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Description................................................................................................................. 18-01-22
Components and Operation.......................................................................................18-01-22
Vibration Monitoring System......................................................................................18-01-22
Controls and Indications...................................................................................................... 18-01-23
Description................................................................................................................. 18-01-23
Engine Control Panel.................................................................................................18-01-23
Thrust Lever Quadrant and Engine Control Panel.....................................................18-01-23
Engine Start Controls.................................................................................................18-01-24
Air Cond/Bleed Control Panel....................................................................................18-01-24
EICAS Display ........................................................................................................... 18-01-25
EICAS Messages ................................................................................................................ 18-01-25
Volume 2 Flight Crew Operating Manual May 06/2005 CSP 100-6 REV 2
18-00-02 INTRODUCTION
The Challenger 300 is equipped with two Honeywell AS907 high-bypass turbofans. Each powerplant is controlled by a full authority digital engine control system (FADEC).
The AS907 turbofan engine is a 4.2 bypass ratio, two-spool direct drive turbofan engine. The single-stage, wide-chord fan is directly driven by a three-stage low-pressure turbine. The core consists of a four-stage-axial compressor with two stages of variable geometry, a single stage of centrifugal compressor, a through-flow annular combustor, 16 fuel nozzles, 2 ignitors and a two-stage high-pressure turbine. Exhaust system includes an exit guide vane, a mixer nozzle and a centerbody. The accessory gearbox mounts the engine air turbine starter and provides accessory drive pads for mounting the hydraulic pump and generator, as well as providing lubrication for the engine.
FLAT-RATED THRUST
Outside air temperature and pressure altitude are determining factors in achieving takeoff power. Increases in ambient tem-perature or pressure altitude adversely affect the engine’s ability to produce rated thrust. Normal takeoff thrust rating is 6826 pounds. The AS907 is flat rated to ISA +15 °C (86 °F) at sea level. Automatic power reserve (APR) provides flat rated takeoff thrust to ISA + 20 °C (95 °F). APR is invoked either during one engine inoperative condition, with TLA at or above takeoff detent and APR armed, or when the throttle is pushed to the forward mechanical stop.
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