C. Remove acoustic filter (Ref 29-12-101 R/I).
D. Remove pump mounting bolts.
NOTE: The two forward mounting bolts are not lockwired. Do not remove the two forward lockwired bolts that secure the mounting bracket.
Bonding jumper is attached to mounting bolt. Disengage bonding jumper from mounting bolt.
E. Remove pump from airplane.
5. Prepare Hydraulic Pump for Installation
A. Check that pump assembly is complete.
NOTE: All fittings and O-rings should be installed or supplied with the assembly and all ports capped.
B. Check that pump is full of clean BMS 3-11 hydraulic fluid.
NOTE: New pumps are partially filled with BMS 3-11. Removal of this fluid and refilling with clean hydraulic fluid is optional.
C. Check that all lockwire is intact and that pressure control adjusting screw is lockwired and sealed with a lead seal.
D. Install acoustic filter (Ref 29-12-101).
6. Install Hydraulic Pump
A. Put the pump in its mounting position.
B. Engage the bonding jumper, which is attached to the airplane structure, with the aft inboard mounting bolt on the pump.
NOTE: The mounting pad, bolt, washers, and bonding jumper must be clean to give a good electrical ground.
C. If two bonding jumpers are part of the pump assembly, engage them with a pump mounting bolt as follows:
(1)
Aft outboard bolt on the No. 1 pump.
(2)
Aft inboard bolt on the No. 2 pump.
D. Install the pump mounting bolts.
E. Safety the two aft mounting bolts with a lockwire.
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F. Connect pressure line to pump outlet.
G. Connect supply line to pump inlet and then to reservoir supply coupling.
CAUTION: WHEN INSTALLING HOSE HALF OF THE QUICK-DISCONNECT, CHECK THAT INDICATOR PINS ARE EXTENDED A MINIMUM OF 0.06 INCH. IF THE INDICATOR PINS ARE NOT PROPERLY EXTENDED FLUID FLOW WILL BE RESTRICTED OR COMPLETELY STOPPED AND RESERVOIR AND/OR PUMP DAMAGE MAY RESULT.
H. Connect case drain line. Check that hydraulic fluid is up to case drain port.
I. Install hydraulic pump electrical connector.
J. Pressurize system B reservoir (Ref 29-09-300 MP).
K. Check that reset button is RESET on ground fault protection controller located aft of P6-1 circuit breaker panel.
L. Close system B pump circuit breaker on P6-11 and P6-12 panels.
WARNING: CHECK THAT RUDDER IS CLEAR TO DEFLECT FULLY BEFORE TURNING POWER ON TO PREVENT INJURY TO PERSONNEL OR DAMAGE TO EQUIPMENT.
M. Pressurize hydraulic system B using applicable pump (Ref 29-12-0 MP).
CAUTION: IF SYSTEM B PUMP DOES NOT OPERATE WHEN SWITCH IS PLACED IN ON POSITION, SWITCH SHOULD BE IMMEDIATELY POSITIONED TO OFF AND THE PUMP AND GROUND FAULT PROTECTION SYSTEM TESTED (REF 29-12-21 A/T).
N. Cycle rudder several times to prime and bleed hydraulic pump.
O. With flight control switches ON and ground interconnect valve closed, check that system B hydraulic pressure gage on copilot's panel stabilizes between 2800 and 3100 psi.
P. Check pump and connections for leaks.
Q. Place pump switch in OFF position.
R. Service hydraulic reservoirs (Ref Chapter 12, Hydraulic Servicing).
S. Close tire burst protection screen doors.
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SYSTEM B ELECTRIC MOTOR-DRIVEN HYDRAULIC PUMP - ADJUSTMENT/TEST
1. System B Electric Motor-Driven Hydraulic Pump Test
A. General
(1) Paragraph C. tests system B hydraulic pumps, and electrical power supply to the pumps. Paragraph D. tests the ground fault protection system.
CAUTION: DO NOT OPERATE EITHER SYSTEM B PUMP MORE THAN 2 MINUTES IF THE NO. 2 (RIGHT-HAND) FUEL TANK CONTAINS LESS THAN 250 GALLONS (1675 POUNDS) OF FUEL. IN SUCH CASES WHEN THE PUMP IS OPERATED WITH LESS THAN THE MINIMUM FUEL FOR HYDRAULIC FLUID COOLING, THE PUMPS SHOULD NOT BE RETESTED UNTIL THE SYSTEM B RESERVOIR HAS RETURNED TO AMBIENT TEMPERATURE.
B. Equipment and Materials
(1) Test Equipment, Ground Fault Protection System, Hydraulic System B-F72917 -( )
C. Test Hydraulic Pump
(1)
Apply power to the No. 1 generator bus by placing either the No. 1 generator or the APU generator left switch to ON.
NOTE: Ground power cannot be used for this test.
(2) 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737 AMM 飞机维护手册 液压 HYDRAULIC POWER(58)
