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SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000 AIRSPEED INDICATIORS The Garmin PFDs are the primary sources of airspeed information. Standby airspeed information is depicted by a mechanical indicator calibrated in knots, connected to the left pitot-static system. Limitation and range markings (in KIAS) match the markings on the PFD as listed in Section 2, Limitations. The standby airspeed indicator is a true airspeed indicator and is equipped with a knob which works in conjunction with the airspeed indicator dial in a manner similar to the operation of a flight computer. To operate the indicator, first rotate the knob until pressure altitude is aligned with outside air temperature in degrees Centigrade. To obtain pressure altitude, momentarily set the barometric scale on the altimeter to 29.92 and read pressure altitude on the altimeter. Be sure to return the altimeter barometric scale to the original barometric setting after pressure altitude has been obtained. Having set the knob to correct for altitude and temperature, read the true airspeed shown in the window by the indicator pointer. For best accuracy, the indicated airspeed should be corrected to calibrated airspeed by referring to the Airspeed Calibration chart in Section 5, Performance. Knowing the calibrated airspeed, read true airspeed in the window opposite the calibrated airspeed. VERTICAL SPEED INDICATION The vertical speed indication on the PFDs depict airplane rate of climb or descent in feet per minute. The pointers are actuated by atmospheric pressure changes resulting from changes of altitude as supplied by the static sources. ALTIMETER (STANDBY INSTRUMENT PANEL) Airplane altitude is depicted by a barometric type altimeter. A knob near the lower left portion of the indicator provides adjustment of the instrument's barometric scale to the current altimeter setting. 7-92 U.S. 208BPHBUS-00
CESSNA SECTION 7 MODEL 208B G1000 AIRPLANE AND SYSTEMS DESCRIPTION VACUUM SYSTEM AND INSTRUMENTS A vacuum system (see Typical Vacuum System figure) provides the suction necessary to operate the standby attitude indicator. Vacuum is obtained by passing regulated compressor outlet bleed air through a vacuum ejector. Bleed air flowing through an orifice in the ejector creates the suction necessary to operate the indicator. The vacuum system consists of the bleed air pressure regulator, a vacuum ejector on the forward left side of the firewall, a vacuum relief valve and vacuum system air filter on the aft side of the firewall, and the standby attitude indicator. ATTITUDE INDICATOR (Standby Instrument Panel) Standby attitude information is depicted by a vacuum-driven attitude indicator. Bank attitude is presented by a pointer at the top of the indicator relative to the bank scale which has index marks at 10°, 20°, 30°, 60°, and 90° either side of the center mark. Pitch and roll attitudes are presented by a miniature airplane superimposed over a symbolic horizon area divided into two sections by a white horizon bar. The upper blue sky and the lower ground area have arbitrary pitch reference lines useful for pitch attitude control. A knob at the bottom of the instrument is provided for inflight adjustment of the miniature airplane to the horizon bar for a more accurate flight attitude indication. LOW-VACUUM WARNING FLAG The standby attitude indicator includes an orange low-vacuum warning flag (GYRO) that comes into view when the vacuum is below the level necessary for reliable gyroscope operation. WARNING The orange low-vacuum warning flag (gyro) is the only indication of the loss of the vacuum system. 208BPHBUS-00 U.S. 7-93
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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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