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GENERAL.
The fuel system components covered in this section consist of fuel cells. fuel selector valves,fuel filter and electric fuel pumps. Each wing contains a fuel cell, having a capacity of 55 U.S. gallons, for a total capacity of 110 U.S. gallons.
This chapter also provides instructions for removal, repair, cleaning, reassembly and testing of repairable components of the fuel system.
The aircraft is approved for operation with an anti-icing additive in the fuel. When an anti-icing additive is used it must meet the specification MIL-I-27686, must be uniformly blended with the fuel while refueling, must not exceed 0.15% by volume of the refueled quantity and to ensure its effectiveness should be blended at not less than 0.10% by volume. One and one-half liquid oz’s. per ten gallons of fuel would fall within this range. A blender supplied by the additive manufacturer should be used. Except for the information contained in this section, the manufacturer's mixing or blending instructions should be carefully followed.
— CAUTION —
ASSURE THAT THE ADDITIVE IS DIRECTED INTO THE FLOWING FUEL STREAM. ADDITIVE FLOW SHOULD START AFTER AND STOP BEFORE FUEL FLOW. DO NOT PERMIT CONCENTRATED ADDITIVE TO COME INTO CONTACT WITH THE AIRCRAFT PA I N T E D S U R FACES OR THE INTERIOR SURFACES OF THE FUEL TA N K S . SOME FUELS HAVE ANTI-ICING ADDITIVES PRE-BLENDED IN THE FUEL AT THE REFINERY. NO FURTHER BLENDING SHOULD BE PERFORMED. FUEL ADDITIVE MUST NOT BE USED AS A SUBSTITUTE FOR PREFLIGHT DRAINING OF THE FUEL SYSTEM DRAINS.
DESCRIPTION.
An independent fuel system is incorporated into each wing permitting each engine to operate from its own fuel supply. However, the two systems are interconnected by means of a crossfeed that will permit fuel from one cell to be drawn by the opposite engine in the event of an emergency.
Fuel cells are installed in the aft nacelles and consists of bladder type tanks.
Fuel pressure and fuel flow for each system are indicated on their respective gauges located in the instrument panel. A fuel quantity gauge for each system, also located in the instrument panel, indicates the amount of fuel remaining as transmitted by electric fuel quantity sending units located in the wing tanks.
Fuel for each engine is drawn through a finger screen located in the fuel tank to a selector valve. From the selector valve, the fuel goes through a fuel filter to the electric pump and into the engine driven pump which forces the fuel to the carburetor.
TROUBLESHOOTING.
Chart 2801, lists troubles which may occur in the mechanical or electrical portions of the fuel system, the probable cause and a suggested remedy. When troubleshooting, first check from the fuel supply or power source to the item affected.
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Figure 28-1. Fuel System Installation
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CHART 2801. TROUBLESHOOTING (FUEL SYSTEM)
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CHART 2801. TROUBLESHOOTING (FUEL SYSTEM)
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STORAGE.
FUEL CELLS.
REMOVAL OF FUEL CELLS. (Refer to Figure 28-2.)
1.
Turn the fuel selector to the off position and drain the fuel cell.
2.
Remove the access covers from the top and side of the nacelle, also from underside of wing at rear of nacelle.
3.
Reaching through the side access panel loosen the clamps and disconnect the fitting at the vent line.
4.
Reaching through the access panel at the bottom rear nacelle. disconnect the clamp to the finger strainer.
5.
Disconnect the wires from the sender unit; remove the bolts that secure the sender and carefully draw the sender with its gasket from the cell. Note the installed position of the sender.
6.
Remove the bolts from the nut rings on the cell.
7.
Reaching through the rear access hole, gently separate the velcro type fasteners holding the fuel cell to the surrounding structures.
8.
Place tape or other protective material around the cell access opening to prevent damage to the cell when removing.
INSTALLATION OF FUEL CELLS. (Refer to Figure 28-2.)
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