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3.4 G1000 FAILURES
3.4.1 NAVIGATION INFORMATION FAILURE
If Garmin G1000 GPS navigation information is not available or invalid, utilize remaining operational navigation equipment as required.
3.4.2 PFD OR MFD DISPLAY FAILURE
1. DISPLAY BACKUP button on audio panel . . PUSH
' Automatic Entry of Display Failure
' -If the PFD and MFD have automatically entered reversionary mode, use the following ' procedure.
' (a) DISPLAY BACKUP button on audio panel . . PUSH (button will be OUT)
' NOTE ' After automatic entry of reversionary mode, the pilot must ' press the DISPLAY BACKUP button on the audio panel. After ' the DISPLAY BACKUP button has been pushed, the system ' will remain in reversionary mode even if the problem causing ' the automatic entry of reversionary mode is resolved. A ' maximum of one attempt to return to normal mode is ' approved using the following procedure.
' (b) DISPLAY BACKUP button on audio panel . . PUSH (button will be IN)
' -If the system returns to normal mode, leave the DISPLAY BACKUP button IN and ' continue.
' -lf the system remains in reversionary mode, or abnormal display behavior such as ' display flashing occurs, then return the DISPLAY BACKUP button to the OUT position.
Page 3 - 16 Rev. 5 15-Nov-2007 Doc. No. 7.01.05-E
3.4.3 AHRS FAILURE
NOTE
A failure of the Attitude and Heading Reference System (AHRS) is indicated by a removal of the sky/ground presentation and a red X and a yellow "AHRS FAILURE" shown on the PFD. The digital heading presentation will be replaced with a yellow "HDG" and the compass rose digits will be removed. The course pointer will indicate straight up and course may be set using the digital window.
1.
Use standby attitude indicator, emergency compass and Navigation Map
2.
Course ............................. set using digital window
3.4.4 AIR DATA COMPUTER (ADC) FAILURE
NOTE
Complete loss of the Air Data Computer is indicated by a red X and yellow text over the airspeed, altimeter, vertical speed, TAS and OAT displays. Some FMS functions, such as true airspeed and wind calculations, will also be lost.
1. Use standby airspeed indicator and altimeter.
Doc. No. 7.01.05-E Rev. 5 15-Nov-2007 Page 3 - 17
3.4.5 ERRONEOUS OR LOSS OF ENGINE AND FUEL DISPLAYS
NOTE
Loss of an engine parameter is indicated by a red X through the data field. Erroneous information may be identified by indications which do not agree with other system information. Erroneous indications may be determined by comparing a display with other displays and other system information.
1.
Set power based on throttle lever position, engine noise and speed.
2.
Monitor other indications to determine the health of the engine.
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本文链接地址：钻石40系列飞机维护手册 DA 40 SERIES AIRPLANE MAINTENANCE MANUAL 2(14)
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