HYDRAULIC FLUID OVERHEAT WARNING SYSTEM............................................. 29-32-0 Description and Operation Adjustment/Test
Hydraulic Fluid Overheat Warning Switch ............................................................... 29-32-11 Removal/Installation
HYDRAULIC FLUID QUANTITY INDICATING SYSTEMS ........................................ 29-33-0 Description and Operation Trouble Shooting
Fluid Quantity Transmitter........................................................................................ 29-33-11 Removal/Installation Inspection/Check
Standby Hydraulic System Reservoir Low Level Warning Switch........................... 29-33-21 Removal/Installation
System B Hydraulic Reservoir Low Level Warning Switch...................................... 29-33-31 Removal/Installation
HYDRAULIC PUMP LOW PRESSURE WARNING SYSTEMS................................. 29-34-0 Description and Operation Adjustment/Test
.[1] Airplanes with 65-44571-xx Heat Exchanger
.[2] Airplanes with S271N401-x Heat Exchanger
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Contents 29 Page 6 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 01/96
HYDRAULIC POWER - DESCRIPTION AND OPERATION
1. General
A. Hydraulic fluid at 3000 psi pressure, is supplied to the hydraulically-operated airplane systems by three separate and independent power systems. (See figure 1.) The power systems are designated as Hydraulic System A, Hydraulic System B and Standby Hydraulic System. Hydraulic fluid is supplied from three pressurized reservoirs, one for each power system. System A receives pressure from two engine-driven pumps installed on engines No. 1 and No. 2. System B receives pressure from two electric motor-driven pumps installed in the wheel well area. The standby system receives pressure from one electric motor-driven pump installed on the keel beam between the wheel wells. The hydraulic power system reservoirs are serviced at the hydraulic fluid filling station in the right wheel well. Refer to Chapter 12, Hydraulic Fluid Servicing.
B. Hydraulic system A supplies hydraulic power to the ground spoilers, inboard flight spoilers, ailerons, leading edge flaps and slats, trailing edge flaps, landing gear, nose wheel steering, elevators, rudder, thrust reverser, and main wheel inboard brakes. Refer to 29-11-0, Hydraulic System A.
C. Hydraulic system B supplies hydraulic power to the ailerons, elevators, outboard flight spoilers, rudder, and main wheel outboard brakes. Refer to 29-12-0, Hydraulic System B.
D. The standby hydraulic system supplies power to the rudder and the leading edge flaps and slats. Refer to 29-21-0, Standby Hydraulic System.
E. The hydraulic ground servicing system is provided to fill a hydraulic reservoir from one location. Refer to 29-09-200, Hydraulic Ground Servicing System.
F. The hydraulic reservoir pressurization system is provided to ensure a positive supply of hydraulic fluid to the pumps and to prevent foaming in the reservoirs. Refer to 29-09-300, Hydraulic Reservoir Pressurization System.
G. System A, system B and standby hydraulic system components located in the forward wheel well area are protected by three wire mesh shield panels. These shields are installed to protect hydraulic components, considered to be critical for minimum safe operating limits, against the effects of a tire bursting after takeoff and retraction of the landing gear. The shield panels are hinged and locked in place by mechanical latches and allow access to hydraulic components for maintenance.
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Hydraulic Power Distribution 545
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
2. Modular Units
A. Modular units are used in the hydraulic power systems to manifold hydraulic fluid to various easily replaceable cartridge type components. This allows component removal without disrupting tube connections. For a description of individual modular units, refer to the applicable hydraulic system.
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