Challenger 300 Flight Crew Operating Manual

Challenger 300 Flight Crew Operating Manual
POWERPLANT
Table of Contents
Introduction ......................................................................................................................... 18-01-01
Honeywell AS907 Engine Sections............................................................................ 18-01-01
Engine Construction ............................................................................................................ 18-01-02
Description ................................................................................................................. 18-01-02
Airflow Paths .............................................................................................................. 18-01-02
Major Powerplant Components.................................................................................. 18-01-03
Engine Fuel System ............................................................................................................ 18-01-04
Description ................................................................................................................. 18-01-04
Components and Operation....................................................................................... 18-01-04
Fuel Pump.................................................................................................................. 18-01-04
Fuel/Oil Heat Exchanger and Fuel Filter.................................................................... 18-01-04
Fuel Metering Unit...................................................................................................... 18-01-04
Fuel System Operation .............................................................................................. 18-01-04
Engine Control System........................................................................................................ 18-01-05
Description ................................................................................................................. 18-01-05
Components and Operation....................................................................................... 18-01-05
FADEC Unit................................................................................................................ 18-01-05
Electrical Power ......................................................................................................... 18-01-05
Engine Idle ................................................................................................................. 18-01-05
Engine Condition and Fault Reporting (ECFR).......................................................... 18-01-06
Thrust Calculations.............................................................................................................. 18-01-07
Thrust Mode Annunciation ......................................................................................... 18-01-07
Max Power (APR) ...................................................................................................... 18-01-07
Auto APR Function .................................................................................................... 18-01-07
Normal-Rated Takeoff N1 Indications (TO) ................................................................ 18-01-07
Climb Thrust (CLB) .................................................................................................... 18-01-08
Cruise Range (CRZ) .................................................................................................. 18-01-08
Bleed Air Extraction ................................................................................................... 18-01-08
N1 and N2 Synchronization ................................................................................................. 18-01-09
Description ................................................................................................................. 18-01-09
Engine Synchronization ............................................................................................. 18-01-09
Mach Hold.................................................................................................................. 18-01-10
Engine Oil System............................................................................................................... 18-01-10
Description ................................................................................................................. 18-01-10
Components and Operation....................................................................................... 18-01-10
Engine Oil Pressure Indications................................................................................. 18-01-10
Engine Oil Level and Replenishment System............................................................ 18-01-11
Engine Oil Temperature ............................................................................................. 18-01-11
Engine Lubrication Schematic ................................................................................... 18-01-12
Engine Bleed Air System..................................................................................................... 18-01-13
Description ................................................................................................................. 18-01-13
Components and Operation....................................................................................... 18-01-13
Engine Starting System ....................................................................................................... 18-01-14
Description ................................................................................................................. 18-01-14
Components and Operation....................................................................................... 18-01-15
Starter Control Valve .................................................................................................. 18-01-15
Air Turbine Starter (ATS)............................................................................................ 18-01-15
Start Sequence .......................................................................................................... 18-01-15
Engine Motoring......................................................................................................... 18-01-16
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18-00-01
POWERPLANT
Table of Contents (Cont)
Ignition System.................................................................................................................... 18-01-16
Description ................................................................................................................. 18-01-16
Components and Operation....................................................................................... 18-01-16
Engine Starting........................................................................................................... 18-01-16
Aerodynamic Stall ...................................................................................................... 18-01-16
Flameout Protection................................................................................................... 18-01-17
Thrust Levers ...................................................................................................................... 18-01-17
Description ................................................................................................................. 18-01-17
Components and Operation....................................................................................... 18-01-17
Thrust Levers ............................................................................................................. 18-01-17
Thrust Reverse Levers............................................................................................... 18-01-17
Thrust Reverser System ..................................................................................................... 18-01-19
Description ................................................................................................................. 18-01-19
Components and Operation....................................................................................... 18-01-19
Thrust Reverser ......................................................................................................... 18-01-19
Reverse Thrust Operation.......................................................................................... 18-01-21
Isolation Control Unit.................................................................................................. 18-01-21
Directional Control Unit .............................................................................................. 18-01-21
Vibration Monitoring System ............................................................................................... 18-01-22
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
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POWERPLANT
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
FAN INLET
HOUSING FRONT FRAME
FAN ROTOR
ASSEMBLY
ASSEMBLY
BLEED PORTS
HIGH PRESSURE
TURBINE ASSEMBLY
SPINNER
COVER RING
ASSEMBLY
CENTER BODY
FAN STATOR
VANE ASSEMBLY
Sep 13/2004
REV 1
HIGH PRESSURE
COMPRESSOR
ASSEMBLY
ACCESSORY GEABOX
ASSEMBLY
LOW PRESSURE
TURBINE ASSEMBLY
Flight Crew Operating Manual
CSP 100-6
EXHAUST
MIXER
NOZZLE
CFO1801002_001
INNER RING
ASSEMBLY
Volume 2
18-01-01
POWERPLANT
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.
AIR INLET
COMPRESSOR
COMBUSTION
TURBINE
SECTION
SECTION
SECTION
SECTION
EXHAUST
BY-PASS
SECTION
SECTION
LEGEND
COLD BYPASS AIRFLOW
FWD
HOT EXHAUST GASES
CFO1801002_019
ACCESSORY
DRIVES
V2
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POWERPLANT
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.
The variable geometry (VG) system regulates airflow across the N2 compressor by changing the position of the inlet guide
vanes and the stator vane for the inlet and first stage of the compressor. The VG system optimizes the angle of attack of the
airflow at the compressor blades and provides compressor stall and surge protection.
The VG inlet guide vanes and stators are programmed by FADEC and positioned by actuators and mechanical linkage.
High-pressure fuel from the engine fuel metering unit is used to hydraulically move the actuators.
N2 speed is displayed on the EICAS. There is no EICAS indication for the variable geometry system.
ACCESSORY GEARBOX
The N2 compressor drives the engine accessory gearbox. Mounted on the gearbox are:
-
Engine lubrication pumps
Hydraulic pump (EDP 1 or EDP 2)
Engine fuel pump and fuel metering unit (FMU)
Air turbine starter
Integral oil reservoir
Generator
Permanent Magnet Alternator (PMA)
The PMA provides three-phase power to each engine control unit (ECU). The ECU measures N2 from one of the three
phase inputs. The PMA is designed to provide the electric power required by the control system and engine at and above
45% N2. This speed is less than the minimum N2 idle speed. The PMA is considered to be the primary source of ECU power, with 28 VDC from the aircraft being the backup source. Aircraft 28 VDC power is required for starting and shutdown.
