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Worksheetspara recu de propu
Total questions: 97
Worksheet time: 49mins
What does the engine fuel and control system?
calculates the quantity of fuel necessary to make the commanded thrust.
calculates the amount of fuel needed to ignite the ordered thrust system.
What is the chapter the engine air system?
chapter 75
chapter 76
chapter 22-76
The engine fuel and control system has three subsystems:
Fuel distribution
Fuel control.
Fuel indication.
Fuel ingnition
Fuel control.
Fuel indication.
Who controls the fuel and engine control system?
the DEU
the EEC
the FMC
How many channels does the EEC use input data to calculate the engine fuel and control outputs to operate the engine?
Four channels
Three channels
Two channels
The airplane fuel system supplies pressurized fuel from?
the forward or main tank.
the center or main tank.
the rigth or main tank.
What is the chapter on the aircraft fuel system?
(CHAPTER 28)
(CHAPTER 75)
(CHAPTER 11)
The maximum certified thrust?
is the thrust the engines will produce if the thrust levers are put against the forward stops.
It is the thrust that the engines will produce if the thrust levers are placed against the rear stops.
The rated thrust?
is the maximum thrust the autothrottle will command.
is the maximum measured thrust that the autothrottle will control.
The EEC gets thrust reverser translating sleeve position?
from a linear variable differential transformer (LVDT).
of a linear AC differential transformer (LVDT).
The EEC sends thrust reverser position to the DEUs for thrust reverser indication?
on the engine display units (DEU).
on the display units (DUs).
What is the thrust reverser chapter?
(SECTION 75-13)
(SECTION 78-30)
(SECTION 72-31)
The EEC uses the thrust lever resolvers (TLRs)?
on the corridor support to obtain the thrust measurement angle (TRA).
on the aisle stand to get thrust resolver angle (TRA).
The start levers and fire handle send signals directly to the HPSOV?
in the HMU. This lets the flight crew shut down the engine in normal or emergency situations.
In the FMC. This allows the crew to shut down the engine in normal or emergency situations.
The EEC does not close the HPSOV.
true
false
what is the chapter on the engine controls?
(CHAPTER 75)
(CHAPTER 76)
(CHAPTER 13)
The start levers send a start signal to the EEC through the DEUs in the position?
In the IDLE position, the EEC operates the engine ignition system
In the NORMAL position, the EEC operates the engine ignition system
What is the chapter the ignition chapter the engine?
(CHAPTER 12)
(CHAPTER 74)
(CHAPTER 75)
Shows the position of the HPSOV?
The ENG VALVE OPEN light
The ENG VALVE CLOSED light
The EEC gets and receives data from these airplane systems and components through the two DEUs:
• Engine and fuel indication
• Start lever IDLE or CUTOFF command
• Air data inertial reference unit (ADIRU) 1 and 2
• Flight management computer (FMC) and control display units (CDUs)
• Flight data acquisition unit (FDAU).
• Engine and fuel gauge
• Idle command or kick-start cutoff
• Air Data Inertial Reference (ADIR) 1 and 2
• Flight Guidance Computer (FMC) and Control Display Units (CDU)
• Flight Data Acquisition Unit (FDAU)
what is chapter is indicating the engine indicating ?
(CHAPTER 75)
(CHAPTER 77)
(CHAPTER 76)
The ADIRU sends?
datos de presión de aire total y estática y de temperatura de aire total al FMC a través de las DEU.
total and static air pressure and total air temperature data to the EEC through the DEUs.
Does this provide a connection between the CDU and the DEUs?
The FMC.
The EEC
The FDAU
Shows EEC maintenance data, and sends commands to the EEC to do system BITE tests?
The CDU.
The EEC
The DEU.
Collects engine parameter data it sends this data to the flight data recorder (FDR)?
The FDAU
The ECC
The CDU
The EEC sends a signal to the EEC ALTN light?
on the P6 aft overhead panel if the EEC is in soft or hard alternate modes.
on the P7 aft overhead panel if the EEC is in soft or hard alternate modes.
on the P5 aft overhead panel if the EEC is in soft or hard alternate modes.
When the EEC switch is in the off position?
the FMC goes to the hard alternate mode.
the EEC goes to the hard alternate mode.
