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spring-loaded lock plunger. The normal actuator position is with
piston rod extended, TR stowed and mechanical lock engaged.
In the stowed position, the four latches (each riding on a ball
bearing) are seated against the lock plunger which retains them in
the extended position. When extended, the latches are seated
against the end of the piston chamber. Deploy hydraulic pressure
(less than 1000 psi) will cause the lock plunger to act against a
retaining spring. When the lock plunger moves away from the
piston, it allows the latches to retract into the piston. As the piston
retracts, residual hydraulic pressure in the STOW side of the
actuator is ported to return through the STOW port.
Hydraulic pressure applied through the STOW port forces the piston
to the extend position. The residual hydraulic pressure in the deploy
side of the actuator is ported to return through the DEPLOY port. At
the end of its stroke, the piston bottoms against the plate at the
cylinder’s end fitting. At the same time, the lock plunger (which is
held against the other side of the plate by retaining spring wedges
between the latches and piston rod surface) forces the latches to
extend from the piston into the locked position. The end
circumference of the plunger is sloped, enabling it to wedge
between the latches, ball bearings and piston rod surface.
The lock indicator switch is operated by a hydraulic plunger in the
switch housing. When the actuator or piston is extended and locked,
the plunger is restrained within the housing by one of the latches. A
ball bearing between the side of the hydraulic plunger and the
spring-loaded switch plunger keeps the switch plunger depressed.
When the actuator piston is unlocked, hydraulic pressure moves a
hydraulic plunger inward towards the cylinder. The ball bearing
seats inside a groove in the plunger, which allows the switch plunger
to extend. Extension or retraction of the switch plunger determines
which set of contacts in the switch is open or closed.
(3) Secondary Lock Actuator:
(See Figure 2.)
The secondary lock actuator is solenoid operated to provide electromechanical
control of the secondary lock for the TR. The actuator is
mounted at the outboard stang beam.
The solenoid is spring-loaded to the extended position and retracts
when 28V DC power is applied to a solenoid coil. A bank of three
microswitches is contained within the actuator. Switch A indicates
shaft position (unlock), switch B controls current to the TR selector
control valve and switch C is not used but can be used to replace
switch B (if necessary).
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-78-00
Page 7
May 30/02
Revision 7
3. Controls and Indications:
A. Circuit Breakers (CBs):
The thrust reverser system is protected by the following CBs:
Circuit Breaker Name: CB Panel: Location: Power Source:
L SEC LOCK P G-7 ESS DC Bus
R SEC LOCK P H-7 ESS DC Bus
L T/REV CONTROL P I-7 ESS DC Bus
R T/REV CONTROL P J-7 ESS DC Bus
T/R EMER STOW (1) P K-7 ESS DC Bus
L T/R EMER STOW (2) P L-7 ESS DC Bus
R T/R EMER STOW (2) P K-7 ESS DC Bus
NOTE(S):
(1) Airplanes SN 1000 - 1182 not having ASC 210 or Part 2 of ASC 418.
(2) Airplanes SN 1000 through 1182 having ASC 210 but not having Part 2
of ASC 418; SN 1183 through 1435 not having Part 2 of ASC 418.
B. Crew Alerting System (CAS) Messages:
Warning (Red) Messages and Annunciations:
CAS Message: SWLP Indication: Cause or Meaning:
L REV UNLOCK L REV UNLOCKED Left thrust reverser has become unlocked.
R REV UNLOCK R REV UNLOCKED Right thrust reverser has become unlocked.
Annunciation: Cause or Meaning:
White REV UNLOCK light above DU 2 or 5. Thrust reverser unlocked.
White REV DPLY light above DU 2 or 5. Thrust reverser deployed.
Advisory (Blue) Annunciations:
Annunciation: Cause or Meaning:
REV ARM light (green) illuminated above
DU 2 or 5.
Parameters satisfied for thrust reverser
deployment.
4. Limitations:
A. Flight Manual Limitations:
Cancellation of reverse thrust should be initiated by 70 KCAS so as to be at
reverse idle by normal taxi speed. Thrust reverser door extension at taxi
speeds is permitted if ASC 166 is incorporated and thrust reversers are
kept low.
For airplanes SN 1000 through 1143 without ASC 166, use of thrust
reversers is limited to one (1) minute every thirty (30) minutes.
OPERATING MANUAL
2A-78-00 PRODUCTION AIRCRAFT SYSTEMS
Page 8
May 30/02
Revision 7
Thrust Reverser Emergency Stow Switch
Figure 1
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-78-00
　
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