曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
none
none
5 minutes
DRY MOTORING # ENGAGEMENT TIME COOLING PERIOD
1
2 & subsequent
90 seconds
30 seconds
5 minutes
5 minutes
POWER PLANT
For Training Purposes Only
May 03
18-17
P I LOT T R A I N I N G GU I D E
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 at 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
• flight in the vicinity of thunderstorms
Auto-ignition (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.
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
CAUTION
POWER PLANT
18-18 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
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 18-10
‘B’ Circuit
‘A’ Circuit
SPS
Both on Cont COMPUTER
P604_18_005
IGNITION
S
T
A
R
T
S
T
A
R
T
S
T
O
P
S
T
O
P
CONT
A
B
ARM
ON
ARM
ON
STOP STOP
START
L-ENG-R
START
ON
POWER PLANT
For Training Purposes Only
May 03
18-19
P I LOT T R A I N I N G GU I D E
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.
Operation
N1 Fan
N1 fan 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 2.7 mils
• Amber VIB icons appear on the N2 dials
ENGINE CONTROL Panel
Figure 18-11
TEST
2
TE
ARM
TEST OFF
3
TEST
1 TEST
APR VIB
OFF
ON
ENG
SPEED
LH RH
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
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