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钻石20飞机飞行手册 DA 20 Airplane Flight Manual(58)

时间:2011-10-28 13:14来源:蓝天飞行翻译 作者:admin
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The individual consumers (e.g. Radio, Fuel Pump, Position Lights, etc.) are connected in series with their respective circuit breakers.  See Figure 7.2 for an illustration of the instrument panel.
7.11.4. Voltmeter
The voltmeter indicates the status of the electrical bus.  It consists of a dial that is marked numerically from 8 - 16 volts in divisions of 2.
The scale is divided into three colored arcs to indicate the seriousness of the bus condition.
These arcs are: 
Red  for  8.0 - 11.0 volts, 
Yellow   for 11.0 - 12.5 volts, 
Green  for 12.5 - 16.0 volts, 
Redline   at 16.1 volts. 
7.11.5. Ammeter 

The ammeter indicates the charging (+) and discharging (-) of the battery.  It consists of a dial, which is marked numerically from -60 to 60 amps.
7.11.6. Generator Warning Light
The generator warning light (red) illuminates during:
- Generator failure, no output from the generator The only remaining power source is the battery (20 amps. for 30 minutes)
7.11.7. Instruments
The instruments for temperatures, pressures, and fuel quantity are connected to their respective sensors.  When the electrical resistance of a sensor changes it causes a corresponding change (needle deflection) in its respective indicator.

7.11.8. Internal Lighting
The internal lighting of the DA20-C1 is provided by a lighting module located aft of the Pilot’s head and on the centerline of the aircraft.  Included in this module are two panel illumination lights and one map light.  The switches for the lights are located on the instrument panel. There is a dimming control located on the left side of the instrument panel for adjusting the intensity of the lighting.  There is a toggle switch located beside the dimming control that controls the intensity of the Wing Flap and Trim Annunciator.  See Figure 7.8.

Care must be taken when adjusting the lights to maintain proper illumination.  The Illumination Pattern and Adjustment shows how the lights are aimed in order to provide proper panel illumination.
Aircraft equipped with supplemental lighting (MOD 32) have a Light Dimmer Module and a Glare Shield mounted Flood Light. Control of the Dimmer for backlit instruments is through the Instrument lighting potentiometer. Control of the flood light is through a potentiometer marked FLOOD.

7.12. PITOT AND STATIC PRESSURE SYSTEMS
The pitot pressure is measured on the leading edge of a calibrated probe below the left wing. The static pressure is measured by the same probe.  For protection against water and humidity, water sumps are installed within the line.  These water sumps are accessible beneath the left seat shell.
The error in the static pressure system is negligible.  For the error of the airspeed indicating system refer to Chapter 5.
The pitot static pressure probe should be protected whenever the aircraft is parked to prevent contamination and subsequent malfunction of the aircraft systems relying on its proper functioning.
 
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