If the ENGINE CONTROL or ALTN light is on?
the MASTER CAUTION lights also come on.
the MASTER WARNING lights also come on.
These are the major components of the engine fuel distribution system:
•Fuel pump assembly
•IDG oil cooler
•Fuel pump attaches
•IDG oil cooler
•Fuel pump assembly
•IDG fuel cooler
what is function the fuel filter in the pump?
Cleans the fuel that goes to the HMU.
Cleans the oil that goes to the HMU.
These units heat the fuel before it goes to the HMU:
• IDG oil cooler
• Oil/fuel heat exchanger
• Servo fuel heater.
• IDG fuel cooler
• Oil/fuel heat exchanger
• Servo fuel heater.
Fuel goes from the fuel nozzle filter to the untagged fuel nozzles and to the burner staging valve (BSV) in the?
PRE SB CFM56-7B 73-44
PRE SB CFM56-7B 75-44
PRE SB CFM56-7B 73-43
When the BSV opens?
fuel goes to the staged fuel nozzles.
The fuel reaches the fuel nozzles which are not staggered.
What is located the fuel nozzle filter?
is forward the top of the engine fan case at the 10:00 position.
is near the top of the engine fan case at the 10:00 position.
where is connected the fuel pump?
Assembly attaches to the fwd face of the accessory gearbox (AGB) on the right side of the engine fan case.
assembly attaches to the aft face of the accessory gearbox (AGB) on the left side of the engine fan case.
where is connected the IDG oil cooler?
attaches at the rear of the fan frame at the 7:00 position.
attaches at the rear of the fan frame at the 6:00 position.
where is connected the servo fuel heater?
attaches to the main oil/fuel heat exchanger, which attaches to the top of the fuel pump assembly.
It connects to the main oil/fuel heat exchanger, which connects to the bottom of the fuel pump assembly.
What is the chapter the engine oil chapter about the main oil/fuel heat exchanger
SECTION 75-20)
SECTION 79-20)
SECTION 79-22)
Where is located the BSV?
is in the core section of the engine. It is at the 7:00 position on the low-pressure compressor case.
is in the core section of the engine. It is at the 6:00 position on the high-pressure compressor case.
From where it goes the fuel manifold goes?
from the fuel nozzle filter, down the left side of the fan case to the fan support strut at the 6:00 position.
from the fuel nozzle filter, up the left side of the fan case to the fan support strut at the 7:00 position.
how many fuel nozzles are there in the combustion case assembly?
20
22
10
The fuel pump assembly has two types of components:
These components are fuel pumps and filters.
These components are oil pumps and filters.
The fuel pump assembly has?
There is a low-pressure fuel pump and a high-pressure fuel pump
There is two high-pressure fuel pump and a high-pressure fuel pump
The low pressure fuel pump?
is a inercial impeller pump
is a centrifugal impeller pump
The high pressure pump?
is a single element, positive displacement gear pump.
is two single element, negative displacement gear pump.
The HMU is connected?
attaches to the fwd end of the fuel pump assembly.
attaches to the aft end of the fuel pump assembly.
The fuel pump assembly attaches?
to the aft side of the AGB
to the fwd side of the AGB
There are two fuel filters in the fuel pump assemblies:
the oil filter and the servo wash filter.
the fuel filter and the servo wash filter.
What is the chapter the fuel flow indicating section about on the inlet fuel filter bypass light?
(SECTION 73-30)
(SECTION 75-22)
The servo wash filter?
is not a Line Replaceable Unit (LRU).
is not a Line Reducing Unit (LRU).
The IDG oil cooler attaches to the fan case at the?
7:00 position
6:00 position
what is the electrical chapter on the IDG cooling system?
(CHAPTER 24)
(CHAPTER 22)
The servo fuel heater?
is a heat exchanger which uses the warmer scavenge oil temperature to increase the servo fuel supply temperature.
is a heat exchanger which uses the warmer scavenge fuel temperature to increase the servo fuel supply temperature.
The servo fuel heater is connected?
to the engine fuel/oil heat exchanger.
to the engine oil/fuel heat exchanger.
