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to left secondary lock relay and to secondary lock
actuator, but is routed directly to solenoid No. 1 of the
left TR selector control valve to maintain hydraulic
pressure to the deploy side of the actuator.
• REV UNLK indication:
The left thrust reverser REV UNLK light will illuminate when
the secondary lock actuator retracts (unlocks), either the
upper or lower door limit switch is activated, or the primary
lock switch (part of TR actuator) is closed (unlocked position).
When any or all of these conditions are present, power is
transmitted from the warning lights power system to energize
the left TR interlock relay. When activated, this relay
completes a circuit through its contacts to the left TR unlock
indicator, causing the REV UNLK light to illuminate. In
addition, when any of the conditions for the REV UNLK light
illumination occurs, the Engine Instrument and Crew Advisory
System (EICAS) and standby warning light indications are
also activated if either Nutcracker No. 1 relay is not energized
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-78-00
Page 3
May 30/02
Revision 7
(air configuration) or power lever No. 2 T/O relay is
energized.
• REV DPLY indication:
The left thrust reverser REV DPLY light on the pilot’s
instrument panel will illuminate when TR doors are fully
deployed. In this condition, power is transmitted from the
warning lights power system through closed contacts of the
deploy limit switch to the left TR deploy indicator which
causes the REV DPLY light to illuminate.
(3) Stowing:
When reverse thrust lever in cockpit is moved to the stow position,
the left TR lever switch opens. This de-energizes the left secondary
lock relay, thereby opening circuits to de-energize solenoid No. 1 of
the left TR selector control valve and to shut off hydraulic pressure
to the deploy side of TR hydraulic actuator. At the same time, circuits
are closed to energize solenoid No. 2 of the left TR selector control
valve to allow hydraulic pressure to the stow side of TR hydraulic
actuator. The REV DPLY light will extinguish when doors begin to
transition towards stow position. When TR doors are stowed and
locked, the REV UNLK light will extinguish also.
(4) Emergency Stowing:
(See Figure 1.)
If an in-flight failure causes a REV UNLK light and REV UNLOCKED
message to be displayed on the EICAS, the T/REV EMER STOW
switch, located on the center pedestal, can be depressed. Although
the results of depressing the T/REV EMER STOW switch are the
same, the sequence of events varies with airplane effectivity as
follows:
Airplanes SN 1000 through 1435 not having Part 2 of ASC 418:
Depressing the T/REV EMER STOW switch completes a circuit from
the essential 28V DC bus via the T/R EMER STOW circuit breaker
(airplanes SN 1000 - 1182 not having ASC 210) or L T/R EMER
STOW and R T/R EMER STOW circuit breakers (airplanes SN 1000
- 1182 having ASC 210 and SN 1183 and subsequent) to energize
the stow solenoid of both TR selector control valves. This in turn
allows hydraulic pressure to the stow side of both TR hydraulic
actuators.
Airplanes SN 1436 and subsequent and airplanes SN 1000
through 1435 having Part 2 of ASC 418: These airplanes have the
existing dual solenoid TR selector control valves replaced with
single solenoid TR selector control valves. The single solenoid TR
selector control valve employs a new spool and sleeve assembly
that is spring biased and hydraulically powered to the stow position.
The new valve spool and sleeve assembly is automatically piloted to
the stow position when hydraulic power is available, thus eliminating
the need for the stow solenoid. Depressing the T/REV EMER STOW
switch removes all electrical power to both TR selector control
valves. Spring pressure and hydraulic pressure then move the spool
to the stow position, allowing hydraulic pressure to the stow side of
both TR hydraulic actuators. The T/R EMER STOW circuit breaker
OPERATING MANUAL
2A-78-00 PRODUCTION AIRCRAFT SYSTEMS
Page 4
May 30/02
Revision 7
(airplanes SN 1000 - 1182 not having ASC 210) or L T/R EMER
STOW and R T/R EMER STOW circuit breakers (airplanes SN 1000
- 1182 having ASC 210 and SN 1183 and subsequent) are removed
on these airplanes.
C. Subsystems, Units and Components:
The thrust reverser system is composed of the following subsystems, units
and components:
(1) Safety Devices, Consisting of the Following:
• Primary lock
• Secondary lock
• Mechanical feedback system
(2) Major Components, Consisting of the Following:
　
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