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POWERPLANT
ENGINE FUEL SYSTEM
DESCRIPTION
Fuel is delivered to the fuel injectors at the pressures and flow rates necessary to maintain the desired engine thrust. The
engine fuel system also performs the following functions:
-
Compressor variable geometry actuator.
Cool the engine oil (heat transfer).
Actuate and lubricate fuel system components.
Provide motive flow for the scavenge and main ejector pumps.
Combustion fuel can be interrupted by moving the L (R) ENGINE run switches to STOP or by selecting the L (R) ENGINE
FIRE switches. The STOP position shuts off the fuel at the fuel metering unit. The L (R) ENGINE FIRE switch closes the
fuel shutoff valve and the fuel metering valve shutoff valve.
COMPONENTS AND OPERATION
FUEL PUMP
The fuel pump mounted on the accessory gearbox is comprised of three separate pumps contained within a single housing.
The fuel pump provides fuel under high pressure and at flow rate that exceeds the requirements of the engine at any power
setting. Excess fuel is bypassed back through the fuel filter system for re-circulation.
Fuel pump pressure is also used to generate motive flow for the scavenge and main ejectors of the aircraft fuel system.
FUEL/OIL HEAT EXCHANGER AND FUEL FILTER
A fuel/oil heat exchanger warms engine fuel and cools engine oil. The engine fuel temperature is indicated on the FUEL
synoptic page.
A 10 micron fuel filter is used to remove solid contaminants from the fuel. The filter is depicted on the FUEL synoptic
page. An impending fuel filter bypass condition on either engine is reported by an advisory CAS message L(R) ENGINE
FUEL BYPASS. A dual impending fuel filter bypass condition on both engines is reported by a caution CAS
message (ENGINES FUEL BYPASS).
FUEL METERING UNIT
The fuel metering unit (FMU) is an electrohydraulic device that meters and distributes the fuel needed for combustion
based upon control signals from the FADEC system. The FMU’s primary components are the fuel metering valve and pressurizing and shutoff valve. The metering valve supplies fuel in response to commands from the FADEC to maintain combustion under all operating conditions. The pressurizing and shutoff valve controls the supply of fuel for combustion.
The FMU also supplies the high-pressure fuel to actuate the VG inlet guide vanes and compressor stator vanes.
FUEL SYSTEM OPERATION
The main fuel ejectors or DC powered boost pumps deliver fuel from the collector tanks via fuel feed manifolds to the engines. Engine fuel shutoff valves (SOVs) are installed in the manifold to interrupt the supply of fuel to the engines during
a fire. The L (R) ENGINE FIRE switches control the SOVs.
At the engine, the fuel is pressurized, heated, filtered, metered, and distributed to the combustion chamber. All fuel scheduling is controlled by the FADEC.
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POWERPLANT
ENGINE CONTROL SYSTEM
DESCRIPTION
The Honeywell AS907 powerplant is controlled by the full authority digital electronic control (FADEC) system.
The FADEC provides a full range of engine control, including thrust reverser control under all steady state and transient
engine conditions. The FADEC controls the operation and performance of the engine through three subsystems: fuel control, compressor airflow management, and engine starting/ignition control.
COMPONENTS AND OPERATION
FADEC UNIT
Critical functions of the FADEC include:
- Control of engine thrust within the required limits, including control of bleed valves, compressor guide vanes
(CGVs), and nacelle anti-ice bleed flow
- Validates N1, N1 limits, and interstage turbine temperature (ITT)
- Thrust reverser operation
- Overspeed circuits
Each powerplant has its own dual-channel FADEC computer. One FADEC channel operates as the in-control channel and
processes information to provide engine control outputs. The other channel operates in standby. The standby channel processes all the input information but does not provide control output with one exception. Both the in-control and standby
channels will respond to an engine overspeed by commanding the shutoff valve in the fuel metering unit to close in order
to return the engine to an on-speed condition.
The in-control and standby channels continuously share command and status data through a crosstalk data bus. Should the
designated in control channel become unserviceable, the standby channel assumes the in control role.
During normal operations with two serviceable FADEC channels, FADEC software directs the channels to alternate in-control and standby roles on each successive engine start.
FADEC malfunctions are presented as either caution or advisory messages. Each message has a different impact on the
dispatch ability of the aircraft.
ELECTRICAL POWER
The PMA ensures FADEC supply when N2 is greater than 45%. For engine starting and whenever N2 is below 45%, the
aircraft electrical system supplies power to the FADEC system.
ENGINE IDLE
When the thrust lever is placed at IDLE, the minimum N2 idle rpm is programmed by the FADEC. Idle rpm is dependent
upon atmospheric information, bleed-air loading and phase of flight.
The FADEC will always program the best idle speed for any phase of flight. When the aircraft transitions from one flight
phase to the next, idle rpm is automatically adjusted. There are three different N2 idle settings: flight idle, reverse idle, and
ground idle.
FLIGHT IDLE
Flight idle refers to the idle setting used when the thrust lever is set to idle while airborne (weight-off-wheels).
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POWERPLANT
ENGINE CONTROL SYSTEM (Cont)
GROUND IDLE
N2 ground idle is the minimum thrust setting. It is selected when weight is on wheels and the thrust lever is idle. Ground
idle varies with altitude and temperature. Increases in altitude or ambient temperature result in an increase in N2 idle rpm.
Decreases in altitude or ambient temperature result in a decrease in N2 idle rpm.
REVERSE IDLE
When reverse idle is selected, reverse balk is activated by the FADEC. Further movement rearward beyond the REV detent
is restricted until the thrust reverser is fully deployed.
SINGLE ENGINE THRUST MANAGEMENT
The FADEC computers continuously crosstalk to share data on the health of each engine. The FADEC will automatically
activate the APR function on the operating engine, should the other engine fail, as long as the TLA is in the TO detent or
above and the APR has not been disabled by the crew.
