Description and Operation 1 ALL General 1 Transmitter - Hydraulic Fluid 1
Temperature
Operation 1 Adjustment/Test 501 ALL TRANSMITTER - TEMPERATURE 29-32-02
Removal/Installation 401 ALL
HYDRAULIC FLUID QUANTITY 29-33-00
INDICATING SYSTEM
Description and Operation 1 ALL General 1 Transmitter - Hydraulic Fluid 1
Quantity
Operation 1
29-CONTENTS
GUN Page 12 Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
CHAPTER 29 - HYDRAULIC
TABLE OF CONTENTS
_________________
Chapter Section Subject_______ Subject ____ Effectivity
_______ Page ___________
MODULE - HYDRAULIC QUANTITY 29-33-02
INTERFACE (HYQUIM) Removal/Installation 401 ALL Adjustment/Test 501 ALL
TRANSMITTER - HYDRAULIC FLUID 29-33-01
QUANTITY
Removal/Installation 401 ALL
HYDRAULIC LOW PRESSURE WARNING 29-34-00
SYSTEM
Description and Operation 1 ALL General 1 Switch - Hydraulic Low 1
Pressure Warning Operation 1 SWITCH - HYDRAULIC LOW PRESSURE 29-34-01 WARNING Removal/Installation 401 ALL
SYNOPTIC - HYDRAULIC FAULT ISOLATION 29-40-00
____________________________________
Component Location 101 ALL
Component Index
Component Location
29-CONTENTS
GUN Page 13 Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
HYDRAULIC POWER - DESCRIPTION AND OPERATION
___________________________________________
1. General_______
A. Four independently operated main hydraulic supply systems are installed in the airplane to get the power necessary for the flight control and landing gear control systems. Each main supply system is related with an engine. Most of the supply system's components are found in the nacelle area above and aft of the engine. The hydraulic supply system is identified by the same number as the related engine. A mark is made with tape bands on the hydraulic lines. The bands identify the lines as part of the hydraulic system, give function, and direction of flow. Bands with color are also included for system identification. Red bands are usd for No. 1, blue for No. 2, orange for No. 3, and green for No. 4. Reservoir pressurization and central reservoir servicing connections are installed with the hydraulic supply systems.
B. An auxiliary hydraulic power source adds to the four main supply systems. An auxiliary ac hydraulic system (AUX ACMP in System 4) is installed in hydraulic supply system No. 4 to give brake pressure during towing operations.
C. An auxiliary ac hydraulic system (AUX ACMP in System 1) is installed in hydraulic supply system No. 1 to give hydraulic pressure for body steering during towing operations.
D. The condition of each primary hydraulic supply system can be monitored on the Engine Indicating and Crew Alerting System (EICAS).
2. Main Hydraulic Supply Systems_____________________________
A. The airplane has four main hydraulic supply systems. Each system operates independently. The only differences between the systems are the type of hydraulic pumps used and the fluid capacities.
(1)
Each of the systems has an engine-driven pump (EDP) that is used as the primary power source. Each system also has a demand pump that is used during operations that require large hydraulic flow. The demand pump is also used if the EDP does not operate correctly.
(2)
Systems 1 and 4 have air-driven pumps (ADP).
(3)
Systems 2 and 3 have ac motor-driven pumps (ACMP).
(4)
Systems 1 and 4 also have auxiliary ac motor-driven pumps that operate only when the airplane is on the ground.
B.
The EDP and the demand pump are installed in parallel for each system. The ADP's and EDP's are the same and are interchangeable. The EDPs will operate continuously when the engine is in operation. The pneumatic system supplies power for the ADPs. The demand pumps 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 ac ground handling bus.
C.
Most of the components of the supply system are in a module configuration as described in 29-11-00. The pneumatic components for reservoir presurization are described in 29-17-00.
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