29-CONTENTS
BEJ Page 6 Jul 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL CHAPTER 29 - HYDRAULIC POWER TABLE OF CONTENTS
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Subject
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HYDRAULIC FLUID QUANTITY
INDICATING SYSTEM
Description and Operation General Switch - Standby Low Quantity Transmitter and Indicator -
Fluid Quantity Trouble Shooting INDICATOR - HYDRAULIC FLUID
QUANTITY Removal/Installation SWITCH - STANDBY HYDRAULIC SYSTEM RESERVOIR LOW QUANTITY Removal/Installation TRANSMITTER/INDICATOR -
HYDRAULIC FLUID QUANTITY Removal/Installation Inspection/Check
PUMP LOW PRESSURE WARNING SYSTEM Description and Operation
General Adjustment/Test SWITCH - HYDRAULIC SYSTEMS A AND
B EDP LOW PRESSURE Removal/Installation SWITCH - HYDRAULIC SYSTEMS A AND B EMDP LOW PRESSURE Removal/Installation SWITCH - STANDBY SYSTEM EMDP LOW PRESSURE Removal/Installation
Chapter SectionSubject_______ Page____ Effectivity___________
29-33-01
1 111 ALL
29-33-11 101 ALL
29-33-21 401 ALL
29-33-12 401 ALL
29-34-0129-34-11 401 601 1 1501 ALLALLALLALL
29-34-21 401 ALL
29-34-31 401 ALL
401 ALL
29-CONTENTS
BEJ Page 7 Jul 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
1.
2.
3.
4.
A
737-300/400/500MAINTENANCE MANUAL
HYDRAULIC POWER - DESCRIPTION AND OPERATION
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General (Fig. 1)
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A. Three separate hydraulic systems provide fluid at 3000 psi to operate the airplane systems shown in figure 1. The hydraulic systems are identified as system A, system B and standby.
B. The standby hydraulic system provides reserve power for critical systems.
C. A ground servicing system fills all hydraulic reservoirs from one location.
D. The indicating systems provide information for crew monitoring of the
operating conditions of each hydraulic system.Main Hydraulic Systems (Fig. 2)
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A. The A and B system components are located on each engine and within the main gear wheel well forward section. The pressure source for each of the A and B systems consists of one engine driven pump (EDP) and one electric motor driven pump (EMDP). The EDP is directly coupled to the engine accessory gearbox and runs all the time that the engine is running. When an ELEC pump switch is ON, the respective EMDP runs all the time.
B. Each hydraulic system has a fluid reservoir which is pressurized by air from the pneumatic system. Filter modules clean the fluid after being pressurized or after passing through the pump case drain and after returning from user systems. Heat exchangers in the fuel tanks cool the pump case drain fluid before it returns to the reservoir.
C. Ground hydraulic power connections are provided on the aft bulkhead of
the left and right air conditioning bays.Standby Hydraulic System (Fig. 2)
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A. The standby system components are located on the keel beam in the main gear wheel well. The pressure source for the standby system is an eletric motor driven pump (EMDP). The standby EMDP is turned on automatically if system A or B fails during takeoff or landing, or it can be turned on manually by operating the FLT CONTROL A, FLT CONTROL B, or the ALTERNATE FLAPS switches on the overhead flight control panel P5.
Power Transfer Unit (Fig. 2)
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A. The power transfer unit (PTU) is located on the keel beam just forward of the standby reservoir. The PTU operates if system B EDP pressure is lost, flaps are not up but less than 15° and airplane is in the air. The PTU consists of a hydraulic motor connected to a hydraulic pump. The motor is driven by system A hydraulic pressure and the pump supplies pressure to the leading edge devices using system B hydraulic fluid. There is no fluid interchange between the A and B hydraulic systems.
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