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ACCORDING TO ELEVATION<
CLIMB SCHEDULE 7850 ft
-
CFO0204002_005
CABIN PREPRESSURIZED
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
02-04-07 CONTROLS AND INDICATIONS (Cont) TAKEOFF AND RETURN TO BASE
WITHIN 10 Min OF LIFTOFF AIRCRAFT ALTITUDE- 6000 ft
< +6000 ABOVE T/O FIELD ELEVATION
FIELD ELEVATION
T/O FIELD
CABIN DESCENDS TO
ELEVATION
T/O FIELD ELEVATION
10 Min TIME
CFO0204002_006
TAKEOFF FROM AIRFIELD ABOVE 7850 FT AND LANDING FIELD ELEVATION LESS THAN 7850 FT
During climb and cruise mode, the target for the cabin altitude will be the normal cabin pressure schedule which is below the maximum normal limit of 7850 ft for aircraft altitudes below 45 000 ft. The warning and caution thresholds will de-crease until the caution threshold reaches 8500 ft and the warning threshold reaches 9400 ft
ALTITUDE
AIRCRAFT ALTITUDE 45,000 MAX
>
500 ft MIN
-
TIME
TAKEOFF
7000 ft
CFO0204002_008
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
02-04-08
AIR CONDITIONING/PRESSURIZATION
CONTROLS AND INDICATIONS (Cont) ECS SYNOPTIC PAGE
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
02-04-09 EICAS MESSAGES
The air conditioning/pressurization system CAS messages and voice aurals are listed below. A brief explanation of each message is provided.
MESSAGE INHIBITS MEANING AURAL WARNING
CABIN ALTITUDE TO/LAND The normal cabin altitude warning is at 9400 ft When a takeoff or landing is conducted above 7850 ft, the warning is at the field elevation + 1550 ft, but limited to no higher than 14 300 ft “Cabin Altitude”
CABIN DELTA P TO/LAND The cabin differential pressure is greater than 9.2 psid or less than -0.5 psid
L (R) BLEED LEAK TO/LAND A leak has been detected in the bleed air ducting downstream of the bleed valve
PACK LEAK TO/LAND A leak has been detected in the pack ducting
TRIM AIR LEAK TO/LAND A leak has been detected in the bleed air ducting downstream of the right flow control valve, up to the precooler crossover and up to the trim air check valve
L (R) PYLON BLEED LEAK TO/LAND A leak has been detected in the engine pylon or tail cone (before shutoff valve)
AIR COND TEMP FAIL TO/LAND The automatic temperature control system has failed
AIR COND TEMP HIGH TO/LAND Excessive air temperature has been sensed in the cabin or cockpit air distribution duct
AUTO PRESS FAIL TO/LAND Both automatic pressurization modes have failed
L (R) BLEED FAIL TO/LAND The affected engine bleed air valve has failed or a temperature or pressure has exceeded limits or the sensor has failed. Under certain low thrust conditions (ground idle at high field elevations or idle with single bleed on), there may be insuffi-cient pressure to keep the bleed valve open
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