The engine oil chapter for more information on the oil
fuel heat exchangerin the section?
(SECTION 79-20)
(SECTION 79-22)
(SECTION 73-20)
How many fuel nozzles are there?
There are ten unstaged and two staged fuel nozzles in the combustion chamber.
There are ten unstaged and ten staged fuel nozzles in the combustion chamber.
The BSV has two positions:
open and closed.
open and normal
the BSV?
prevents fuel flow to the staged nozzles.
supply fuel flow to the staged nozzles.
Fuel flows only to the unstaged nozzles when the staged nozzles are closed, all metered fuel goes?
through the ten unstaged nozzles only.
through the two unstaged nozzles only.
The BSV has four switches. These switches give?
BSV position to channel A and channel B of the EEC.
BSV position to channel B and channel A of the EEC.
what is location the BSV?
is at the 6:00 position of the engine core section
is at the 7:00 position of the engine core section
The EEC uses these inputs to find fuel/air ratio in the combustor:
T3 (high pressure compressor discharge temperature)
PS3 (high pressure compressor discharge pressure)
FMV position (fuel flow)
N2 speed
T2 (high pressure compressor discharge temperature)
PS3 (high pressure compressor discharge pressure)
FMV position (fuel flow)
N1 speed
The EEC controls?
the BSV based on fuel air ratio.
the BSV based on oil air ratio.
The EEC always commands the BSV open for these conditions (unstaged):
N2 speed less than 80%
N1 speed greater than 55%
Engine at steady state on the ground
EEC cannot read the BSV position.
N2 speed less than 55%
N2 speed greater than 80%
Engine at steady state on the ground
EEC cannot read the BSV position.
The EEC finds a NO DISPATCH condition and sends a signal to the DEU when one of these failures occur:
BSV failed in the open position
• Control current to the BSV solenoid out of range and FMC in single channel operation.
BSV failed in the closed position
• Control current to the BSV solenoid out of range and EEC in single channel operation.
The fuel manifold supplies fuel to the fuel nozzles. How many fuel nozzles are there?
Twenty
Thirty
Energizes the ENGINE CONTROL light on the P5 aft overhead panel and the MASTER CAUTION lights when the DEU senses the airplane on the ground and the EEC has detected a no dispatch condition?
The DEU
The FDAU
FUEL MANIFOLDS TYPES:
One fuel manifold is the unstaged fuel manifold, the other is the staged fuel manifold.
One oil manifold is the unstaged oil manifold, the other is the staged fuel manifold.
.The HPSOV is part of?
The HMU
The CDU
The DEU
The staged fuel manifold supplies fuel?
to the ten staged fuel nozzles
to the twenty staged fuel nozzles
All of the fuel nozzles have primary and secondary fuel flow at approximately?
15psi
125psi
25psi
30psi
the fuel nozzles open in the primary fuel flow mode. When the fuel pressure increases to approximately 125 psi?
the oil nozzles also closed in secondary fuel flow mode.
the fuel nozzles also open in secondary fuel flow mode.
The nozzles with a silver band?
have a higher fuel flow than the other sixteen nozzles.
have a lowher fuel flow than the other nineteen nozzles.
These are the major engine control system components:
• Airplane data interfaces.
• Sensors.
• Electronic engine control (EEC).
Display Engine Unit (DEU)
• Airplane data interfaces.
• Sensors.
• Electronic engine control (EEC).
• Hydromechanical Unit (HMU).
The EEC sends engine system data to the airplane all of this data goes?
through DEU 1 or DEU 2.
through DEU A or DEU B
The autothrottle computer can operate?
the thrust levers.
the ATC inlet levers.
See the autothrottle section for more information on auto throttle computer control of the thrust levers in the section?
(SECTION 75-22)
(SECTION 22-31)
The EEC has an interface with these engine systems and components:
• * Engine identification plug
• * Hydromechanical unit (HMU)
• * Engine air control system
• * Engine sensors
• * Fuel flow transmitter
• * EEC alternator
* Ignition system
• * Engine identification plug
• * Hydromechanical unit (HMU)
• * Engine air control system
• * Engine sensors
• * Fuel flow transmitter
• * CDU alternator
* Fuel system
The EEC uses?
the engine observation plug for ignition rating and other engine information.
the engine identification plug for thrust rating and other engine information.
