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NOTE: The oil level indication lights on the refuel defuel panel are for reference only. If the CHECK OIL light on the refuel defuel panel is illuminated, visually check the oil tank sight glass for dispatch ability.
CFO1801002_020
ENGINE NACELLE OIL LEVEL SIGHT GAGE REFUEL DEFUEL CONTROL PANEL
ENGINE OIL TEMPERATURE
Excessively high engine oil temperatures are displayed as L (R) ENG OIL TEMPERATURE HIGH (C) CAS message.
Sep 14/2005 Flight Crew Operating Manual Volume 2 REV 4 CSP 100-6
18-01-11
POWERPLANT
ENGINE OIL SYSTEM (Cont) ENGINE LUBRICATION SCHEMATIC
TANK PRESSURIZATION
LEGEND
VENT
FUEL
OIL
CFO1801002_022
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
18-01-12 ENGINE BLEED AIR SYSTEM
DESCRIPTION
The engine bleed air system provides intermediate pressure (IP) air to the environmental control system and the opposite engine air turbine starter. It provides high pressure (HP) air to the wing and engine anti-icing systems.
The integrated air system management controller (IASC) controls bleed-air extraction from the engines. IASC 1 supports L BLEED and IASC 2 supports R BLEED functions.
Bleed-air is also extracted from the compressor by the surge bleed valves to regulate airflow through the engine core and is controlled by the FADEC.
L and R bleed-air selection, ON or OFF, is accomplished via the AIR COND/BLEED panel on the center pedestal. A cross-bleed valve is installed between the left and right pneumatic ducts, that can be opened automatically or manually by press-ing the XBLEED push button, to provide bleed-air for engine starting. The APU is the normal source of bleed-air that is used for engine starting.
COMPONENTS AND OPERATION
Engine bleed-air components consists of a bleed duct, intermediate pressure valve (IPV) and intermediate check valve.
Engine bleed-air duct assembly directs compressor bleed-air to the common bleed manifold that is located in the aft equip-ment bay. The engine compressor supplies bleed-air to operate the aircraft pneumatic system.
The nacelle bleed-air ducts are monitored for bleed-air leakage by the engine fire detection system.
Refer to Chapter 2, Air Conditioning and Pressurization, and Chapter 14, Ice and Rain Protection for more discussion on
the bleed air system.
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
18-01-13 ENGINE STARTING SYSTEM
DESCRIPTION
The AS907-1 turbofan engine is equipped with an air turbine starter (ATS) and starter control valve. The start system is designed to achieve assisted ground starts, assisted inflight starts, and windmill inflight starts. Assisted starting can be ac-complished with bleed air from the APU, an adjacent engine, or ground power. The engine also has an auto ignition func-tion, which automatically provides ignition in the event of a stall, combustor blowout, or momentary loss of fuel. The starting system is used to accelerate the N2 high pressure section of the engine to a speed at which combustion light-off and self sustaining rpm occurs. Placing the engine run switch to RUN turns on the aircraft electrical boost pump. The START switch signals the FADEC to initiate the start sequence.
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