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L/R COOL LVL The annunciation is active when engine coolant level is low.
PITOT FAIL The annunciation is active when the Pitot heater is failed.
PITOT HT OFF The annunciation is active when the Pitot heat is off.
STAL HT FAIL The annunciation is active when the stall heater is failed.
STAL HT OFF The annunciation is active when the stall heater is off.
STICK LIMIT Control stick limiting system (variable elevator stop) has failed.
L/R AUX FUEL E This annunciation can only occur when the auxiliary fuel tank system (optional) is installed. The annunciation is active when the L/R auxiliary fuel tank is empty and the FUEL TRANSFER pump is ON.
INTEG RAIM not available The annunciation is active when RAIM (Receiver Autonomous Integrity Monitor) is not available.
AHRS ALIGN: Keep Wings Level The annunciation is active when the AHRS (Attitude and Heading Reference System) is aligning.
CHECK GEAR (if installed) Landing gear is not down and locked.
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Page 7 - 62 Rev. 5 15-Nov-2007 Doc. No. 7.01.05-E
Annunciation advisory alerts on the G1000
Advisory alerts Meaning / Cause
L/R GLOW ON The annunciation is active when the glow plugs are powered.
L/R FUEL XFER The annunciation is active when fuel transfer from auxiliary to main tank is in progress.
Message advisory alerts on the G1000
Advisory alerts Meaning / Cause
PFD FAN FAIL The annunciation is active when the PFD fan is inoperative.
MFD FAN FAIL The annunciation is active when the MFD fan is inoperative.
GIA FAN FAIL The annunciation is active when the GIA fan is inoperative.
7.11 PITOT-STATIC SYSTEM
Total pressure is measured at the leading edge of a Pitot probe under the left wing. Static pressure is measured at two orifices at the lower and rear edges of the same probe. To protect against dirt and condensation there are filters in the system, which are accessible from the wing root. The Pitot probe is electrically heated.
With the alternate static valve, the static pressure in the cabin can be used as static pressure source in the event of a failure of the Pitot-static system.
' If an Autopilot System is installed, additional static sources may be installed.
7.12 STALL WARNING SYSTEM
The lift detector of the DA 42 is located on the front edge of the left wing below the wing chord line. It is supplied electrically and provides a stall warning, before the angle of attack becomes critical. The stall status is announced to the pilot by a continuous sound in the cockpit.
The lift detector vane, the mounting plate and the complete housing are heated to prevent icing. Heating is engaged together with the Pitot heating.
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本文链接地址:钻石42飞机飞行手册 DA 42 Airplane Flight Manual(114)
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