TABLE I
5B8
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 28-42-11 Page 401
F95280 F95290
Fuel Low Pressure Switch Installation 5B8
28-42-11 Page 402 Figure 401 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/85
5B8 Fuel Low Pressure Switch Installation
Jun 20/84 Figure 401 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 28-42-11 Page 403
E. Remove the fuel boost pump access panels for the applicable fuel tank.
F. Close the applicable fuel boost pump removal valves.
WARNING: IF BOOST PUMP REMOVAL VALVES FOR APPLICABLE TANK ARE NOT CLOSED, SIPHONING OF FUEL MAY OCCUR WHEN FUEL LOW PRESSURE SWITCH IS REMOVED.
4. Remove the Fuel Low Pressure Switch (Airplanes with low pressure switches installed on the wing leading edge beams) (Fig. 401)
A. Disconnect the electrical connector from the low pressure switch.
B. Put a small container under the low pressure switch to catch the fuel drips.
C. Disconnect the fuel line from the low pressure switch.
D. Disconnect the vent line from the low pressure switch.
E. Remove the mounting bolt, washer and nut (4 locations).
F. Remove the low pressure switch.
(1)
Remove the two unions and O-rings from the low pressure switch.
(2)
Discard the O-rings.
5. Remove the Fuel Low Pressure Switch (Airplanes with low pressure switches installed on the wing front spar) (Fig. 401)
A. Disconnect the electrical connector from low the pressure switch.
B. Put a small container under the low pressure switch to catch the fuel drips.
C. Remove the fuel low pressure switch.
(1) Discard the O-ring on the low pressure switch.
6. Install the Fuel Low Pressure Switch (Airplanes with low pressure switches installed on the wing leading edge beams) (Fig. 401)
A. Put low pressure switch on bracket or leading edge rib, with vent port forward of fuel line port.
(1)
Install new O-rings on the switch ends of the unions.
(2)
Install the unions in the low pressure switch.
B. Install the mounting bolt, washer and nut (4 locations).
C. Connect the fuel line to the low pressure switch.
D. Connect the vent line to the low pressure switch.
7. Install the Fuel Low Pressure Switch (Airplanes with low pressure switch installed on the wing front spar) (Fig. 401)
A. Install a new O-ring on the low pressure switch.
B. Install the fuel low pressure switch in the front spar.
8. Restore Airplane to Normal
A. Connect the electrical connector to the low pressure switch.
NOTE: If the electrical connectors do not mate, check the low pressure switch for the correct part number. Refer to paragraph 1.B.
B. If steps 3.E. and 3.F. were accomplished previously, open the applicable fuel boost pump removal valves and install boost pump access panels.
NOTE: Make sure that the boost pump removal valve is open before you install the boost pump access panel.
C. Remove leading edge flap locks (AMM 27-81-0/201).
WARNING: LEADING EDGE FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONS.
D. Do the test of the low pressure switch (AMM 28-42-0/501).
5B8
28-42-11 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/03
FUEL TEMPERATURE INDICATING SYSTEM - DESCRIPTION AND OPERATION
1. General
A. The fuel temperature indicating system allows the fuel temperature in tank No. 1 to be read on an indicator located on the forward overhead panel. A temperature sensing bulb is located in fuel tank No. 1. (See figure 2.)
B. The temperature bulb contains a resistance element whose resistance varies in proportion to changes in temperature. This element controls the current passing through the meter movement of the fuel temperature indicator. Power is supplied to the system through 28 volt ac bus No. 2 in the load control center (P6-2). (See figure 1.)
2. Fuel Temperature Bulb
A. The temperature bulb is an armored, bayonet locking, type bulb. It has a temperature range of -50 to +300°C. The resistance at 0°C is 90.38 ohms. The bulb is contained in a housing which projects into tank No. 1 through the rear spar. (See figure 2.) The housing is integral with the tank wall, and allows the bulb to be removed without draining the tank.
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