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DOOR OPENED
HORN MUTE
ON
Messages:
PROXIMITY
NOSE DOOR OPEN
GEAR DISAGREE
PARKING BRAKE
PARK BRAKE SOV
HORN MUTED
PROX SYS FAULT
. DOWNLOCK 1,2
COMMANDS:
EXTEND
RETRACT
AURAL/VISUAL WARNING MESSAGES
Primary Page
P
R
OXIMIT
Y
SE
N
SOR
UNIT
EL
E
CTR
ONIC
S
STALL WARNING
SYS/AOA
HORIZ STAB TRIM
CONTROL UNIT 1,2
FLAP ELECTRONIC
CONTROL UNIT 1,2
HYDRAULIC MOTOR
PUMP 1,2
ANTI SKID
INBD/OUTBD
STALL PROTECTION
SYSTEM
AIR DATA SYS--
PROBE HEATERS
FUEL SYSTEM
COMPUTER UNIT
AUXILIARY POWER
UNIT (ECU, FIRE)
THRUST REVERSER
1,2
AIR DRIVEN
GENERATOR
AUTO DEPLOY
UTILITY BUS
SHED
IRS SYS
<0025>
PAX DOOR:
PIN 1,2 LOCKED
CAM 1,2 LOCKED
<0039> <0006>
Vol. 1 16--30--3
REV 56, Jan 31/03
LANDING GEAR
Proximity Sensing System
Flight Crew Operating Manual
CSP A--013
MASTER
PSEU --- EICAS Messages <MST>
Figure 16---30---2
NOTE
The WOW OUTPUT
caution message may
be accompanied by
the following:
WOW OUTPUT
Caution (amber)
Comes on to indicate
that WOW outputs,
channel 1 and
channel 2 do not
agree.
PFD, speed trend
vector inoperative,
PFD low speed cue
comes on,
PFD displays TA only,
RTU indicates TCAS
STANDBY and
ATC 1(2) STANDBY,
Inadverent takeoff
configuration warnings,
Fuel quantity fluctuates
during pitch and bank
maneuvers.
NOTE
One or more of the
WOW sensors
disagree with each
other which may affect
air and ground modes
of operation.
Expect that inadvertent
operations of WOW
dependant systems
may occur.
WOW INPUT Caution
(amber)
Comes on to indicate
that a WOW sensing
circuit has failed or is
in disagreement with
the other sensing
circuits.
PROX SYS CHAN
Caution (amber)
Comes on to indicate
that the normal landing
gear extension/retraction
system is inoperative.
NOTE
If landing gear extension/
retraction is abnormal,
GEAR DISAGREE warning
WOW OUTPUT FAIL message will not come on.
Status (white)
Comes on to indicate
that a WOW output
fault is detected in a
non--critical system.
PROX SYS FAULT
Status (white)
Comes on to indicate
a failure in the PSEU
system.
Status Page
WOW OUTPUT FAIL
<0039>
<0039>
PROX SYS FAULT
Primary Page
<0039>
<0006>
WOW INPUT
WOW OUTPUT
PROX SYS CHAN
<0039>
<0039>
PROX SYS FAULT
Status (white)
Comes on to indicate
that the PSEU has
detected:
a sensor/internal
failure, or
a loss of redundency
REV 56, Jan 31/03
Vol. 1 16--30--4
LANDING GEAR
Proximity Sensing System
Flight Crew Operating Manual MASTER
CSP A--013
A. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
PROX SENS
LGC /D2 DC ESS 4 B13
PROX SENS
LGC /D2 WOW
1 & 2 DC BAT 2
P3
Proximity
Sensing
Landing Gear
Control
PROX SENS
LGC /D1
P2
PROX SENS
LGC /D1
DC BUS 1 1
F6
PROX SENS
WOW 1
F7
PROX SENS
WOW 2 DC BUS 2 2 F9
Vol. 1 16--40--1
REV 56, Jan 31/03
LANDING GEAR
Brake System
Flight Crew Operating Manual
CSP A--013
MASTER
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 No. 3 hydraulic system and the brakes of the
outboard wheels are powered by No. 2 hydraulic system.
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 No. 2 and No. 3
　
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