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SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 CAS MESSAGES (Continued) 23.GENERATOR AMPS (AMBER) - Indicates that the generator output is less than -10 amps or greater than 200 amps (-15/300 with 300 amp starter generator). 24.ALTNR AMPS (AMBER) - Indicates that the alternator output is less than -10 amps or greater than 75 amps. 25.IGNITION ON (WHITE) - Indicates electrical power is being supplied to the engine ignition system. 26.STBY PWR ON (WHITE) - Indicates that the standby alternator is generating electrical power. 27.SPD NOT AVAIL (WHITE) - Indicates that the “SPD” key was pressed on Autopilot Mode Control panel. GROUND CONTROL Effective ground control while taxiing is accomplished through nose wheel steering by using the rudder pedals; left rudder pedal to steer left and right rudder pedal to steer right. When a rudder pedal is depressed, a spring-loaded steering bungee (which is connected to the nose gear and to the rudder bars) will turn the nose wheel through an arc of approximately 15° each side of center. By applying either left or right brake, the degree of turn may be increased up to 51.5°. Moving the airplane by hand is most easily accomplished by attaching a tow bar (stowed in aft cargo compartment) to the nose gear fork axle holes. If a tow bar is not available, or pushing is required, use the wing struts as push points. Do not use the propeller blades or spinner to push or pull the airplane. If the airplane is to be towed by vehicle, never turn the nose wheel beyond the steering limit marks either side of center. If excess force is exerted beyond the turning limit, a red overtravel indicator block (frangible stop) will fracture and the block, attached to a cable, will fall into view alongside the nose strut. This should be checked routinely during preflight inspection to prevent operation with a damaged nose gear. The minimum turning radius of the airplane, using differential braking and nose wheel steering during taxi, is as shown in the Minimum Turning Radius figure. 7-22 U.S. 208BPHBUS-00
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION 208BPHBUS-00 MINIMUM TURNING RADIUS Figure 7-5 U.S. 7-23
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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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