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PROX SYS CHAN caution (amber)
Indicates loss of one PSEU channel
or input/output of a critical system.
MLG FAULT status (white)
Indicates PSEU has detected a
fault in the main landing gear
shuttle valve.
PROX SYS FAULT 1
PROX SYS FAULT 2
MLG FAULT
BRT
Status Page
Primary Page
Vol. 1 16--30--5
LANDING GEAR
Proximity Sensing System REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
A. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
PSEU CH A DC BUS 1 1 G1
Electronics
PSEU CH B DC BUS 2 G1
Proximity
S i
y Unit PSEU CH A P1
Sensing PSEU CH B BATTERY
BUS
2 P2
Weight On
Wheels WOW RELAY
P3
Vol. 1 16--30--6
LANDING GEAR
Proximity Sensing System REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 16--40--1
LANDING GEAR
Brake System REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
1. BRAKE SYSTEM
Each wheel of the main landing gear is equipped with self-adjusting multi-disc brakes. The
brakes of the inboard wheels are powered by hydraulic system 3 and the brakes of the
outboard wheels are powered by hydraulic system No. 2.
Brake application is initiated by pressing the rudder pedals which are mechanically linked to
the associated brake control valves. The brake control valves meter hydraulic pressure,
proportional to the pedal pressure, to the four main wheel brake units, through four
independent anti-skid control valves and four hydraulic fuses.
If a leak occurs in a brake line, the associated hydraulic fuse will close off the hydraulic line,
preventing loss of the entire system fluid.
With the loss of one hydraulic system, the aircraft has 50% symmetric braking capability with
full anti-skid control to the working brakes. In the event of a failure of both hydraulic systems
2 and 3, accumulators in each hydraulic system will provide reserve pressure for braking.
During landing roll or rejected takeoff, reverse thrust and the ground spoilers will decelerate
the aircraft, if the brakes are degraded or fail completely.
Available inboard and outboard brake pressure is continuously monitored and displayed on
EICAS on the hydraulic synoptic page, and any abnormal brake pressure detected is
displayed on EICAS in the form of a visual message.
During landing gear retraction, hydraulic pressure is applied to the main wheel brake control
valves to stop main wheel spin. A rubber spin-down pad assembly in the nose landing gear
wheel well provides resistance to stop the nose wheel from spinning after gear retraction.
Two brake wear indicator pins installed on each brake assembly provide a visual indication
of brake wear.
NOTE
The brake wear indicator pinsmust be checked with the brakes
applied and No. 2 and No. 3 hydraulic systems pressurized.
Vol. 1 16--40--2
LANDING GEAR
Brake System REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Brake System --- Schematic
Figure 16---40---1
L R
CO--PILOT’S
BRAKE PEDALS
NO.3
HYDRAULIC
SYSTEM
LEFT
INBOARD
BRAKE
CONTROL
VALVE
RIGHT
INBOARD
BRAKE
CONTROL
VALVE
LEFT
INBOARD
ANTI--SKID
CONTROL
VALVE
RIGHT
INBOARD
ANTI--SKID
CONTROL
GEAR UPLINE
PARKING
BRAKE
SOV
VALVE
RIGHT
OUTBOARD
BRAKE
CONTROL
VALVE
LEFT
OUTBOARD
BRAKE
CONTROL
VALVE
L R
LEFT
INBOARD
BRAKE
PILOT’S
BRAKE PEDALS
NO. 2 HYDRAULIC SYSTEM
NO. 3 HYDRAULIC SYSTEM
MECHANICAL LINK
ANTI--SKID
CONTROL
UNIT
(ASCU)
NO.2
HYDRAULIC
SYSTEM
RIGHT
OUTBOARD
BRAKE
LEFT
OUTBOARD
BRAKE
RIGHT
INBOARD
BRAKE
LEFT
OUTBOARD
ANTI--SKID
CONTROL
VALVE
RIGHT
ANTI--SKID
CONTROL
VALVE
OUTBOARD
ACCUMULATOR P P ACCUMULATOR
PRESSURE
SENSOR
EICAS
T
TEMPERATURE
SENSOR
EICAS
T T T
HYD
SENSOR
PARKING
BRAKE
HANDLE
RETURN
RETURN
Vol. 1 16--40--3
LANDING GEAR
Brake System Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
Brake System EICAS Indications <1001>
Figure 16---40---2
IB BRAKE PRESS
OB BRAKE PRESS
IB or OB BRAKE PRESS caution (amber)
　
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