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specific to the thrust reversers:
During normal thrust reverser deployment the following illuminations
will occur:
1. REV white EI.
2. UNL amber EI.
3. DEP green EI.
During normal thrust reverser stowage the above illuminations will be
reversed.
The CWP contains red L and R REV UNSAFE lights which will illuminate
in conjunction with a UNL or DEP red EI above the N1 indicator.
Whenever this illumination occurs, a continuous “LEFT” or ”RIGHT
REVERSER UNSAFE” voice message will sound. This voice message
can be silenced by depressing the mute switch located on the right
thrust lever or depressing the master CAUT/WARN light.
EICAS Color Description
DEP (EI) Red Uncommanded deployment of the associated (L
or R) thrust reverser.
DEP (EI) Green Normal thrust reverser deployment on the ground.
REV (EI) Amber The associated (L or R) thrust reverser system is
armed in flight or on the ground with thrust lever
greater than MCR.
REV (EI) White The associated (L or R) thrust reverser system is
armed on the ground with thrust lever in IDLE.
REV AUTOSTOW White The associated (L or R) thrust reverser autostow
function is activated.
REV FAULT White A fault is detected in the associated (L or R) thrust
reverser system.
UNL (EI) Red The associated thrust reverser system is not
armed, but an unlock condition is detected.
UNL (EI) Amber On the ground, the thrust reverser is in transition
between stow and deploy. It will temporarily illuminate
during normal thrust reverser deployment. If
illumination continues for more than several seconds,
an abnormal condition exists and the master
caution is tripped.
Pilot’s Manual
2-28 PM-126A
THRUST REVERSER SYSTEM SCHEMATIC
Figure 2-4
L R TR AUTOSTOW (white)
L R REV UNSAFE (red)
L R TR FAULT (white)
CAS MESSAGES
LOWER
BLOCKER
DOOR
UPPER
BLOCKER
DOOR
PRIMARY
DEPLOY/STO
ACTUATOR
STOW
DEPLOY
ELECTRICAL
UNLATCH
RETURN
PRESSURE
MAIN
HYDRAULIC
SYSTEM
THRUST REVERSER
ISOLATION VALVE
THRUST REVERSER
CONTROL UNIT
FULL DEPLO
SWITCH
UNLOCK
SWITCH
UNLATCH
ACTUATOR
LATCH
HOOKS
THROTTLE
RETARD
MECHANISM
UNLATCH
SWITCH
THRUST REVERSER
CONTROL VALVE
A78-0001
Pilot’s Manual
PM-126A 2-29
AIRCRAFT FUEL SYSTEM
The aircraft fuel system consists of two wing tanks, a fuselage tank, a
fuel flow indicating system, a fuel quantity indicating system, a fuel
transfer system, a fuel vent/expansion system and a single-point pressure
refueling system.
WING TANKS
The wing is divided into two separate fuel-tight compartments which
serve as fuel tanks. Each tank extends from the wing root to a point just
short of the winglets, thus providing a separate fuel supply for each engine.
A crossflow shutoff valve is installed to permit fuel transfer between
wing tanks. Wing tank over-pressurization is prevented by
vent/expansion lines between the wing tanks and fuselage tank. This
allows access to the main fuel vent/expansion system of the fuselage
tank. Flapper-type check valves, located in the various wing ribs, allowing
free fuel flow inboard but restricted outboard fuel flow. A main
jet pump is mounted in each wing tank near the center bulkhead to
supply fuel under pressure to the respective engine fuel system. A
standby pump also located at this location can be utilized as a back-up
for the main jet pump, or be used to transfer fuel from wing tank to
wing tank or defuel the aircraft. Three scavenge jet pumps, located
throughout each wing tank, are used to transfer fuel to the inboard collector
bay containing the main fuel jet pump. A fourth scavenge jet
pump, located in the forward end of the collector tank, is used to transfer
fuel to the inlet of the main fuel pumps. A fifth scavenge jet pump,
located in the outlet of the fuselage to wing transfer line, is used to assist
gravity in the transfer of fuel from fuselage to wing during normal
aircraft operation. The wings are filled from the fuselage tank through
the refueling manifold or the gravity filler port.
FUSELAGE TANK
The fuselage tank consists of a single bladder-type cell located in the aft
fuselage. The tank is equipped with a pressure refueling adapter, a
gravity filler port, a fuel probe, a refueling manifold/nozzle, and a fuel
vent/expansion system with an auxiliary vacuum/pressure relief
valve. The tank allows the entire fuel system to be serviced through a
　
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