The FADEC system monitors N2 rpm of both engines. If the mismatch of N2 speed exceeds 15%, the FADEC automatically
increases the N1 speed of the operable engine.
AUTOMATIC POWER RESERVE
When an engine fails, the automatic power reserve (APR) feature of the FADEC will automatically increase the thrust for
the operating engine to the emergency thrust power setting of APR power.
Automatic Power Reserve is available when APR is armed during takeoff if the thrust levers are in the TO detent or above
and if APR has not been disabled by the crew. On the approach, APR is armed for the go-around when in approach configuration (either engine is available, flaps greater than 20° , or the landing gear is down).
APR power for both engines can also be selected by advancing both thrust levers to the APR stop. A cyan APR icon appears
to the right of each N1 indicator.
ENGINE CONDITION AND FAULT REPORTING (ECFR)
An engine condition and fault reporting system is installed to provide monitoring of engine health. The system periodically
records engine parameters and allows the crew to request that conditions be recorded at anytime. Use of the system entails
downloading data from the FADEC for review by maintenance personnel. The data may be downloaded at anytime to assist
in diagnosing engine problems which may be encountered. The ECFR is intended for maintenance functions and in-flight
monitoring or diagnosis by maintenance personnel. The system is integrated into the FADEC of each engine.
ECFR EVENT SWITCH
The EVENT switch is located on the engine control panel. The switch allows the flight crew to manually initiate data collection to the ECFR.
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POWERPLANT
ENGINE CONTROL SYSTEM (Cont)
THRUST CALCULATIONS
FADEC automatically computes a target thrust rating for thrust lever position and presents the target or maximum value on
the N1 indicator.
On the ground, normal rated takeoff thrust is automatically calculated when an engine is started. Normal rated N1 takeoff
rpm is continuously updated for changes in the Mach number, delta ambient temperature, and pressure altitude.
During the takeoff roll, the N1 normal rated takeoff thrust value is continuously updated as the aircraft accelerates. At 65
kt discrete inputs for the thrust calculations are locked in. The calculation is unlocked when the aircraft altitude exceeds
400 ft. AGL or the thrust lever is retarded from the TO detent.
The cyan color target N1 appears on the N1 indicator as:
- N1 caret (doughnut for cruise power)
- N1 digital reference
-Thrust mode annunciation
THRUST MODE ANNUNCIATION
The thrust mode annunciation identifies the position of the thrust lever during most phases of operation or a specific armed
condition.
With both engines operating, the following thrust mode annunciations are presented:
-
APR
TO
CLB
CRZ
REV
MAX POWER (APR)
When either or both thrust levers are placed in the APR detent, the FADEC increases the engine thrust to automatic power
reserve power (APR). The APR power setting is an emergency thrust setting.
To protect against inadvertent APR activation, the pilot must apply increased force to move the thrust lever forward to the
APR detent.
APR thrust is indicated on the associated N1 gauge by:
- Cyan caret
- Cyan N1 digital reference
- Cyan APR icon
AUTO APR FUNCTION
- AUTO APR function indications are the same as APR indications. If the aircrew elects to disable the AUTO APR
function, an AUTO APR OFF (S) CAS message is displayed and the AUTO APR OFF switch is illuminated.
NORMAL-RATED TAKEOFF N1 INDICATIONS (TO)
Normal-rated takeoff thrust is automatically calculated by FADEC when electrical power is applied to the aircraft on the
ground. Takeoff thrust is set on the takeoff roll by placing the thrust levers in the TO detent.
The programmed normal-rated takeoff thrust value is displayed on the MFD by the following indications:
- Cyan caret
- Cyan N1 digital reference
- Cyan TO thrust mode annunciation for takeoff thrust
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POWERPLANT
ENGINE CONTROL SYSTEM (Cont)
CLIMB THRUST (CLB)
When the thrust lever is placed in the CLB detent, the FADEC electronically programs the engine to accelerate or decelerate
to the climb thrust setting.
The programmed climb thrust value is displayed on the MFD EICAS by the following indications:
- Cyan caret
- Cyan N1 digital reference
- Cyan CLB thrust mode annunciation
CRUISE RANGE (CRZ)
Cruise power is unlike other thrust settings in that it is not associated with a thrust lever detent.
Cruise power is set by positioning the thrust lever in the quadrant range that exists between the IDLE and CLIMB detents.
In this range, the pilot manually sets the thrust levers to maintain cruise speed or sets thrust for the descent and approach.
In cruise, FADEC does not set the cruise thrust to match the FADEC generated maximum cruise thrust target value. To
distinguish maximum cruise power (CRZ) from other detent-related thrust settings, a cyan N1 doughnut is used instead of
a caret.
Maximum cruise power (CRZ) is indicated by the following:
- Cyan doughnut
- Cyan N1 digital reference
- Cyan CRZ thrust mode annunciation
BLEED AIR EXTRACTION
When the thrust levers are in any of the detents and a new bleed air demand is placed on the engines, the N1 target rpm may
change to compensate for the new bleed-air demands.
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POWERPLANT
N1 AND N2 SYNCHRONIZATION
DESCRIPTION
OFF, N1, or N2, is selected with the AUTO SYNC switch, located on the ENGINE control panel. When SYNC (N1 or N2)
is selected, the two engines are synchronized if the thrust levers are in the CRZ or CLB setting.
COMPONENTS AND OPERATION
ENGINE SYNCHRONIZATION
When the AUTO SYNC selector switch is set to N1, the FADEC matches the fan speed of the slave engine to the speed of
the master engine. The left and right engines will automatically designate themselves as master and slave engines using a
cross-engine communication link. The engine with higher N1 compensation, or the left engine when N1 compensation of
the two engines is the same, becomes the master engine. If the measured N1 or N2 of the slave engine is not within 5% of
the master engine set point, the FADEC will provide an indication that synchronization is commanded but not achieved.
ENGINE
L ENG FIRE
R ENG FIRE
APU FIRE
FIRE
1
AUTO APR
FIRE
FIRE
FIRE EXT
ARMED
2
EVENT
ARMED
AUTO
SYNC
MACH HOLD
N1
OFF
N2
L STARTER
R STARTER
OFF
OFF
IGNITION
CRANK
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START
CFO1801002_023
OFF
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POWERPLANT
THRUST CALCULATIONS (Cont)
MACH HOLD
Mach hold is a function provided by FADEC that minimizes throttle movements over long periods during cruise. Limited
adjustment is available to the master engine to hold the selected Mach. For MACH HOLD to be active, N1 or N2 must be
synchronized, the aircraft trimmed for steady, level flight and the autopilot engaged in either Altitude Hold or Altitude Select (with altitude captured).
