D. Spoiler Hydraulic Actuation System:
(See Figure 13.)
A flight spoiler actuator and ground spoiler actuator are installed in each
wing. Both actuators are tandem actuators that receive hydraulic pressure
for operation from L SYS and R SYS. Should there be a loss of one
hydraulic system, the remaining system will continue to provide operational
pressure.
The ground spoiler actuators also require hydraulic control pressure,
normally provided from L SYS. In the event both L SYS engine driven
pumps fail, the PTU and AUX pumps can be used to provide control
pressure.
Hydraulic pressure to all flight and ground spoiler actuators can be
inhibited through the use of the SPOILER CONTROL switch located on the
cockpit center pedestal. When selected to OFF, operation of flight spoilers,
ground spoilers and speed brakes is inhibited.
E. Spoiler Position Sensing and Indication System:
The spoiler position sensing and indication system provides indication of
spoiler position to Data Acquisition Units (DAUs) #1 and #2 and the
Maintenance Data Acquisition Unit (MDAU). This is accomplished through
the use of spoiler position resolvers installed on each wing. Flight spoiler,
ground spoiler and speed brake movement is visually depicted on the
FLIGHT CONTROLS synoptic page.
3. Controls and Indications:
(See Figure 13 and Figure 14.)
NOTE:
A full description of the FLIGHT CONTROLS synoptic
page can be found in section 2B-03-00: Engine
Instruments and Crew Alerting System Description.
A. Circuit Breakers (CBs):
The spoiler system is protected by the following CBs:
Circuit Breaker Name: CB Panel: Location: Power Source:
L SURFACE XDCRS LEER C-18 #1 ESS 26 VAC Bus
R SURFACE XDCRS REER C-6 #2 ESS 26 VAC Bus
SPDBRK ALARM REER A-26 R ESS DC Bus
SPLR FLT PWR S/O CPOP E-3 R ESS DC Bus
GND SPOILERS CPOP E-2 R ESS DC Bus
LEFT WOW POP C-1 L ESS DC Bus
RIGHT WOW CPOP C-1 R ESS DC Bus
WHEEL SPEED POP C-3 L ESS DC Bus
TQA CPOP C-2 R MN DC Bus
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-27-00
Page 39
May 22/01
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