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switch/light; and
• At 55% N2 rpm, the start control valve is de-energized and the ATS disengages.
The ATS is subject to the following starter engagement limits:
STARTER ENGAGEMENT LIMITATIONS
START # ENGAGEMENT TIME COOLING PERIOD
1 30 seconds none
2 30 seconds none
3 & subsequent 30 seconds 5 minutes
POWER PLANT
Description
Vol. 2 19−10−14
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
ENGINE STARTING SYSTEM (CONT'D)
DRY MOTORING # ENGAGEMENT TIME COOLING PERIOD
1 90 seconds 5 minutes
2 & subsequent 30 seconds 5 minutes
Dry-Motoring
Dry-motoring is performed with ignition off and thrust levers at SHUTOFF.
Dry-motoring may be used for engine ground starts and engine airstarts.
IGNITION SYSTEM
Description
Two independent alternating current (AC) ignition systems are provided for each engine. Each
ignition system consists of one ignition exciter and one igniter plug.
Ignition system A is powered by the AC Essential Bus. Ignition system B is powered by the Battery
Bus through a static inverter.
Operation
There are three ignition system modes:
Normal − Prior to engine start, the ignition is armed by selecting either A or B ignition switch/light
at the START/IGNITION panel. When an ignition system is armed, the corresponding white ARM
light illuminates. Ignition is energized upon starter engagement and is de-energized at starter
cutout (55% N2). While an ignition system is energized, the corresponding green ON light
illuminates and the IGNITION A(B) advisory EICAS message appears.
Continuous ignition − Continuous ignition may be selected by pressing the CONT ignition
switch/light on the START/IGNITION panel. Both ignitions A and B are energized. When
continuous ignition is selected, both green ON lights illuminate and the IGNITION A/B advisory
EICAS message appears.
Continuous ignition must be used during the following flight conditions:
• Takeoff and landings on contaminated runways;
• Takeoff with high crosswind components (greater than 10 knots);
• Flight through moderate or heavier intensity rain;
• Flight through moderate or heavier intensity turbulence; or
• Flight in the vicinity of thunderstorms.
Autoignition (aerodynamic stall protection) – Automatic activation of continuous ignition is
based upon angle-of-attack (AOA) data. Both systems A and B are energized by the stall warning
computer, and remain on until the airplane flight attitude is corrected.
POWER PLANT
Description
Vol. 2 19−10−15
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
IGNITION SYSTEM (CONT'D)
CAUTION
Activation of the Stall Protection System Test will activate continuous
ignition.
Both ignition systems A and B are disabled on the associated engine when the L(R) ENGINE FIRE
PUSH switch/light is selected. If continuous ignition was in use, the white ON legend of the CONT
switch/light will extinguish, but the green ON lights in the switch/lights remain illuminated, and the
IGNITION A/B advisory EICAS message remains displayed (to advise the crew that continuous
ignition is still active on the unaffected engine).
Ignition System
Figure 19−10−10
VIBRATION MONITORING SYSTEM
Description
The power plant consists of two major rotating assemblies, the N1 fan and N2 core sections. Each
assembly is continuously monitored for vibration. Indications are displayed on the EICAS primary
page.
POWER PLANT
Description
Vol. 2 19−10−16
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
VIBRATION MONITORING SYSTEM (CONT'D)
Operation
N1 Fan
N1 fan core vibration is displayed as a numeric readout on the EICAS primary page as FAN VIB.
When the N1 vibration level is 2.7 mils or greater, the color of the readout changes to amber.
There is no associated caution EICAS message.
N2 Core
N2 core vibration levels are continuously monitored but are presented only when vibration levels
exceed a target value. An amber VIB icon appears in the middle of the N2 gauge when the
vibration target value is exceeded. There is no associated caution EICAS message.
Vibration Monitoring System Test
The system is tested by selecting the VIB switch on the ENGINE CONTROL Panel to the TEST
position. In the TEST position, high vibration levels are simulated in the electrical circuitry. The
following indications appear on selection of the ENGINE VIB test switch:
• FAN VIB readouts increase to 3.6 mils, changing from green to amber, passing through
　
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