TANK AND COMPENSATOR UNIT BUSSING PLUG - REMOVAL/INSTALLATION
1. General
A. There are three tank and compensator unit bussing plugs, one for each fuel tank. The removal/installation procedures are the same, only the physical location is different. Two plugs are installed on the front spar and one on the rear spar in the wheel well area (Fig. 401).
2. Equipment and Materials
A. Petrolatum - VV-P-236 (Ref 20-30-21)
B. Aliphatic Naphtha (cleaning solvent) - TT-N-95 (Ref 20-30-31)
C. Leading Edge Flap Actuator Locks - F80048-89 (Preferred), F80048-90 (Preferred), F80048-84 (Alternate), and F80048-36 (Alternate)
3. Remove Bussing Plug (Fig. 401)
A. For front spar plug, extend flaps and install leading edge flap locks (Ref 27-81-0, MP).
WARNING: REFER TO 27-81-0, MP FOR LOCK INSTALLATION PROCEDURE. FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL.
B. Open GRD FUELING and FUEL QTY circuit breakers on aft overhead panel P6.
C. Disconnect electrical connector from face of plug. Ensure that circuit breakers opened in step
3.B. remain open as long as plug is open circuited.
CAUTION: DO NOT LEAVE ELECTRICAL POWER ON WITH CONNECTOR DISCONNECTED. OPEN CIRCUITED FUEL QUANTITY UNITS DRIVE QUANTITY INDICATOR POINTER AGAINST STOP, AND CONTINUED RUNNING WILL DAMAGE INDICATOR CLUTCH.
D. Remove six mounting bolts attaching plug to receptacle, discard seal washers, and, while exercising care, remove plug from receptacle.
CAUTION: BE EXTREMELY CAREFUL WITH RECEPTACLE PINS AND/OR SOCKETS. THE RECEPTACLE IS A PART OF THE FUEL TANK WIRING HARNESS ASSEMBLY. DAMAGE TO THE RECEPTACLE WILL RESULT IN THE REMOVAL OF THE COMPLETE HARNESS ASSEMBLY.
4. Install Bussing Plug
A. Clean machined surface on back of plug and seal contacting surface around receptacle with cleaning solvent. Wipe dry with a clean lint-free cloth.
B. Fit a new O-ring seal in machine groove and carefully engage contact pins of plug with pin sockets in bulkhead receptacle. Observe caution of step 3.D.fc
500
May 01/00 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 28-41-41 Page 401
C. Coat new seal washers and threads of mounting bolts with petrolatum.
D. Install plug mounting bolts, using one each thin washer and seal washer under each bolt head (Fig. 401). Tighten bolts evenly to a torque range of 40 to 50 pound-inches.
E. Connect electrical connector to bussing plug. For front spar plug, remove leading edge flap locks and retract leading edge flaps (Ref 27-81-0 MP).
WARNING: LEADING EDGE FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL.
F. Check operation of fuel quantity indicating system and adjust if necessary (Ref 28-41-0 A/T or 28-41-05 A/T).
G. Close GRD FUELING and FUEL QTY circuit breakers on aft overhead panel P6.
Tank Unit and Compensator Unit Bussing Plug Installation 508
28-41-41 Figure 401 Oct 20/86
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
520 Tank Unit and Compensator Unit Bussing Plug Installation
Nov 01/75 Figure 401 (Sheet 2) 28-41-41
Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
FUEL QUANTITY INDICATOR - REMOVAL/INSTALLATION
1. Remove Fuel Quantity Indicator
A. Open QTY and EP GRD FUELING circuit breakers on circuit breaker panel P6.
B. Loosen clamp screw of applicable indicator and withdraw indicator from panel.
WARNING: MAKE SURE EACH ELECTRICAL CONNECTOR HAS A TAG TO IDENTIFY THE CORRECT ELECTRICAL CONNECTOR INSTALLATION LOCATION TO THE INDICATOR BEING REMOVED. CROSS-CONNECTION OF THE ELECTRICAL CONNECTORS CAN CAUSE THE AIRPLANE SYSTEM TO MALFUNCTION AND THE LOSS OF SAFE FLIGHT.
C. Disconnect electrical connector at indicator and attach a tag to identify the correct electrical connector installation location to the indicator being removed.
2. Install Fuel Quantity Indicator
A. Check side of indicator to be installed for presence of inked stamp adjustment setting values.
(1)
If adjustment setting values are on indicator, compare with these on indicator which was removed. They should be identical.
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