Mach Hold authority only allows N1 to be adjusted within ± 3% N1 for the thrust lever position at the time MACH HOLD
is active. When active, a green MACH HOLD will be displayed between the N1 indicators (on aircraft without SV 6.0 upgrade and FADEC V-10 software, the green light will flash momentarily, then extinguish). At authority limits, a white
MACH HOLD is displayed .
ENGINE OIL SYSTEM
DESCRIPTION
The engine oil system provides cooling and lubrication for all of the engine bearings, gears and splines. It also provides
fuel heating and shaft vibration damping (through the use of hydraulic mounts). The engine oil sump venting and breather
system is also integral to the overall lubrication system.
COMPONENTS AND OPERATION
Oil is supplied to the engine by the oil pump that draws hot oil from the accessory gear box (AGB) oil tank. The oil is
filtered and cooled in the fuel heater/oil cooler (FHOC) prior to flowing into the engine bearing sumps. In the engine bearing sumps (forward and aft) and in the AGB, the oil lubricates the bearings, seals, and gears and cools them by absorbing
heat directly as it passes in and around these components.The oil is scavenged by dedicated scavenge pumps and returned
to the oil tank. Power to drive the oil pump is provided by the compressor spool trough the AGB.
An oil filter bypass valve and an impending bypass switch are located in parallel with the filter. The switch provides a warning when the filter becoming clogged and the pressure drop across it reaches 45 psi, indicating that impending bypass is
imminent. The bypass valve opens at 65 psi. The ECU monitors the switch and the oil temperature, and provides an indication of impending filter bypass to the cockpit when the switch is open and oil temperature is in the normal operating
range. During bypass mode, the system still provides a minimum filtration level by means of an accessible last chance
screen. Once the impending bypass warning has been indicated, the CAS message remains illuminated during the bypass
mode and logged by the FADEC to direct maintenance action prior to the next flight. Before oil is returned to the oil tank
it flows across the chip detector in the AGB housing. The chip detector is linked to the ECU to provide an indication on
the EICAS. Chip detector and impending oil filter bypass advisory CAS messages are presented as L (R) ENGINE OIL
CHIP and L (R) ENGINE OIL BYPASS.
ENGINE OIL PRESSURE INDICATIONS
To provide system redundancy, a pressure switch and separate pressure transmitter are used to monitor the engine oil pressure. When low oil pressure is detected by the pressure switch, a L (R) ENG OIL PRESS LOW (W) is presented. Excessively high oil pressure is indicated by a L (R) ENG OIL PRESS HIGH (C). An imminent bypass of the oil filter is
annunciated by a L (R) ENGINE OIL BYPASS (A) CAS message.
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POWERPLANT
ENGINE OIL SYSTEM (Cont)
ENGINE OIL LEVEL AND REPLENISHMENT SYSTEM
The engine oil servicing doors are located on the forward and left side of each engine nacelle. Oil quantity may be checked
by a sight gage on the AGB and replenished through the oil filler port. The gage bands are marked FULL, ONE LOW, and
NO DISPATCH. However, the primary means to check oil on the Challenger 300 is with the Remote Oil Level Sensor
(ROLS). Oil levels are transmitted by the ARINC 429 bus to the refuel/defuel panel located in the right wing root fairing.
Wait at least 15 minutes, but not more than 1 hour following engine shutdown before checking the oil using ROLS, and
service the tank if more than one quart (0.95 liter) low. Each engine oil tank capacity is 7.8 quarts (7.4 liters), while the oil
volume at the FULL mark is 5.7 quarts (5.4 liters). The ONE LOW band indicates when the tank is approximately 1 quart
below FULL. The NO DISPATCH band is approximately 1.6 quarts below FULL. If the oil level is below this band, the
tank should be serviced prior to dispatch. However, if the oil level is within the band, the engine can be operated at least
10 hours without servicing the tank. The 10 hour time frame assumes a maximum engine oil consumption rate. Note that
the oil volume is less than the total tank volume of 7.8 quarts (7.4 liters). The total tank volume design accounts for hot oil
volume expansion and for the additional volume between the sight gage FULL mark and the fill-to-spill level.
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.
ENGINE OIL LEVEL
Full
Full
TEST
FULL
ON
One
Low
CHECK OIL
Dispatch
CFO1801002_020
No
POWER
RIGHT
ENGINE NACELLE OIL LEVEL SIGHT GAGE
LEFT
REFUEL DEFUEL CONTROL PANEL
ENGINE OIL TEMPERATURE
Excessively high engine oil temperatures are displayed as L (R) ENG OIL TEMPERATURE HIGH (C) CAS message.
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POWERPLANT
ENGINE OIL SYSTEM (Cont)
ENGINE LUBRICATION SCHEMATIC
TANK
PRESSURIZATION
VALVE
TANK VENT
FORWARD SUMP
SCAVENGE SCREEN /
MAGNETIC PLUG
(DEBRIS MONITOR)
FILL PORT
WITH
ELECTRICAL
CHIP DETECTOR
WITH
LOCKING CAP,
REMOTE OIL LEVEL
SELF-CLOSING
VALVE
SCREEN,
INDICATOR BOSS
FLAPPER VALVE
AND SCUPPER
OIL SCAVENGE
OIL
DISCHARGE
OIL TANK
SIGHT GAGE
PRESSURE
TEST PORT
PRESSURE
TEST PORT
PRESSURE
RELIEF VALVE
FILTER
AIR/OIL
ROTATION
OIL
FILTER
SEPARATOR
FILTER ELECTRICAL
IMPENDING/
PRESSURE
ADJUSTING
MECHANICAL
BYPASS
NACELLE
DISCHARGE
ACCESSORY
GEARBOX
VALVE
TEST PORT
OIL PUMP
SIPHON
FUEL HEATER/
OIL COOLER
BREAK
AFT SUMP
SCAVENGE
FUEL FILTER
GEARBOX SUMP
SCAVENGE SCREEN
SCREEN /
(DEBRIS MONITOR)
PLUG
ASSEMBLY
MAGNETIC
DRAIN PLUG
MAGNETIC
DRAIN
FEATURE
OIL INLET
(2 PLACES)
(DEBRIS
MONITOR)
PRESSURE
AGB OIL
NOZZLES
REDUCTION
LAST-CHANCE
ORIFICE
SCREEN
OIL
TANK
TEMPERATURE
DRAIN PLUG
TRANSDUCER
AFT
SUMP SUPPLY
OIL PRESSURE
FORWARD
TRANSDUCER
SUMP SUPPLY
DE-OIL
(DUAL SWITCH)
VALVE
LEGEND
CFO1801002_022
VENT
FUEL
OIL
V1
Volume 2
18-01-12
Flight Crew Operating Manual
CSP 100-6
Sep 13/2004
REV 1
POWERPLANT
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 crossbleed valve is installed between the left and right pneumatic ducts, that can be opened automatically or manually by pressing 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 equipment 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.
