737 AMM 飞机维护手册 液压 HYDRAULIC POWER(70)

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CAUTION:  ENSURE THAT RESERVOIR IS CLEAN, MOUNTING SURFACES ARE FREE FROM FOREIGN MATERIAL, AND THAT FOREIGN MATERIAL DOES NOT ENTER RESERVOIR OR CONNECTING HYDRAULIC LINES DURING MAINTENANCE PROCEDURES.
B.  Place reservoir in position and fasten to mounting assembly with mounting bolts.
C.  Connect electrical connector to low level warning switch (Fig. 401).
D.  Connect pump supply line between reservoir and standby pump.
E.  Connect all other hydraulic lines to reservoir.
CAUTION:  PRIOR TO INSTALLING HOSE HALF OF QUICK DISCONNECT, VISUALLY CHECK FOR DISCONNECT POPPET STRAIGHTNESS. AFTER QUICK DISCONNECT CONNECTION, CHECK THAT INDICATOR PINS ARE EXTENDED A MINIMUM OF 0.06 INCH. IF INDICATOR PINS ARE NOT PROPERLY EXTENDED, FLUID FLOW WILL BE RESTRICTED OR COMPLETELY STOPPED AND RESERVOIR AND/OR PUMP DAMAGE MAY RESULT.
IF EXCESSIVE TORQUE IS REQUIRED WHEN RECONNECTING THE TWO HALVES OF THE QUICK DISCONNECT, DISASSEMBLE THE FITTING AND CHECK FOR POPPET STRAIGHTNESS AGAIN.
F.  Service hydraulic reservoirs (Ref Chapter 12, Hydraulic Fluid Servicing).
G. Pressurize hydraulic reservoirs and check for leaks (Ref 29-09-300).
H Remove tags from pump switches.

500 
Jun 20/90  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  29-21-11 Page 403 

STANDBY HYDRAULIC SYSTEM ELECTRIC MOTOR-DRIVEN PUMP - REMOVAL/INSTALLATION
EFFECTIVITY
TASK/NYAB Installation
1. General

A.  Should replacement of the standby hydraulic pump be required due to mechanical malfunction, check the pressure filter, and the case drain filter for particles of foreign material. If an excessive amount is present, remove and clean filter bowl thoroughly and install new filter element.
B.  A container will be necessary to catch fluid from disconnected lines. Take necessary precaution to prevent spillage of fluid. Should any fluid spill on the airplane, decontaminate. See Chapter 12, Cleaning and Washing.
2.  Removal/Installation Standby Hydraulic System Motor-Driven Pump Assembly
A.  Equipment and Materials
(1)  
Skydrol Assembly Lube - MCS 352 or Fire Resistant Hydraulic Fluid -BMS 3-11

(2)  
Hydraulic Fluid -BMS 3-11

(3)  
Suitable container to catch drained fluid

B.  Prepare Hydraulic Pump Assembly for Removal
(1)  
Depressurize standby reservoir. Refer to 29-09-300, Hydraulic Reservoir Pressurization System - MP.

(2)  
Open standby hydraulic pump circuit breakers on P6-11 and P6-12 panels.

(3)  
Disconnect pump supply line at quick-disconnect at standby reservoir and drain fluid from line into container.

C.  Remove Hydraulic Pump Assembly
(1)  Disconnect hydraulic pump electrical connector (9, Fig. 401).
Feb 15/73 29-21-22 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

F87737
Standby System Hydraulic Pump Installation  501 
29-21-22  Figure 401  Oct 20/84 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(2)  
Disconnect lines from pump and install protective covers.

(3)  
Remove mounting bolts (2) and remove pump assembly from airplane.

D.  Prepare Hydraulic Pump Assembly for Installation
(1)  
Remove plug (3, Fig. 401) from lowest drain port in the pump mounting flange and install O-ring and drain fitting in open port.

(2)  
Check that pump and motor are properly assembled and that pump mounting bolts (4) are lockwired.

(3)  
Install O-rings and reducers in pump ports. Lubricate with assembly lube or hydraulic fluid.

(4)  
Fill pump approximately half full with BMS 3-11 hydraulic fluid through supply port.

E.  Install Hydraulic Pump Assembly
(1)  
Place hydraulic pump assembly in mounting position and instal1 mounting bolts (2, Fig. 401).

NOTE:  Pump mounting bolts, washers, nuts and faying surfaces must be clean to provide an adequate electrical ground.

(2)  
Connect supply line (8), pressure line (7) and case drain line (6) to hydraulic pump.

(3)  
Connect supply line at reservoir.

(4)  
Install electrical connector (9).

(5)  
Pressurize standby system reservoir (Ref 29-09-300).

(6)  
Pressurize standby system to bleed pump and check for leaks.

(a)  
Connect electrical power to airplane.

(b)  
Close standby pump circuit breakers on P6-11 and P6-12 panels.

(c)  
On the overhead panel, position system A flight control switch to STBY RUD and cycle rudder several times.
　
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