R Hydraulic Power Users
R Figure 002A
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Hydraulic Components - Location Figure 003
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Hydraulic Components - Location Figure 004
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Pipeline and Component Identification Figure 005
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Manifold Connections Figure 006
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The seal drains of some components (emergency generator, power control units, power transfer unit and electric pumps) and the pressure relief valves of the reservoirs are connected to the seal drain system. This system collects the fluid leakage from these components and keeps it in containers which can be emptied on the ground. This prevents the collection of hydraulic fluid in the aircraft structure where it may cause a risk of fire.
An air bleed from the pneumatic system of the aircraft pressurizes the reservoirs to 50 psi (3.5 bar) . This makes sure that there is a sufficient supply of fluid to the pumps in all conditions.
There are electrically-operated motorized valves in the suction lines to the two engine pumps. They close automatically when the engine fire handles are operated and stop the supply of hydraulic fluid to the pump.
2. System Description__________________
A. Main System
**ON A/C 001-049, 051-061, 101-105, 201-203,
(Ref. Fig. 007)
**ON A/C 062-099, 106-149, 204-299, 301-399,
(Ref. Fig. 007A)
**ON A/C 151-199,
(Ref. Fig. 007B)
R **ON A/C 401-499,
R (Ref. Fig. 007C)
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399,
R (Ref. Fig. 008)
Hydraulic Power - Schematic
Figure 007 (SHEET 1)
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Hydraulic Power - Schematic
Figure 007 (SHEET 2)
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Hydraulic Power - Schematic
Figure 007 (SHEET 3)
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Hydraulic Power - Schematic R Figure 007A
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Hydraulic Power - Schematic R Figure 007B
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INTENTIONALLY BLANK
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R Hydraulic Power - Schematic
R Figure 007C (SHEET 1)
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R Hydraulic Power - Schematic
R Figure 007C (SHEET 2)
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R Hydraulic Power - Schematic
R Figure 007C (SHEET 3)
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Line Routing of Forward Part
Figure 008
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R (Ref. Fig. 008A)
R **ON A/C ALL
R (Ref. Fig. 009, 010)
The three systems are each pressurized by one main pump. The Green system pump is connected to the left engine and the Yellow system pump is connected to the right engine. The Green and Yellow pumps supply hydraulic power when their engine operates. The electric pump of the Blue system starts automatically when any one of the engines operates. The three system main pumps are usually set to operate permanently. If necessary (because of a system fault, or for servicing), the pumps can be set to off from the flight compartment.
Most of the components of the systems are in the three hydraulic compartments. The Green system components are in the main landing gear compartment. The Yellow system components are in the hydraulic compartment in the right belly fairing. The Blue system components are in the hydraulic compartment in the left belly fairing. The two hydraulic compartments (Blue and Yellow) are forward of the main landing-gear compartment.
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