V1
Sep 13/2004
REV 1
Flight Crew Operating Manual
CSP 100-6
Volume 2
18-01-13
POWERPLANT
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 accomplished with bleed air from the APU, an adjacent engine, or ground power. The engine also has an auto ignition function, 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.
DC electrical power and air from the bleed-air manifold are required to open the start valve and engage the air turbine starter. The bleed-air manifold can be pressurized by the:
- APU bleed air
- Ground cart HP bleed air
- Opposite engine bleed air (crossbleed)
The pneumatic pressure from any of the three pneumatic sources is displayed on the ECS synoptic page.
APU,
OUTPUT
SHAFT
N2
COMPRESSOR
AIR TURBINE
STARTER
STARTER
CONTROL
VALVE
FLOW
CROSS-
CONTROL
BLEED
VALVE
VALVE
GROUND AIR
SUPPLY
OR ENGINE
CROSS-BLEED
START
AIR
FLOW
ENGINE
L ENG FIRE
R ENG FIRE
APU FIRE
ECU
FIRE
FIRE
FIRE
1
FIRE EXT
2
ARMED
EVENT
ARMED
AUTO APR
AUTO
MACH HOLD
SYNC
N1
OFF
N2
OFF
ON
INTEGRATED
L STARTER
CRANK
AIR
R STARTER
OFF
OFF
START
IGNITION
ON
CRANK
START
SYSTEM
(IAS)
CFO1801002_018
ENGINE CONTROL
PANEL
V2
Volume 2
18-01-14
Flight Crew Operating Manual
CSP 100-6
May 06/2005
REV 2
POWERPLANT
ENGINE STARTING SYSTEM (Cont)
COMPONENTS AND OPERATION
STARTER CONTROL VALVE
The starter control valve is mounted adjacent to the air turbine starter (ATS) inside the engine nacelle. The valve normally
requires 28 VDC power and pneumatic pressure to open. When the L (R) starter switch on the ENGINE control panel is
moved to the START position, the FADEC supplies 28 VDC power to energize the solenoid. This allows pneumatic pressure to open the valve and engage the air turbine starter.
When N2 rpm is > 50%, the FADEC removes power from the solenoid, the start valve closes and the air turbine starter
disengages.
AIR TURBINE STARTER (ATS)
The air turbine starter is mounted on the accessory gearbox. The ATS converts pneumatic energy into mechanical motion.
The starter, through a sprag clutch, mechanically engages the accessory gearbox and assists in accelerating the engine to
idle speed. During the start sequence, the start valve closes and the ATS disengages when the N2 reaches or exceeds 46.2%
or the OFF position is selected on the throttle quadrant assembly panel.
For subsequent starts, the starter sprag clutch does not require that the engine rotation be completely stopped before engaging the starter. The ATS may be engaged at any rpm up to 50% rpm (starter cutout speed).
START SEQUENCE
L ENGINE
R ENGINE
RUN
RUN
OFF
OFF
CFO1801002_015
Each engine has a set of L (R) STARTER switches on the ENGINE control panel and a set of RUN/OFF switches on the
throttle quadrant panel.
OFF
CRANK
START
OFF
CRANK
START
To start the engines, set the related engine switch to RUN. This turns on the fuel DC boost pump and operates the ECU
start cycle. Set START switch to the START position and hold it for one second to operate the usual ground or air start.
When the applicable engine RUN position is selected on the TQA and the starter switch is set to START the:
- The start valve on the associated engine opens to allow pressure from the bleed air manifold to engage the ATS
When the engine’s N2 reaches 46.25%, the:
- The start valve closes and the ATS disengages
If the start valve fails to close after achieving 50% N2, a L (R) STARTER FAIL ON (C) CAS message is shown
Refer to the Airplane Flight Manual for starter limits.
May 06/2005
REV 2
Flight Crew Operating Manual
CSP 100-6
Volume 2
18-01-15
POWERPLANT
ENGINE STARTING SYSTEM (Cont)
ENGINE MOTORING
Dry motoring is accomplished by toggling the start switch from OFF to CRANK and hold for the duration of the cranking.
Dry motoring may become necessary to cool the engine when restarting the engine immediately after shutdown.
Wet motoring is accomplished by setting the RUN/OFF switch to RUN, toggling the start switch from OFF to CRANK and
holding the latter for the duration of cranking. In response, the ECU energizes the air turbine starter control valve, controls
the run solenoid, and controls the fuel metering valve per the start sequence.
A dry motoring follows the wet motoring start. Dry motoring is used to clear any pools of fuels that may have collected in
the engine during the wet motoring.
IGNITION SYSTEM
DESCRIPTION
The ignition system consists of an ignition exciter, two igniter plugs, and two sets of igniter leads. The ignition system for
each engine is a dual independent and redundant system. The ECU will activate the ignition system during automatic starts
and restarts. The ECU will also automatically turn the ignition system off when the engine is running. The pilot can manually activate the ignition system by turning on the IGNITION switch.
For automatic ground starts, the ECU uses one ignition channel, changing the channel used on each start. For all other starts,
both ignition channels are used simultaneously. The system is capable of continuos operation by manual activation by the
pilot, but is normally only energized during the starting sequence.
