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• Flaps
• Wheel Brakes
• Nosewheel Steering
• Standby Electrical Power System Motor
B. Flight Hydraulic System:
Functionally and structurally similar, the Flight system (Figure 3)
compliments the Combined system by sharing the workload, yet remaining
independent and isolated for specific functions. Its pump is located on the
right engine, and its reservoir and manifold are located on right side of the
tail compartment.
Total system capacity is approximately 4.5 gallons (17 liters). This includes
the reservoir, lines and all system components. Pressurized fluid is
provided to the following systems, units and components:
• Ailerons
• Speed Brakes
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-29-00
Page 5
October 11/02
Revision 8
• Flight Spoilers
• Ground Spoilers
• Rudder
• Elevator
• Yaw Damper
• Right Thrust Reverser
• Utility Pump Motor
C. Fluid Replenishing System:
Hydraulic system fluid replenishing can be accomplished by using either
the fill connection on the ground test panel (underside of the aircraft, just
forward of the tail compartment door) or an onboard replenishing system
(inside the tail compartment).
2. Description of Subsystems, Units and Components:
A. Combined System and Flight System Reservoirs:
(See Figure 4 and Figure 5.)
(1) Combined System Reservoir Particulars:
The Combined system reservoir contains two chambers separated
by a bulkhead; one chamber supplies the Combined and Utility
systems, and the other supplies the Auxiliary system. Total capacity
of the reservoir is 5.5 gallons (20.8 liters) with a Combined system
working volume of 3.75 gallons (14.2 liters) and an Auxiliary system
working volume of 1.75 gallons (6.6 liters). Both chambers are full
under normal operating conditions. An opening at the top of the
reservoir bulkhead allows fluid flow from the Combined chamber to
the Auxiliary chamber. Filling of both chambers can be
accomplished using either the fill connection on the ground test
panel (underside of the aircraft, just forward of the tail compartment
door) or a replenishing system (inside the tail compartment).
Four suction ports are included on the reservoir: engine pump, utility
pump, auxiliary pump and ground test rig. Six return ports are also
incorporated. Other ports include one each for the bleed line and
pressure relief valve.
(2) Flight System Reservoir Particulars:
The Flight system reservoir differs from the Combined system
reservoir in that it is a smaller, single chamber reservoir. Total
capacity of the reservoir is 1.25 gallons (4.7 liters) with working
volume of 0.86 gallons (3.25 liters). Filling is accomplished using the
same methods as the Combined system reservoir.
Five ports are included on the Flight system reservoir: suction,
return, drain, bleed and relief valve.
(3) Reservoir Pressure Relief Valves:
A pressure relief valve is installed on each reservoir to prevent
overpressurization. If reservoir pressure exceeds 100 psi, the valve
opens to vent excess pressure overboard through a vent line. The
valve closes at 75 psi.
(4) Reservoir Thermal Switches:
OPERATING MANUAL
2A-29-00 PRODUCTION AIRCRAFT SYSTEMS
Page 6
October 11/02
Revision 8
A thermal switch is installed on each reservoir to monitor system
fluid temperature. If fluid temperature reaches 220 ±5°F (104 ±3°C),
the thermal switch closes causing a blue CMB HYD HOT or FLT
HYD HOT advisory message to be displayed on the Crew Alerting
System (CAS). As fluid temperature drops to 175 ±10°F (79 ±6°C),
the thermal switch opens, clearing the CAS message.
NOTE:
Automatic operation of the utility pump is not possible
with a FLT HYD HOT advisory message displayed.
(5) Reservoir Manual Bleeder Valves:
A manual bleeder valve installed on each reservoir provides a
means to relieve trapped air pressure acquired during servicing.
Pressing and holding the BLEED button on the valve opens the
valve, venting excess air pressure overboard through a vent line.
(6) Reservoir Fluid Quantity Transmitters:
A fluid quantity transmitter installed on each reservoir measures fluid
quantity by using the reservoir piston’s movement to actuate a
spring-loaded tape reel mechanism. When supplied with 28V DC
from the Essential DC bus, the quantity transmitter supplies an
output voltage proportional to fluid quantity to the Data Acquisition
Units (DAUs) for display on the HYDRAULICS system page.
(7) Reservoir Sight Gauges:
　
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