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Pilot’s Manual
PM-132A 2-23
FIRE EXTINGUISHING SYSTEM
Figure 2-3
L ENGINE
EXTINGUISHER FIRE
ARMED
[CLOSED]
FIRE
PUSH
ARMED
[CLOSED]
FIRE
PUSH
FIRE EXT NGUISHER
R ENGINE
ARMED ARMED
BLEED AIR
SHUTOFF
VALVES
FUEL
SHUTOFF
VALVE
HYDRAULIC
SHUTOFF
VALVE
L NACELLE
#1
CONTAINER
PRESSURE
GAUGE
SHUTTLE
VALVES
RELIEF VALVE
PRESSURE
GAUGE
RELIEF VALVE
#2
CONTAINER
BLEED AIR
SHUTOFF
VALVES
FUEL
SHUTOFF
VALVE
HYDRAULIC
SHUTOFF
VALVE
R NACELLE
RED YELLOW
THERMAL
DISCHARGE
INDICATOR
MANUAL
DISCHARGE
INDICATOR
L DC
GENERATOR
TRIP
L WSHLD
ALTERNATOR
TRIP
L ENGINE
IGNITORS
TRIP
L THRUST REVERSER
CONTROL UNIT
TRIP
R DC
GENERATOR
TRIP
R WSHLD
ALTERNATOR
TRIP
R ENGINE
IGNITORS
TRIP
R THRUST REVERSER
CONTROL UNIT
TRIP
#1 #2 #2 #1
Pilot’s Manual
2-24 PM-132A
THRUST REVERSERS
Each engine is equipped with an independent, electrically controlled,
hydraulically actuated, clamshell-type thrust reverser. The thrust reverser
system consists of a thrust reverser control unit, an engine nacelle
afterbody on each engine, a piggy-back thrust reverser lever on
each main thrust lever, associated hydraulic plumbing, and associated
electrical wiring.
The thrust reverser control unit integrates all deploy, stow, and indication
functions of the thrust reverser system. Input signals indicating the
status of each of these functions are analyzed by the thrust reverser
control unit. Different combinations of these signals will generate the
applicable output command from the thrust reverser control unit.
Each nacelle afterbody consists of an upper and lower blocker door, an
inboard and outboard primary deploy/stow actuator, unlatch actuator,
unlatch switch, unlock switch, full deploy switch, and a throttle retard
mechanism. Hydraulic power for thrust reverser operation is supplied
by the aircraft hydraulic system. A selector valve for each thrust reverser
is installed in the tailcone. The selector valves control hydraulic flow
to the associated system actuators in response to electrical inputs from
the associated thrust reverser lever and position switches via the thrust
reverser control unit.
The thrust reverser levers and the system circuit breakers are the only
controls used by the crew to operate the system. Electrical power for
thrust reverser control and indication circuits is 28-vdc supplied by the
L and R ESS buses through the L and R REVERSER circuit breakers. The
L REVERSER circuit breakers located in the ENGINE group of the pilot’s
circuit breaker panel include the 5-amp DEPLOY, the 3-amp ANN,
and the 3-amp STOW. The R REVERSER circuit breakers located within
the ENGINE group of the copilot’s circuit breaker panel also include a
5-amp DEPLOY, a 3-amp ANN, and a 3-amp STOW.
In order to arm the thrust reversers, both main gear weight-on-wheels
switches must be in the ground mode (aircraft weight on the main gear)
and the thrust levers must be in the IDLE position. When fully armed
(reverser system relays and switches are properly sequenced), the associated
isolation valve is open and the system is ready for deploy/stow
commands by operation of the thrust reverser levers.
The clam-shell type blocker doors are held in the stowed position by
latch hooks. The latch hooks are hinged to the unlatch actuator, and are
rotated away from the blocker doors for thrust reverser deployment.
When the deploy cycle is initiated, hydraulic pressure is applied to the
stow side of the primary actuators which move the doors into an
Pilot’s Manual
PM-132A 2-25
overstowed condition. Overstowing the thrust reversers allows the unlatch
actuators to rotate the latch hooks. As the latch hooks begin to rotate,
the unlock switch signals the thrust reverser control unit of the
unlocked condition. As the latch hooks clear the blocker door receptacles,
an unlatch switch signals the thrust reverser control unit that the
blocker doors are unlatched. After the latch hooks are unlatched, hydraulic
pressure is applied to the deploy side of the primary actuators
which push the doors open.
Stow is initiated automatically whenever an unlock condition is detected
and the thrust reverser lever is forward of the thrust reverser deploy
detent. This occurs during the normal stow cycle and also to correct an
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