COMPONENTS AND OPERATION
ENGINE STARTING
When the FADEC in-control channel is determined during N2 spool-up, the in-control channel closes the associated ignition relay. When the applicable L (R) ENGINE RUN switch is selected, the FADEC selected dc powered ignition exciter
is energized. Ignition is de-energized by the FADEC at starter cutout.
AERODYNAMIC STALL
At an excessively high angle of attack (AOA), there is a possibility that turbulent airflow from the wing root could disrupt
the flow of air into the engine intake. Disruption of airflow at the intake could lead to engine compressor stall. The FADEC
and the stall protection computer provide two levels of compressor stall protection.
As the aircraft angle of attack reaches the stick shaker firing angle, the stall protection computer signals the FADEC
to energize both ignition channels.
If the FADEC detects a compressor stall or surge, the FADEC will modulate engine thrust to clear the event.
FLAMEOUT PROTECTION
If the FADEC detects an engine flameout, it will automatically initiate a re-light. Both ignitions systems are energized.
An engine flameout is detected when the following occurs:
- The engine is subidle and either the ITT rate of change is negative, or the N2 rate of change is lower
than commanded
- A flameout is detected while the engine RUN/OFF switch is still in the RUN position
- The L (R) ENGINE FLAMEOUT (C) CAS message is illuminated
When the affected engine’s ENGINE RUN switch is placed in the OFF position, the L (R) ENGINE FLAMEOUT caution
message is replaced by the L (R) ENGINE SHUTDOWN (S) message.
Volume 2
18-01-16
Flight Crew Operating Manual
CSP 100-6
May 06/2005
REV 2
POWERPLANT
THRUST LEVERS
DESCRIPTION
The thrust lever quadrant contains the thrust levers, thrust reverse finger lifts, microswitches and internal locks and stops
necessary to control the engines in forward and reverse thrust.
COMPONENTS AND OPERATION
THRUST LEVERS
Thrust lever quadrant settings are MAX REV, REV, IDLE, CLB, TO, and APR. In addition, the range of movement of the
thrust lever between IDLE and CLB is defined as the cruise range.
The thrust levers incorporate both mechanical stops and soft detents.
Self-centering soft detents prevent the thrust levers from moving inadvertently.
FRICTION KNOB
A friction knob allows the pilot to change the friction setting for the thrust levers.
THRUST LEVER POSITION MEASUREMENT
Actual thrust lever positions are electrically measured by rotary variable differential transformers (RVDTs) or sensed by
micro switches that are housed within the thrust quadrant. The information is provided to the FADEC, the flight control
computers (FCC) and to the data concentrator units (DCU). Other aircraft systems are influenced by thrust lever position
are as follows:
-
Landing gear warning system
Takeoff configuration warning system
Cabin pressurization
Ground spoilers
TAKEOFF AND GO-AROUND (TOGA)
Takeoff and go-around (TOGA) switches are included in each thrust lever. When pressed, the TOGA switch signals the
flight control computers to modify flight director commands and the FMS position is updated through the flight management computer(s).
THRUST REVERSE LEVERS
The thrust levers are linear throttles, which means that reverse thrust is not modulated by use of piggyback levers, instead,
the thrust reverser levers are lifted above a gate, which allows the thrust lever itself to translate aft to modulate the reverse
thrust level. The reverse thrust setting is for ground use only.
May 06/2005
REV 2
Flight Crew Operating Manual
CSP 100-6
Volume 2
18-01-17
POWERPLANT
THRUST LEVERS (Cont)
TAKE-OFF/GO AROUND
(TO/GA) SWITCH
THRUST
REVERSER
LEVER
APR
AUTOMATIC
POWER
RESERVE
TO
THRUST
APR
APR
TO
TO
OFF
CLB
CLB
CLB
TAKE
REVERSER
CONTROL
CLIMB
LEVER
THRUST
IDLE
IDLE
IDLE
REV
REV
IDLE FORWARD
THRUST
REV
IDLE
REVERSE
TO/GA
TOGA
SWITCH (2)
TO/GA
THRUST
MAX
REV
MAX
REV
MAX REV
L ENGINE
R ENGINE
RUN
RUN
FRICTION
REVERSE
THRUST
KNOB
OFF
OFF
CFO1801002_006
MAXIMUM
V1
Volume 2
18-01-18
Flight Crew Operating Manual
CSP 100-6
Sep 13/2004
REV 1
POWERPLANT
THRUST REVERSER SYSTEM
DESCRIPTION
The thrust reversers help stop the aircraft on landing and during a rejected takeoff (RTO). The system is operable on the
ground only; the reversers will not deploy in flight.
COMPONENTS AND OPERATION
THRUST REVERSER
The thrust reverser is powered by the left hydraulic system for the left reverser and the right hydraulic system for the right
reverser and is controlled by the FADEC and electrical signals from the airplane.
The hydraulic system has:
-
Isolation control unit
Directional control unit
Hydraulic and electro-hydraulic primary locks
Door actuators
Tertiary actuator locks
The electrical system comprises:
-
Isolation control unit inhibition switch
Stow switches — two per door, signal feedback to the FADEC
Deploy switch — one per door, signal feedback to the FADEC
Maintenance test switch — allows thrust reverser operation without engine operating
UPPER
DOOR
UPPER ACTUATOR
UPPER TERTIARY LOCK
ELECTRO-HYDRAULIC
PRIMARY LOCK
LOWER TERTIARY LOCK
LOWER
DOOR
LOWER ACTUATOR
Sep 13/2004
REV 1
Flight Crew Operating Manual
CSP 100-6
CFO1801002_011
HYDRAULIC
PRIMARY LOCK
Volume 2
18-01-19
POWERPLANT
THRUST REVERSER SYSTEM (Cont)
THRUST REVERSER STOWED
FORWARD THRUST
THRUST REVERSER STOWED
FORWARD THRUST
ACTUATOR
UPPER DOOR
EXHAUST UNIT
FIXED STRUCTURE
THRUST REVERSER DEPLOYED
REVERSE THRUST
EXHAUST
CONE
LOWER DOOR
ACTUATOR
THRUST REVERSER DEPLOYED
REVERSE THRUST
Volume 2
18-01-20
Flight Crew Operating Manual
CSP 100-6
CFO1801002_010
EXHAUST NOZZLE
Sep 13/2004
REV 1
POWERPLANT
THRUST REVERSER SYSTEM (Cont)
REVERSE THRUST OPERATION
When reverse thrust is desired, the thrust levers are drawn aft to the IDLE position, where the thrust reverser levers may
be lifted, thus allowing the main thrust levers to be pulled further rearward to the REV soft detent. This rearward movement
signals the FADEC (via the RVDTs) and the thrust reversers (via the microswitches in the TQA) that thrust reverser deployment has been commanded. Once in the REV detent, it is unnecessary to hold the thrust reverse levers up, as they stay
in place until the pilot selects forward operation. Interlock balks will prevent movement of the levers rearward beyond REV
until the thrust reverser deploy switches provide feedback that the thrust reverser doors are fully deployed. During the deployment sequence, a white REV icon is displayed on the EICAS, and N1 target and bug are removed from the display.
