500 System B Hydraulic Pump Acoustic Filter Installation
May 01/99 Figure 401 (Sheet 2) 29-12-101
Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
HYDRAULIC GROUND POWER MODULAR UNIT - REMOVAL/INSTALLATION
1. General
A. A container will be necessary to catch fluid from the modular unit and disconnected hydraulic lines. Should any fluid spill on the airplane, decontaminate. Refer to Chapter 12, Cleaning and Washing.
2. Equipment and Materials
A. Skydrol Assembly Lube -MCS 352 or Fire Resistant Hydraulic Fluid -BMS 3-11
3. Remove Ground Power Modular Unit
A. Gain access to modular unit by opening the air conditioning duct access door on right side of airplane.
B. Depressurize hydraulic system B. Refer to 29-12-0, Hydraulic System B -MP.
C. Depressurize hydraulic reservoirs. Refer to 29-09-300, Hydraulic Reservoir Pressurization -MP.
D. Disconnect lines from modular unit (Fig. 401).
E. Cap open lines and plug ports to prevent contamination.
F. Remove mounting bolts and remove modular unit.
4. Install Ground Power Modular Unit
A. Lubricate O-rings and threaded fittings with assembly lube or hydraulic fluid.
B. Install check valve and O-ring in outlet port of modular unit (Fig. 401).
C. Install union and O-ring in inlet port.
D. Place modular unit in mounting position and install mounting bolts.
E. Connect hydraulic lines to inlet and outlet ports.
F. Check that filter bowl is tight and lockwired.
G. Pressurize hydraulic system B and check for leaks at check valve (Ref 29-12-0).
H. Close access door.
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29-19-100 Page 401
F87664
Hydraulic Ground Power Modular Unit Installation 500
29-19-100 Figure 401 May 15/67
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
HYDRAULIC GROUND POWER MODULAR UNIT FILTER - UNIT SERVICING
1. General
A. The ground power modular unit filter bowl should be removed at regular intervals and the element checked for contamination. If excessive contamination exists, the element should be replaced.
B. A container will be necessary to catch fluid when removing the modular unit filter bowl. Should any fluid spill on the airplane, decontaminate. Refer to Chapter 12, Cleaning and Washing.
2. Equipment and Materials
A. Skydrol Assembly Lube - MCS 352 or Fire Resistant Hydraulic Fluid - BMS 3-11
3. Remove Ground Power Modular Unit Filter Element
A. Gain access to modular unit by opening air conditioning duct access door on right side of airplane.
B. Remove filter bowl with filter element (Fig. 301).
C. Dispose of element and clean filter bowl.
Install Ground Power Modular Unit Filter Element
A. Lubricate 0-rings and threaded fittings with assembly lube or hydraulic fluid.
B. Insert backup ring and O-ring in groove inside upper end of filter element (Fig. 301).
C. Install backup ring, O-ring and backup ring in groove in filter head.
D. Place element in filter bowl and screw into filter head.
E. Torque filter bowl 50 to 75 pound-inches and install safety wire.
F. Close access door.
500
Feb 15/73 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 29-19-111 Page 301
F87681
Ground Power Modular Unit Filter Servicing 500
29-19-111 Figure 301 May 15/67
Page 302
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
STANDBY HYDRAULIC SYSTEM - DESCRIPTION AND OPERATION
1. General
A. The standby hydraulic power system (Fig. 1) operates only on demand, and supplies fluid under pressure of 3000 psi for alternate operation to the standby rudder, the leading edge flaps and slats and thrust reverser.
B. The standby hydraulic system includes the equipment necessary to store, pressurize, deliver, control, monitor and filter the hydraulic fluid to operate the systems supplied by the standby system (Fig. 2). Hydraulic fluid for the standby system is stored in a pressurized reservoir. One variable displacement electric motor-driven pump supplies fluid to systems upon demand. Pump operation is controlled by either the RUDDER standby control switch, or the ALTERNATE FLAP control switch. Refer to Chapter 27, Rudder Hydraulic Control System and Leading Edge Flaps and Slats System. A filter in the pressure line from the pump filters the fluid before it enters the various systems. A pressure switch in the pressure line from the pump is connected to a low pressure indicator light on the pilots' overhead panel. A pressure relief valve protects the system against damage by abnormally high pressures. A pump case drain filter in the pump return line is provided to detect incipient pump failures and to filter all standby return fluid before it enters the systems.
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