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The only exception to this is for engines without the altitude compensating fuel pump, operating at very high altitudes, where the low air density may require leaning to maintain satisfactory engine operation.
C. Full Throttle
When operating at full throttle, the mixture must be set at FULL RICH. This applies to take-off, balked landings and climb.
The only exception is for engines without the altitude compensating fuel pump the mixture should be leaned as actual power falls below 75% of maximum rated power, as may be the case in an extended climb (reference Section 5.3.2, Cruise performance).
NOTE
All adjustment of the mixture control should be done in small increments.
7.9.4. Propeller
The propeller is a fixed pitch Sensenich wood propeller.
7.9.5. Lubricating
CAUTION
NEVER OPERATE THE ENGINE WITH THE OIL FILLER CAP REMOVED. OBSERVE NORMAL PROCEDURES AND LIMITATIONS WHILE RUNNING ENGINE.
The engine has high pressure wet sump lubrication. The oil is pumped by a mechanical, engine driven pump. An oil dipstick indicates the level of oil in the tank. The dipstick is marked for US quarts.
With the engine stopped, check the oil level on the dipstick. The oil level must be between the 6 US quarts and 4 US quart level as indicated by the markings on the dip stick. See Figure 7.5, Oil System Schematic Diagram.
Figure 7.5. Oil System Schematic Diagram
7.10. FUEL SYSTEM
The aluminum tank is located behind the seats, below the baggage compartment. The capacity is specified in Section 2 of this manual. The tank filler on the left side of the fuselage behind the canopy is connected to the tank with a rubber hose. A grounding stud is located on the under side of the fuselage near the trailing edge of the left hand wing. The aircraft must be grounded prior to any fueling operation.
The tank vent line runs from the filler neck through the fuselage bottom skin to the exterior of the airplane. The vent line is the translucent plastic hose adjacent to the left wing root. The vent line must be clear for proper fuel system operation. The tank has an integral sump which must be drained prior to each flight, by pushing up on the brass tube which protrudes through the underside of the fuselage, forward of the trailing edge of the left hand wing.
Two outlets with finger filters, one left and one right, are installed at the bottom of the tank (see Figure 7.6). Fuel is gravity fed from these outlets to a filter bowl (gascolator) and then to the electric fuel pump. The filter bowl must be drained prior to each flight, by pushing up on the black rubber tube that protrudes through the underside of the fuselage, adjacent to the fuel tank drain. The electric fuel pump primes the engine for engine starting (Prime ON) and is used for low throttle operations (Fuel Pump ON). When the pump is OFF, fuel flows through the pump's internal bypass. From the electric pump, fuel is delivered to the engine's mechanical fuel pump by the fuel supply line. Fuel is metered by the fuel control unit and flows via the fuel distribution manifold to the injector nozzles.
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