Once the doors are fully deployed, the REV icon changes to a green color, and the interlock baulk is released. This will
allow for thrust lever modulation between the REV and MAX REV positions. N1 target and bug are set to the maximum
reverser N1 setting.
To stow the thrust reversers, the main thrust levers are moved forward to the IDLE position. As the lever move between
the REV and IDLE positions, the thrust reverser levers will return to their forward thrust position. Interlock balks will prevent movement of the main thrust levers forward beyond IDLE until the thrust reverser stow switches provide feedback
that the doors have completely closed. During the stow phase, the REV icon will go from green to white, and the N1 target
and bug are removed from the display. Once the doors are fully stowed, the REV icon will disappear, and the N1 target and
bug will reset to the takeoff setting. Also, the forward interlock baulk will be removed, allowing for forward
thrust modulation above idle thrust.
Thrust reverser operation of each engine is independent of the other engine. If the FADEC senses that a thrust reverser door
is unlocked in flight, the FADEC will limit engine thrust to idle, irrespective of thrust lever position. It will also post
a L (R) REVERSER UNSAFE (W) CAS message. If the main thrust levers are pulled rearward to the REV position when
the aircraft is not on the ground (no WOW or wheel spinup signal), the doors will not be unlocked, and an amber REV icon
is illuminated inside the N1 display. This caution signal is removed if the levers are restored to IDLE or forward while in
the air.
ISOLATION CONTROL UNIT
The isolation unit controls the hydraulic system pressure to the thrust reverser system.
DIRECTIONAL CONTROL UNIT
The directional control unit controls hydraulic pressure to the upper and lower door actuators to deploy force.
A pressure switch sends a signal to the directional control unit. The directional control unit control also sends a signal to
the upper and lower door actuators causing an overstow of the thrust reverser doors to enable unlatching of the primary
locks.
The unit contains a directional control valve that is controlled by a solenoid valve. The solenoid valve is controlled from
thrust lever microswitches, WOW and wheel spinup signals. When the solenoid is energized, a deploy valve opens allowing
hydraulic pressure to sequentially release the two primary locks.
Through the WOW or wheel spinup signal, two tertiary locks (prevents uncommanded thrust reverser deployment) release
and allows the directional control valve to the deploy position.
As the aircraft decelerates, the maximum N1 is reduced which limits thrust reverser authority and also helps prevent thrust
reverser controllability problems.
Sep 13/2004
REV 1
Flight Crew Operating Manual
CSP 100-6
Volume 2
18-01-21
POWERPLANT
VIBRATION MONITORING SYSTEM
DESCRIPTION
The vibration sensor is a self-generating velocity pickup design that outputs a voltage signal proportional to velocity. The
signal is shared by both ECUs and annunciated in the cockpit.
COMPONENTS AND OPERATION
VIBRATION MONITORING SYSTEM
The powerplant fan assembly is continuously monitored for vibration. There is a vibration pickup on each engine, to provide feedback to the aircrew which engine is producing high vibration levels. It is also used by maintenance personnel for
ground based fan trim balancing. A L (R) ENGINE VIBRATION (C) CAS message is illuminated and a VIB icon is displayed on the MFD. If there is a loss of vibration signals from the affected engine(s), a L (R) ENGINE VIB FAIL (A) is
displayed as a CAS message.
STANDARD WIRING
LOW NOISE CABLE
EICAS
ENGINE CONTROL
UNIT
RIGHT ENGINE
N1
SPEED
PROBE
N1
SPEED
PROBE
N2
SPEED
PROBE
N2
SPEED
PROBE
VIBRATION
TRANSDUCER
VIBRATION
TRANSDUCER
CFO1801002_007
AIRFRAME
LEFT ENGINE
Volume 2
18-01-22
Flight Crew Operating Manual
CSP 100-6
Sep 13/2004
REV 1
POWERPLANT
CONTROLS AND INDICATIONS
DESCRIPTION
The thrust levers control the application of forward and reverse thrust.
TOGA switches provide data for other operating systems.
The ENGINE panel provides switches to control engine starts, continuous ignition, Mach hold, engine synchronization,
disabling of the auto APR function, as well as fire extinguishing.
Engine-operating parameters are presented on the EICAS display. Indications include N1 and N2 (in percent values), as
well as ITT, fuel flow, oil pressure and temperature, ignition system and start status, high engine vibration levels, thrust
reverser use, as well as the selection of engine synchronization and mach hold.
