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
take the preselected fuel quantity on the aircraft.
Throughout the automatic refuel operation the FQI
computer monitors the density of fuel in each tank
and the distribution of the load.
MULTI-TANK INDICATOR (MTI)
A multi-tank indicator displays the fuel quantity in
each tank.
PRESELECTOR
The preselector shows the preselected and actual total
fuel quantities as monitored by the computer.
L/G CONTROL LEVER
The computer receives ground/flight information from
the landing gear control lever. The FQI computer
receives ground information from the landing gear,
when selected DOWN with aircraft on jacks. This signal
is used to provide electrical supply to the FQI
computer in this specific configuration.
ADIRUs
Acceleration data is received from Air Data Inertial
Reference System during flight and is used as an
alternate source of attitude.
The Air Data Inertial Reference Units (ADIRUs) send
the acceleration/attitude informations.
Normally, effects of attitude, changes in
acceleration, effective pitch and roll angles are
calculated from the height of fuel at each probe and
the knowledge of the tank geometry stored in the
computer memory.
CFDS
ARINC 429 output links transmit BITE information from
the Computer to the Centralized Fault Display System.
The Centralized Fault Display System (CFDS) monitors
fault conditions and BITE.
TMUFUEB01-T01 LEVEL 3
EFFECTIVITY 28-42-00 Page 4
Sep 30/99
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 244
ALL
QUANTITY INDICATING
FMGC
Fuel parameters are sent to the Flight Management and
Guidance Computers (FMGC) for navigation computations.
ECAM
Total and individual tank fuel mass information is
sent to the ECAM display unit.
TMUFUEB01-T01 LEVEL 3
EFFECTIVITY 28-42-00 Page 5
Sep 30/99
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 245
ALL
SELF EXAMINATION
What happens if one channel of the FQIC fails?
A - Half of the Quantity Indicating data is
no longer available.
B - FQIS operates normally, only CFDS report
will indicate failure.
C - Fuel warning is triggered in addition to
CFDS report.
What happens if a quantity probe (other than 13
or 14) fails?
A - Corresponding tank qty display flashes.
B - Quantity indication disappears.
C - Quantity indication remains the same.
TMUFUEB01 LEVEL 3
EFFECTIVITY 28-42-00 Page 6
Sep 30/99
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 246
ALL
28 - FUEL SYSTEM
28-46-00 FUEL LEVEL SENSING
CONTENTS:
General
High Level
Low Level
Full level
Underfull level
Overflow Level
Temperature Sensing
Self Examination
TMUFUEC01 LEVEL 3
EFFECTIVITY 28-46-00 Page 1
Oct 31/99
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 247
ALL
FUEL LEVEL SENSING
GENERAL
The aircraft is equipped with two multi-channel Fuel
Level Sensing Control Units (FLSCUs) and a third one,
if the Additional Center Tank (ACT) is installed.
They provide high fuel level sensing, low fuel level
sensing, full fuel level sensing, underfull fuel level
sensing, overflow level and temperature sensing.
Fuel level and temperature sensors feed signals to
the multi-channel amplifiers.
The FLSCUs detect and amplify the signals and trigger
switching functions in the appropriate circuits.
HIGH LEVEL
The high level sensors, when immersed in fuel, signal
the associated tank refuel valve to shut when the MODE
SELECT switch is set to REFUEL.
Wet high level sensors cause the associated:
- tank refuel valves to shut,
- blue HI LVL lights to come on, on the
refuel/defuel control panel (800 VU).
Wet center tank high level sensor causes fuel transfer
from optional ACT to center tank to stop.
LOW LEVEL
Exposure of the center tank low level sensors causes
the center tank pumps to stop after a time delay.
Exposure of the inner cell low level sensor to air
results in immediate opening of the intercell transfer
valves.
Exposure of the inner cell low level sensor to air for
30 seconds causes LO LEVEL warning to appear on ECAM.
A separate low level sensor signals the IDG fuel return
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
ATA 28 FUEL SYSTEM(29)
