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1. VIBRATION MONITORING
An engine vibration monitoring computer, mounted in the avionics compartment, monitors
the vibration levels in each engine. Each engine provides the computer with signals from an
accelerometer, an N1 fan speed sensor and an N2 core speed sensor. The computer
processes the signals and provides a vibration velocity amplitude signal to the EICAS for
display on the primary page.
Vol. 1 20--60--2
POWER PLANT
Vibration Monitoring Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
Vibration Monitoring VIB Icon <1001>
Figure 20---60---1
93.5 93.5
93.5 93.5
TO
N1
0 0.0
C ALT RATE P
0.9
N A F
GEAR
20
2200 1070 2200
FUEL QTY (KG)
SLATS / FLAPS
VIB TOTAL FUEL 5470
OIL PRESS
OIL TEMP
FF (KPH)
48
96
210
56
97
210
N2
ITT
600
91.0
600
90.2
DN DN DN
0
Primary Page
BRT
VIB (Icon) (amber)
Displayed when N2
vibration limit is exceeded.
4.0 MILS
0 MILS
N1 (Fan) Vibration Gauges
Displayed when oil pressure of
both engines exceed 25 psi.
VIB
F
A
N
0.9
1.75 MILS
0.9
1.75 MILS
VIB
0.9
N1 Vibration Readout,
scale and pointer
Green, < 1.75 MILS
Amber, > 1.75 MILS
Vol. 1 20--60--3
POWER PLANT
Vibration Monitoring Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
Vibration Monitoring
Figure 20---60---2
L or R VIB FAULT status (white)
Indicates that respective engine
N1 or N2 speed sensor has failed.
BRT
Status Page
Vol. 1 20--60--4
POWER PLANT
Vibration Monitoring Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
A. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
Vibration
Monitor Computer ENG VIB
MON AC BUS 1 1 C7
Vol. 1 20--70--1
POWER PLANT
Reverse Thrust Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
1. REVERSE THRUST
Reverse thrust assists in stopping the aircraft during landing rollout or during a rejected
take-off.
Reverse thrust is accomplished by hydraulic actuators moving the engine translating cowl
assemblies aft to block the rearward discharge of fan bypass air. As the translating cowls
move rearward, cascade vanes are uncovered to redirect the fan bypass air forward.
The thrust reverser system is armed using the thrust reverser LH and RH switches on the
THRUST REVERSER panel and controlled using the thrust reverser levers on the throttle
quadrant.
Reverse Thrust --- General
Figure 20---70---1
WITH REVERSER DEPLOYED
BYPASS
AIR FLOW
NORMAL OPERATION
BYPASS
AIR FLOW
BYPASS
AIR FLOW
BYPASS
AIR FLOW
Reverse Thrust --- Thrust Reverser Subpanel
Figure 20---70---2
LH or RH ARMED
Used to arm thrust reverser
system.
Thrust Reverser Subpanel
Center pedestal
Vol. 1 20--70--2
POWER PLANT
Reverse Thrust Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
Reverse Thrust --- Thrust Reverser Levers
Figure 20---70---3
THRUST
REVERSER
MAX POWER
THRUST
REVERSER
DEPLOY
THRUST
REVERSER
STOW
LEFT ENGINE
THRUST
REVERSER
LEVER
RIGHT ENGINE
THRUST
REVERSER
LEVER
RELEASE
TRIGGER
GUARD
Thrust Reverser Levers
With thrust levers at
IDLE, pulling on thrust
reverser levers deploys
thrust reversers if the
following conditions are met:
Thrust reverser system
is armed.
Aircraft is on ground or
wheel spin--up exceeds
20 kt.
Thrust lever solenoids
prevent thrust reverser
lever movement
beyond the deploy
position until reverser
assemblies are fully
deployed.
Once reversers are
fully deployed, thrust
reverser levers regulate
reverse thrust from
reverse idle to
maximum reverse
power.
Returning thrust
reverser levers to
forward IDLE (fully
down) stows reversers.
Once reversers are
stowed, thrust levers
can be moved forward
to increase thrust.
FORWARD
THRUST
IDLE
RELEASE
TRIGGERS
THRUST LEVER
AT IDLE
NOTE
When reverse thrust has
been selected, forward
thrust is locked out.
Vol. 1 20--70--3
POWER PLANT
Reverse Thrust REV 1, Jan 13/03
　
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