THRUST LEVER QUADRANT AND ENGINE CONTROL PANEL
APR
APR
TO
TO
CLB
CLB
ENGINE
L ENG FIRE
R ENG FIRE
APU FIRE
IDLE
REV
REV
FIRE
FIRE EXT
1
TO/GA
TO/GA
REV
EV
AUTO APR
FIRE
FIRE
ARMED
2
ARMED
AUTO
SYNC
REV
MACH HOLD
N1
OFF
L ENGINE
RUN
N2
R STARTER
OFF
CRANK
OFF
OFF
L STARTER
R ENGINE
RUN
EVENT
OFF
IGNITION
START
OFF
CRANK
START
CFO1801002_023
IDLE
REV 2
May 06/2005
REV 2
Flight Crew Operating Manual
CSP 100-6
Volume 2
18-01-23
POWERPLANT
CONTROLS AND INDICATIONS (Cont)
L ENGINE
R ENGINE
RUN
RUN
OFF
OFF
CFO1801002_015
ENGINE START CONTROLS
OFF
CRANK
START
OFF
CRANK
START
AIR COND/BLEED CONTROL PANEL
AIR SOURCE
NORM
RAM AIR
OFF
PACK ONLY
TRIM AIR
ONLY
ON
L BLEED
R BLEED
XBLEED
OFF
OFF
APU
CFO1801002_003
ON
OV
T
EICAS DISPLAY
85.0 MCT
85.0 MCT
93.0
61.0
NI
MACH
HOLD
VIB
VIB
600
600
ITT
84.7
46
115
7300
IGN
S
T
A
R
7300 T
N2
84.7
OIL PRESS 46
OIL TEMP
FF PPH
APU RPM
APU EGT
115
300
250
CFO1801002_017
IGN
S
T
A
R
T
2
Volume 2
18-01-24
Flight Crew Operating Manual
CSP 100-6
May 06/2005
REV 2
POWERPLANT
EICAS MESSAGES
The powerplant messages are shown on the EICAS. In the table below are the powerplant messages, meanings, inhibits,
and aural warnings along with a brief explanation of each message.
MESSAGE
INHIBITS
L (R) ENGINE
EXCEEDANCE
The respective engine has exceeded a speed or
temperature limit
L (R) ENGINE FIRE
The L (R) ENGINE FIRE CAS, FIRE EI in the
N1 indicator, FIRE indication in the L(R) ENG
FIRE switch, or “LEFT (RIGHT) ENGINE FIRE’
voice message indicates that the engine fire
detection loop has activated. An engine fire is
usually accompanied by other indications, such
as: excessive ITT, erratic or rough engine operation, fluctuating engine indications, or smoke in
the cabin.
L (R) ENG OIL
PRESS LOW
TO/LAND
L (R) ENGINE
FLAMEOUT
The respective engine oil pressure is low
The respective engine has had a flameout
ENGINES FUEL
BYPASS
TO/LAND
Both engine fuel filters are impending bypass
L (R) ENG OIL TEMP
HIGH
TO/LAND
The respective engine oil temperature is high
L (R) ENG ANTI-ICE
FAIL
TO/LAND
The respective engine anti-ice has failed
L (R) ENG
DSPL MISCOMP
TO/LAND
The respective engine N1 or ITT display does
not agree with the other N1 or ITT display
L (R) ENG FUEL SOV
FAIL
TO/LAND
The respective engine fuel shutoff valve has
failed to close when commanded
L (R) ENG OIL TEMP
HIGH
TO/LAND
The respective engine oil pressure is low
L (R) ENG OIL PRESS
HIGH
TO/LAND
The respective engine oil pressure is high
TO/LAND
A higher than normal level of vibration has been
sensed in the respective engine
L (R) ENGINE
VIBRATION
Sep 14/2005
REV 4
“Left (Right)
Engine Fire”
Illumination of either the L or R REVERSER
UNSAFE CAS, or a REV EI indicates an unsafe
thrust reverser condition. The affected engine
should automatically decelerate to idle. The
autostow function will attempt to stow the
reverser doors
L (R) REVERSER
UNSAFE
REV 4
MEANING
AURAL
WARNING
Flight Crew Operating Manual
CSP 100-6
Volume 2
18-01-25
POWERPLANT
MESSAGE
INHIBITS
MEANING
L (R) FADEC FAIL
TO
Major control system failure affecting both channels of the respective FADEC. The engine may
shutdown or got to idle, or engine operation may
be degraded. Failure of the control system may
cause control effect, performance degradation
or a loss of a protective system
L (R) REVERSER FAIL
TO
The respective thrust reverser has failed
L (R) START
ABORTED
TO/LAND
The ground engine start on the respective
engine has been aborted
L (R) STARTER FAIL
TO/LAND
The respective engine starter has failed
L (R) STARTER FAIL
ON
TO/LAND
The respective engine starter has failed ON
DOWNLOAD FADEC
TO/LAND
The FADEC maintenance data should be downloaded
ENG SYNC/M-HOLD
FAIL
TO/LAND
Engine SYNC and Mach hold are not available
L (R) ENG A/ICE FAIL
ON
TO/LAND
The respective nacelle anti-ice has failed ON
L (R) ENG FUEL TEMP
LOW
TO/LAND
The fuel temperature in the respective engine
filter is low
L (R) ENG IGN FAUL
TO/LAND
A fault has been detected in the respective
engine ignition
L (R) ENG THRUST
FAULT
TO/LAND
A fault has been detected in the respective
engine thrust
L (r) ENGINE FAULT
TO/LAND
A fault has been detected in the respective
engine
L (R) ENGINE FUEL
BYPASS
TO/LAND
The respective engine fuel filter is impending
bypass
ENG MACH HOLD
FAIL
TO/LAND
The Mach hold function has run out of authority
L (R) ENGINE MINOR
FAULT
TO/LAND
The engine has detected a minor engine fault
L (R) ENGINE OIL
BYPASS
TO/LAND
The respective engine oil filter is impending
bypass
ENGINE SYNC FAIL
TO/LAND
The engine sync mode has failed
L (R) ENG VIBRATION
FAIL
TO/LAND
Loss of vibration signal from affected engine
AURAL
WARNING
4
Volume 2
18-01-26
Flight Crew Operating Manual
CSP 100-6
Sep 14/2005
REV 4
POWERPLANT
MESSAGE
INHIBITS
L (R) ENGINE ANTIICE FAULT
TO/LAND
Anti-ice bleed over-pressure detection, may
result in higher ITT than normal
L (R) ENGINE OIL
CHIP
TO/LAND
Metal debris detected in engine lube system
AUTO APR OFF
L (R) ENGINE
SHUTDOWN
L (R) REVERSER INOP
Sep 14/2005
REV 4
MEANING
AURAL
WARNING
Auto APR has been selected off
The respective engine has shutdown with the
RUN switch OFF or the respective FIRE switch
pushed
The respective thrust reverser is inoperative
and is mechanically pinned, hydraulically and
electrically isolated
Flight Crew Operating Manual
CSP 100-6
Volume 2
18-01-27
Instruction Sheet
Challenger 300
Flight Crew Operating Manual - Volume 2
REVISION 1
1/04
Sep 13/2004
Flight Crew Operating Manual
CSP 100-6
Volume 2
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