW
RUDDER
PEDALS
28 VDC
BUS 1
NOSE WHEEL
DC
BUS 2
P604_15_011
MUTED
ANTI-SKID
NOSE STEER
ARMED
HORN
OFF
Nosewheel
Steering
Switch
7° 0° 7°
55°
99°
55°
99°
STEERING TILLER
PILOT’S SIDE PANEL
No. 3
Hydraulic System
(From Nose Landing
Gear Down Line)
Rudder Pedals
Steering Tiller
Steering Inop
Legend
Power
Commands
Messages
Hydraulic Power
P604_15_011
STEERING
ACTUATOR
LANDING GEAR / BRAKES
15-16 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Wheels and Brakes
Description
Dual-wheel assemblies are installed on each main landing gear strut, and each main
wheel is equipped with a carbon brake disk assembly. The nose gear has two wheels
and uses chine tires to eject ground water away from the aircraft engines.
Components and Operation
Each wheel of the main landing gear is equipped with self-adjusting multidisc carbon
brakes. Hydraulic system 3 powers the brakes of the inboard wheels and hydraulic
system 2 powers the brakes of the outboard wheels. A parking brake function is
available at both the inboard and outboard brakes. Anti-skid protection is provided.
Each main wheel has four fusible plugs that melt to prevent tire burst in the event of an
overheated wheel or brake condition.
Brake application is initiated by pressing the brake pedals which are mechanically
linked to the four associated brake control valves. The brake control valves meter
hydraulic pressure to the brakes through anti-skid control valves.
During gear retraction, hydraulic pressure from the nose landing gear is directed to the
brake control valves to stop main wheel rotation (in-flight braking).
In case of failure of hydraulic systems 2 or 3, accumulators in both hydraulic brake
systems provide pressure for approximately six brake applications with the anti-skid
selected off. Loss of either hydraulic system 2 or 3 results in a 50% reduction in
braking capability. Braking remains symmetrical and anti-skid is available at the
working brakes.
Two brake wear indicator pins are installed on each brake assembly to provide a visual
indication of brake wear. When the end of the wear indicator pin is flush with the top
of the indicator housing, the brake should be serviced.
The brake wear indicator pins must be checked with the brakes
applied and hydraulic systems 2 and 3 pressurized.
NOTE
LANDING GEAR / BRAKES
For Training Purposes Only
May 03
15-17
P I LOT T R A I N I N G GU I D E
Brakes and Lower Main Gear Structure
Figure 15-8
Hydraulic Synoptic Page (Inboard and Outboard Brake Pressure)
Figure 15-9
P604_15_031
Brake Wear Indicator
Axle
Carbon
Brake
Disks
BRT BRT
1B 3A 3B 2B
3050
PSI
3000
PSI
2950
PSI
INBD
BRAKES
3000 PSI
OUTBD
BRAKES
3000 PSI
80 °C 15 °C
RUDDER
L ELEVATOR
L AILERON
FLT SPLR
GND SPLR
RUDDER
L ELEVATOR R
L AILERON R
LNDG GEAR
N/W STEER
NOSE DOOR
RUDDER
ELEVATOR R
AILERON R
FLT SPLR
MLG AUX ACT
1A 2A
49%
HYDRAULIC
95 °C
82% 76%
Inboard and Outboard Brake
Pressure Readout
Green
White
Amber
Indicates brake pressure of
respective system. Readout in
50-psi increments.
– brake pressure is
1050 psi to 3200 psi.
– brake pressure is
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