The HMU supplies?
metered fuel for combustion and servo fuel pressure for engine systems operation.
metered fuel for combustion and servo oil pressure for engine systems ignition
These are the servo fuel systems the EEC controls through the HMU:
Variable states vanes (VSVs).
Variable bleed vanes (VBVs).
Transient bleed valve (TBV).
Low pressure turbine active clearance control (LPTACC).
High pressure turbine active clearance control (HPTACC).
Variable stator vanes (VSVs).
Variable bleed valves (VBVs).
Transient bleed valve (TBV).
Low pressure turbine active clearance control (LPTACC).
High pressure turbine active clearance control (HPTACC).
The EEC uses input data from various engine sensors to calculate the engine fuel and control outputs for engine operation. These are the engine sensors:
T12 (inlet total temperature)
PT25 (high pressure compressor inlet temperature)
T3 (high pressure compressor discharge temperature)
HPTACC sensor
T49.5 (second stage low pressure turbine nozzle temperature)
P0 (inlet static pressure)
PS3 (high pressure compressor discharge pressure).
T12 (inlet total temperature)
PT125 (low pressure compressor inlet temperature)
T3 (high pressure compressor discharge temperature)
HPTACC sensor
T49.5 (first stage low pressure turbine nozzle temperature)
P0 (inlet static pressure)
PS5 (high pressure compressor discharge pressure).
The EEC controls ac power from the airplane electrical power system to operate?
the left and right ignition systems on the engine.
the right and left fuction systems on the engine.
The engine fuel and control system has an interface with these airplane systems and components:
Display electronic units (DEUs).
Start lever coming command.
Engine fire switches.
AC transfer bus A or B.
Autothrottle computer.
Thrust lever angle.
Engine strut.
Thrust reverser sleeve position.
Display electronic units (DEUs).
Start lever stop command.
Engine fire switches.
AC transfer bus 1 or 2.
Autothrottle computer.
Thrust lever angle.
Engine strut.
Thrust reverser sleeve position.
The engine fuel and control system connects through the ARINC 429 bus to these components:
* Common display system display electronics units (DEUs)
* Autothrottle computer.
* Common display system Fligh Management Computer (FMC)
* Autothrottle computer.
The CDU?
shows DEU maintenance data and sends commands to the FMC to do system BITE tests.
shows EEC maintenance data and sends commands to the EEC to do system BITE tests.
The FDAU?
collects engine parameter data. It sends this data to the flight data recorder (FDR).
collects engine parameter data. It sends this data to the flight Management Computer (FMC).
The FMC gets and sends CDU commands to the EEC through?
The DEUS
The FMC
The CDU
When pulled up, engine fire switches send a close command to?
the HPSOV in the EEC
the HPSOV in the HMU.
The EEC uses?
the airplane transfer buses for power when it does not receive power from the DEU alternator.
the airplane transfer buses for power when it does not receive power from the EEC alternator.
See the autothrottle section for more information in the section?
(SECTION 22-31)
(SECTION 25-71)
See the engine controls section for more information in the section?
(CHAPTER 76)
(CHAPTER 75)
The EEC monitors?
thrust reverser position normal
thrust reverser sleeve position
The ADIRU sends total air pressure and temperature data to?
the EEC the EEC uses this data to control engine thrust.
the EEC the FMC uses this data to control engine thrust.
The FMC controls the CDU. The FMC sends and receives CDU commands to and from the EEC through?
The DEUs
The CDU
These components of engine fuel and control system are on the left side of the engine:
T3 sensor.
PS3 pressure port.
EEC alternator.
PT25 sensor.
Hydromechanical unit (HMU).
T5 sensor.
PS3 pressure port.
EEC alternator.
PT125 sensor.
Hydromechanical unit (HMU).
These components of the engine fuel and control system are on the right side of the engine:
ECC wiring harness.
TCC sensor.
dentification (ID) plug.
Engine electronic control (EEC).
T3 sensor.
EGT wiring harness.
TCC sensor.
dentification (ID) plug.
Engine electronic control (EEC).
T12 sensor.
