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SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 FIREWALL FUEL SHUTOFF VALVE A manual firewall fuel shutoff valve, located on the aft side of the firewall, enables the pilot to shut off all fuel flow from the fuel reservoir to the engine. The shutoff valve is controlled by a red push-pull knob labeled FUEL SHUTOFF-PULL OFF and located on the right side of the pedestal. The push-pull knob has a press-to-release button in the center which locks the knob in position when the button is released. FUEL TANK SELECTORS Two FUEL SELECTORS, one for each tank, are located on the overhead console. The selectors, labeled LEFT, ON and OFF and RIGHT, ON and OFF, mechanically control the position of the two fuel tank shutoff valves at each wing tank. When a fuel tank selector is in the OFF position, the shutoff valves in the tank are closed. When in the ON position, both shutoff valves in the tank are open, allowing fuel from that tank to flow to the reservoir. Normal fuel management is with both fuel tank selectors in the ON position. Before refueling, or when the airplane is parked on a slope, turn off one of the fuel tank selectors (if parked on a slope, turn high wing tank off). This action prevents crossfeeding from the fuller or higher tank and reduces any fuel seepage tendency from the wing tank vents. FUEL SELECTORS OFF WARNING SYSTEM A test switch, labeled TEST SWITCH, FUEL SELECT OFF - DN, is located on the lower left corner of the instrument panel. When this switch is placed in the DOWN position, the Red FUEL SELECT OFF MSG will illuminate and two warning horns will sound simultaneously indicating that the fuel selector warning circuitry is operational. FUEL BOOST PUMP SWITCH An auxiliary boost pump switch, located on the left sidewall switch and circuit breaker panel, is labeled FUEL BOOST and has OFF, NORM, and ON positions. When the switch is in the OFF position, the auxiliary boost pump is inoperative. When the switch is in the NORM position, the auxiliary boost pump is armed and will operate when fuel pressure in the fuel manifold assembly drops below 4.75 psi. This switch position is used for all normal engine operation where main fuel flow is provided by the ejector boost pump and the auxiliary boost pump is used as a standby. When the auxiliary boost pump switch is placed in the ON position, the auxiliary boost pump will operate continuously. This position is used for engine start and any other time that the auxiliary boost pump cycles on and off with the switch in the NORM position, and for all operations utilizing aviation gasoline. 7-66 U.S. 208BPHBUS-00
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION FUEL FLOW INDICATION A fuel flow indicator, located beneath the quantity indicators on both the ENGINE and SYSTEM pages, indicates the fuel consumption of the engine in pounds per hour based on Jet A fuel. The indicator measures the flow of fuel downstream of the fuel control unit just before being routed into the flow divider. The fuel flow indicator receives power from a pull-off type circuit breaker labeled F FLOW NP & NG, on the left sidewall switch and circuit breaker panel. FUEL QUANTITY INDICATIONS Fuel quantity is measured by four fuel quantity transmitters (two in each tank) and indicated by two electrically-operated fuel quantity indicators on the upper portion of the instrument panel. The fuel quantity indicators, which measure volume, are calibrated in pounds (based on the weight of Jet A fuel on a standard day). An empty tank is indicated by a red line and the letter E. When an indicator shows an empty tank, approximately 2.8 gallons remain in the tank as unusable fuel. The left and right fuel quantity indicators each receive power from a pull-off type circuit breaker. The breakers are labeled LEFT FUEL QTY and RIGHT FUEL QTY, respectively, and are located on the left sidewall switch and circuit breaker panel. WARNING Because of the relatively long fuel tanks, fuel quantity indicator accuracy is affected by uncoordinated flight or a sloping ramp if reading the indicators while on the ground. Therefore, to obtain accurate fuel quantity readings, verify that the airplane is parked in a laterally level condition, or if in flight, make sure the airplane is in a coordinated and stabilized condition. WING TANK FUEL LOW CAUTION CAS MESSAGES Two float sensors one for each wing tank will trigger the appropriate amber CAS message, L FUEL LEVEL LOW or R FUEL LEVEL LOW MSG. when the fuel in the respective tank is 25 gallons (170 lbs) or less. When the fuel quantity in each tank is less than 25 gallons (170 lbs), amber L-R FUEL LEVEL LOW CAS MSG will replace the previously displayed L or R FUEL LEVEL LOW CAS message. 208BPHBUS-01 U.S. 7-67
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CESSNA INTRODUCTION MODEL 208B G100
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CESSNA SECTION 1 MODEL 208B G1000 G
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CESSNA SECTION 2 MODEL 208B G1000 L
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SECTION 3 CESSNA EMERGENCY PROCEDUR
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SECTION 3 CESSNA ABNORMAL PROCEDURE
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CESSNA SECTION 3 MODEL 208B G1000 A
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CESSNA SECTION 4 MODEL 208B G1000 N
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CESSNA SECTION 5 MODEL 208B G1000 P
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CESSNA SECTION 6 MODEL 208B G1000 W
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SECTION 7 CESSNA AIRPLANE AND SYSTE
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CESSNA SECTION 8 MODEL 208B G1000 H
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