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Figure 1
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REPLENISHING
DESCRIPTION AND OPERATION
1. GENERAL
The procedures concern the following fluids :
- fuel - refer to 12-11-00,
- oil - refer to 12-12-00,
- hydraulic - refer to 12-13-00,
- gas - refer to 12-14-00,
- refrigerant (option) - refer to 12-15-00,
1 - oxygen (option) - refer to 12-16-00.
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FUEL
DESCRIPTION AND OPERATION
1. GENERAL
Before the first flight of the day and after each refueling, use the fuel sampler and drain fuel from the fuel tank drains and the fuel filter drain to determine if contaminants are present, and the aircraft has been fueled with the proper grade and type of fuel.
The L.H. and R.H. wing fuel tanks are gravity filled through the filler port located on top of each wing. Procedures for filling both wing tanks are identical - refer to 12-11-01.
The fuel tanks are drained through the draining valves - refer to 12-11-02.
The tanks must be ventilated prior to any operation on the tanks - refer to 12-11-03.
2. FUEL TANK CAPACITY
WARNING : REFUEL THE TANK AFTER EACH FLIGHT AND KEEP FUEL TANKS FULL TO MINIMIZE CONDENSATION IN THE TANKS, RESPECTING WEIGHT AND BALANCE LIMITS.
Capacity of each tank : 44.4 U.S. Gal. (168 litres)
Total usable quantity : 86.2 U.S. Gal. (326 litres)
3. APPROVED FUEL
100 LL grade aviation fuel (Blue) (TB 01-901 A)
100 grade aviation fuel (Formerly 100 / 130) (Green) (TB 01-901 B).
CAUTION : NEVER FLY THE AIRCRAFT WITH CONTAMINATED (WATER, SAND, RUST, DUST...) OR UNAPPROVED FUEL.
NOTE : Isopropyl alcohol (TB 10-002) or ethylene glycol monomethyl ether (TB 10-901) may be added to the fuel supply in quantities not exceeding 1 % or 0.15 %, respectively, of the total volume. Refer to "Fuel Additives" Paragraph 4. for additional information.
4. FUEL ADDITIVES (Figure 1)
Strict adherence to recommended preflight draining instructions as described in Section 4 of the Pilot's Operating Handbook will eliminate free water accumulations from the tank sumps. While small amounts of water may still remain in solution in the gasoline, it will normally be consumed and go unnoticed in the operation of the engine.
One exception to this can be encountered when operating under the combined effect of the use of certain fuels, with high humidity conditions on ground followed by flight at high altitude and low temperature. Under these unusual conditions, small amounts of water in solution can precipitate from the fuel stream and freeze in sufficient quantities to induce partial icing of the engine fuel system.
　
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