565 Hydraulic Fluid Overheat Warning System Schematic
Oct 20/89 Figure 1 29-32-0
Page 1
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
HYDRAULIC FLUID OVERHEAT WARNING SYSTEM - ADJUSTMENT/TEST
1. Hydraulic Fluid Overheat Warning System Test
A. General
(1)
System B hydraulic overheat warning system is tested for electrical continuity between the overheat warning lights and the overheat switches and for proper operation and temperature settings of the switches. The overheat switches are installed in the case drain lines of system B No. 1 and No. 2 hydraulic pumps (Ref 29-32-11, Fig. 401). Temperature settings are checked by applying controlled heat to each overheat switch.
NOTE: The temperature sensor (235 +8°F) connected to the motor housing of system B hydraulic pumps (ABEX) is not considered to be a line maintenance test item and should be tested per the manufacturer's overhaul manual.
(2)
A container will be necessary to catch any fluid leakage from disconnected hydraulic lines. Should any fluid spill on the airplane, decontaminate (Ref Chapter 12, Cleaning and Washing).
B. Equipment and Materials
(1)
Temp Cal Probe Heater (attachment to Jet Cal engine analyzer) or equivalent
(2)
Suitable container for BMS 3-11
C. Test Overheat Warning System
(1)
Provide electrical power to airplane.
(2)
Check that all three indicator light circuit breakers, including section 1 and 5 circuit breakers in the P6 panel are closed.
(3)
Press-to-test both system B overheat warning lights on forward overhead panel. Both lights should illuminate.
(4)
Depressurize hydraulic reservoir system (Ref 29-09-300 MP).
(5)
Open section 1 and section 5 circuit breakers on P6 panel.
(6)
Remove electrical connector from each System B hydraulic pump.
(7)
Connect pin 7 of each electrical connector plug to ground at thermal sensor hex fitting.
(8)
Close Section 1 and 5 circuit breakers on P6 Panel.
(9)
Check that warning light illuminates.
(10)
Open section 1 and 5 circuit breakers on P6 Panel.
(11)
Remove jumper from pin 7 of electrical connector and reconnect electrical connector to hydraulic pump.
(12)
Disconnect electrical connectors from overheat switches in case drain line.
CAUTION: DO NOT ATTEMPT TO REMOVE OR INSTALL OVERHEAT SWITCHES WITH ELECTRICAL CONNECTORS ATTACHED TO SWITCH.
(13)
Remove overheat switches from case drain line and cap lines (Ref\29-32-11 R/I).
(14)
Reconnect electrical connectors to overheat switches.
(15)
Close Section 1 and 5 circuit breakers on P6 Panel.
(16)
Gradually heat each overheat switch 215 to 235°F at a rate of 5 degrees per min (+1 degree per minute). Check that corresponding warning light illuminates.
NOTE: Use Temp Cal probe heater or equivalent to apply heat.
(17)
Slowly decrease temperature to 165°F at a rate of 5 degrees per min (+1 degree per minute). Check that warning light goes out.
(18)
Open section 1 and 5 circuit breakers on P6 panel.
(19)
Disconnect electrical connectors from overheat switches and reinstall overheat switches (Ref 29-32-11 R/I).
(20)
Reconnect electrical connectors to overheat switches.
(21)
Close section 1 and 5 circuit breakers on P6 panel.
(22)
Check overheat switches for leaks (Ref 29-32-11 R/I).
(23)
Remove electrical power if no longer required.
502
Oct 20/83 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 29-32-0 Page 501
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29-32-0 Page 502 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 01/95
HYDRAULIC FLUID OVERHEAT WARNING SWITCH - REMOVAL/INSTALLATION
1. General
A. The system B overheat warning switches are installed in No. 1 and No. 2 pump case drain return lines. They are located just above the keel beam on the forward wheel well bulkhead (Fig. 401).
B. A container will be necessary to catch any fluid spilled from disconnected hydraulic lines. Should fluid spill on the airplane, the affected area must be decontaminated. Refer to Chapter 12, Cleaning and Washing.
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