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Refer to Chapter 2, Air Conditioning and Pressurization, and Chapter 14, Ice and Rain Protection for more discussion on
the bleed air system.
V 1
POWERPLANT
Volume 2 Flight Crew Operating Manual May 06/2005
18-01-14 CSP 100-6 REV 2
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.
CFO1801002_018
N2
COMPRESSOR
OUTPUT
SHAFT AIR TURBINE
STARTER
STARTER
CONTROL
VALVE
FLOW
CONTROL
VALVE
CROSSBLEED
VALVE
AIR
FLOW
ECU
ENGINE CONTROL
PANEL
INTEGRATED
AIR
SYSTEM
(IAS)
APU,
GROUND AIR
SUPPLY
OR ENGINE
CROSS-BLEED
START
ENGINE
L ENG FIRE APU FIRE R ENG FIRE
1 FIRE EXT 2
AUTO
SYNC
AUTO APR
L STARTER
IGNITION
R STARTER
MACH HOLD
EVENT
OFF
N1
N2
OFF
START CRANK
OFF
CRANK START
ON
ON
FIRE
ARMED ARMED
OFF
FIRE FIRE
V 2
POWERPLANT
May 06/2005 Flight Crew Operating Manual Volume 2
REV 2 CSP 100-6 18-01-15
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
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.
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.
CFO1801002_015
CRANK START
OFF
CRANK START
OFF
R ENGINE
OFF
RUN
L ENGINE
OFF
RUN
POWERPLANT
Volume 2 Flight Crew Operating Manual May 06/2005
18-01-16 CSP 100-6 REV 2
ENGINE STARTING SYSTEM (Cont)
　
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