曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

inhibitor is used and the Cold Weather Operations procedures in FCOM, Vol. 1 are
followed.
7. The in flight re-start envelope is defined in Figure 05-32-01 of this manual
8. Minimum oil pressure varies with engine speed. Maximum allowable oil pressure
increases with engine speed and with low oil temperature
9. A minimum oil temperature of 5 °C is required to operate engines above ground idle
power. Between 5 and 14 °C, the engines may be operated from idle up to but not
including CLB power.
LIMITATIONS
02-06-02 Airplane Flight Manual DOT Approved Aug 16/2005
CSP 100-1 REV 4
POWERPLANT LIMITATIONS (Cont)
ENGINE START:
Three consecutive engine start cycles may be conducted, followed by a cooling
period of 15 minutes, prior to additional starts and motoring.
The engine must be motored for 30 seconds after an aborted start.
For engine ground starting altitude and temperature limits, refer to the
following chart:
Ground Start Envelope
Figure 02-06-02
For aircraft 20006 thru 20033 not incorporating Service Bulletin 100-52-05
(Replacement of Passenger Door Telescopic Struts for Improved Cold Weather
Operation) the following limitation applies:
Operation is prohibited if the airplane, with engines shut down, is exposed to
a ground ambient temperature of -20 °C (-4 °F) or below for a period of more
than 2 hours, unless an approved procedure is used to warm the airplane
following this exposure.
Fuel system icing inhibitor must be used when fuel temperature is below -20 °C
(-4 °F) (for takeoff only), unless cold weather procedures are followed.
ENGINE CRANKING:
The engine can be motored (cranked) for up to 5 minutes, followed by a cooling
period of 15 minutes prior to additional starts or motoring.
OIL
Oils conforming to Honeywell specification EMS 53110, Type II are
approved.
THRUST REVERSERS
Limit thrust reverser system use to ground operations on paved surfaces.
Do not attempt to deploy thrust reversers in flight.
Do not use thrust reversers to back up the aircraft.
Do not use thrust reversers for touch-and-go landings.
Reverse thrust above idle reverse is prohibited below 40 KIAS.
0
5000
10000
15000
-20 -10 0 20 30 40 50
OAT (°C)
PRESSURE ALTITUDE (ft)
-2000
10
Ground Start Envelope
-40 -30
EFFECTIVITY
LIMITATIONS
DOT Approved Feb 08/2006 Airplane Flight Manual 02-06-03
REV 5 CSP 100-1
AUXILIARY POWER UNIT (APU) LIMITATIONS
APU TYPE
Honeywell 36-150BD auxiliary power unit.
MAXIMUM ALTITUDE
APU Operation ......................................................................37 000 ft.
APU GEN...............................................................................30 000 ft.
Bleed air for Engine Start .......................................................20 000 ft.
For aircraft 20001, 20002, 200101 and subsequent, and aircraft 20003 thru
20100 incorporating Service Bulletin 100-21-05 the following applies:
Bleed air for ECS ........................................................................20 000 ft.
For aircraft 20003 thru 20100 not incorporating Service Bulletin 100-21-05
the following applies:
Bleed air for ECS ........................................................................15 000 ft.
Do not use the APU to start the left engine on the ground above 9000 ft.
Operation of the APU during fluid de-icing/anti-icing is prohibited.
Do not take off with an APU SHUTDOWN (A) CAS displayed without conducting
an inspection. If the APU automatically shuts down due to an APU
failure, a visual inspection of the unit must be conducted prior to flight.
APU START
Delay starting the APU for 5 minutes after application of anti-icing fluid near
the APU area.
The APU may be started up to an altitude of 30 000 ft (14 000 ft on the ground).
The APU starter is limited to 30 seconds continuous cranking time.
Do not start the APU above 300 KIAS.
Three start attempts may be made, each followed by a one-minute cooling
period. After the third start attempt, there must be a 20-minute cooling period.
Two more start attempts may then be made. No further attempts may be made
for at least 40 minutes. Six successful starts may be made at 10 minute intervals
with a one hour waiting period prior to additional start attempts.
APU OPERATION
The EICAS system is designed to show system status with specified colors.
The maximum and minimum limits are indicated in red.
The maximum APU RPM is 110%.
The maximum APU EGT is:
1024 °C for start
714 °C for normal operations.
EFFECTIVITY
EFFECTIVITY
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：Bombardier_Challenger_Global_00-Limitations(10)