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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
POWERPLANT
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 18-01-01
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 temperature
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.
HONEYWELL AS907 ENGINE SECTIONS
CENTER BODY
HIGH PRESSURE
TURBINE ASSEMBLY
FRONT FRAME BLEED PORTS
ASSEMBLY
SPINNER
COVER RING
ASSEMBLY
FAN ROTOR
ASSEMBLY
FAN INLET
HOUSING
INNER RING
ASSEMBLY
FAN STATOR
VANE ASSEMBLY
ACCESSORY GEABOX
ASSEMBLY
HIGH PRESSURE
COMPRESSOR
ASSEMBLY
LOW PRESSURE
TURBINE ASSEMBLY
EXHAUST
MIXER
NOZZLE
CFO1801002_001
POWERPLANT
Volume 2 Flight Crew Operating Manual May 06/2005
18-01-02 CSP 100-6 REV 2
ENGINE CONSTRUCTION
DESCRIPTION
The AS907 powerplant has two independent major assemblies. The N1 section consists of a fan rotor that is driven through
a shaft by a three stage low-pressure turbine. The N2 section is comprised of four axial flow and one centrifugal compressor,
combustor, accessory gearbox and a two stage high pressure turbine. The high pressure turbine drives the compressor.
AIRFLOW PATHS
Inlet air is initially accelerated and compressed by the fan and is split into two streams. A large percentage of the fan air
exits into the bypass duct. The remainder is directed into the core of the engine. This core airflow passes through a four
stage axial compressor and a single stage centrifugal compressor. Exiting the high pressure compressor diffuser the airflow
is directed into the in line annular combustor where fuel is injected. The fuel/air mixture is ignited and a continuos combustion
is maintained. The expanding gases are then directed through the two stage high pressure and three stage intermediate
turbine assembly, driving both rotating groups, and exiting the engine through the mixer nozzle.
CFO1801002_019
AIR INLET
SECTION
ACCESSORY
DRIVES
COMPRESSOR
SECTION
COMBUSTION
SECTION
BY-PASS
SECTION
EXHAUST
SECTION
TURBINE
SECTION
FWD
COLD BYPASS AIRFLOW
HOT EXHAUST GASES
LEGEND
V 2
POWERPLANT
May 06/2005 Flight Crew Operating Manual Volume 2
REV 2 CSP 100-6 18-01-03
ENGINE CONSTRUCTION (CONT)
MAJOR POWERPLANT COMPONENTS
N1 FAN
N1 fan consists of twenty two titanium inserted blades. the fan containment system uses an aluminum honeycomb material
surrounded by an aramid fiber wrap.
N1 fan speed is indicated on the EICAS.
N2 COMPRESSOR
The N2 compressor is a variable geometry (VG) axial flow compressor that is mechanically driven by the high-pressure
turbine assembly.
　
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