747-400
FAULT ISOLATION/MAINT MANUAL
SYS 3 HYDRAULIC RIGHT POWER
PUMP ELCU, M3371 CENTER
GENERATOR 3 POWER SEE V
CENTER-RIGHT PANEL, P515
UTILITY
POWER
ELCU (REF) FEEDER GALLEY LEFT POWER
ELCU (REF) CENTER
SEE W
FWD
GENERATOR 4 POWER CENTER-RIGHT PANEL, P615
RIGHT POWER CENTER
V
GENERATOR 1 POWER CENTER-LEFT PANEL, P514
GALLEY FEEDER
ELCU (REF) UTILITY POWER
ELCU (REF) SYS 2 HYDRAULIC
FWD PUMP ELCU, M3370 GENERATOR 2 POWER
CENTER-LEFT PANEL, P614
LEFT POWER CENTER W Main Hydraulic Supply System - Component Location Figure 102 (Sheet 16)
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A
PRESSURE HOSE CHECK VALVE (FIREWALL-MOUNTED)
HYDRAULIC PRESSURE HOSE (REF)
HYDRAULIC SUPPLY HOSE (REF) CASE DRAIN HOSE CHECK VALVE (FIREWALL-MOUNTED)
747-400 FAULT ISOLATION/MAINT MANUAL RIGHT THRUST REVERSER HALF 416 (ENG 1) 436 (ENG 3) 426 (ENG 2) 446 (ENG 4)
XSEE CHECK VALVE
SUPPLY HOSE SELF-SEALING DISCONNECT (REF)
COVER PLATE (REF)
FUEL HOSE (REF)
HYDRAULIC CASE DRAIN HOSE (REF)
CHECK VALVE
FWD X
Main Hydraulic Supply System - Component LocationFigure 102 (Sheet 17)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
MAIN HYDRAULIC SUPPLY SYSTEM - DESCRIPTION AND OPERATION
________________________________________________________
1. General_______
A. The airplane has four main hydraulic supply systems. Each system operates independently. The only difference between the systems is the type of demand hydraulic pumps that are used and the fluid capacities. The hydraulic supply systems have the following components:
-Engine-driven pump (EDP)
-Demand pump
-Reservoir
-
Hydraulic fluid filters
-
Hydraulic supply shutoff valve
-Heat exchanger
-Pressure module
-Return module
-Case drain module
-Reservoir pressurization module
-
Hydraulic interface module (HYDIM)
B.
Systems 1 and 4 are used to supply power for all landing gear systems, normal and alternate brake systems, and the trailing edge flaps. These systems also supply power for some of the primary flight controls (ailerons, elevators, and rudder) for the redundancy that is necessary. Systems 2 and 3 are used to supply power for most of the primary flight controls. System 2 helps supply power for the alternate brakes.
C.
Each system supplies power for the thrust reverser operation of the related engine.
D.
Each of the systems has an EDP that is used as the primary power source. Each system also has a demand pump that is used during operations that require a large hydraulic flow. The demand pump is also used if the EDP does not operate correctly.
E.
Systems 2 and 3 have ac motor-driven pumps (ACMP).
F.
Systems 1 and 4 have air-driven pumps (ADP).
G.
Systems 1 and 4 also have auxiliary ac motor-driven pumps that operate only when the airplane is on the ground.
H.
The EDP and the demand pump are installed in parallel for each system. The EDP's and ADP's are the same and interchangeable. The EDPs will operate continuously when the engine is in operation. The pneumatic system supplies power for the ADPs. The ADPs have three modes of operation: off, run-continuously, or run-on-demand. Electrical power for the ACMPs is supplied by the 115-volt ac power bus. Electrical power for the auxiliary pump is supplied by the 115-volt dc ground handling bus.
2. Engine-Driven Pump__________________
A. The EDP is installed on the engine accessory gearbox. It is a variable-displacement pressure-compensated pump. When it is in operation it can supply maximum fluid flow at an output pressure of 2,850 psi. When there is no fluid flow, the output pressure is 3,100 psi.
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