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89 flashcardsby Adam
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1
The engine control unit takes it power from
  • Channel A from permanent magnet alternator and Channel B from essential bus bar
  • Channel A and Channel B of the permanent magnet alternator
  • Channel A from one stator and Channel B from different stator or permanent magnet alternator
2
A FADEC loses its ADC inputs, the pilot should
  • Switch both EECs to Alt
  • Do nothing
  • Switch to stanby instruments of pitot / static
3
In the event of EEC Channel A failing
  • Channel B assumes control
  • The EEC goes into Alternate Mode
  • The engine shuts down
4
A FADEC system consists of
  • EEC, ADC and sensors
  • HMU, ADC and sensors
  • HMU, sensors and EEC
5
With the engine running normally, power to the EEC is supplied by
  • The 115V essential AC bus
  • A dedicated dual winding alternator
  • A dedicated single winding alternator
6
The aircraft AC bus supplies power to the EEC
  • During idle power
  • At all times
  • During engine start
7
A FADEC system controls
  • Engine limit protection
  • Air data and inertial reference system
  • Throttle lever position
8
One advantage of FADEC over the normal hydro-mechanical fuel system is that it
  • Reduces fuel consumption
  • Improves the thrust
  • Improves the engine performance and reduces pilot work-load
9
A FADEC consists of
  • Electronic control and throttle position transmitter
  • Electronic controls, sensors and an HMU
  • Electronic control only
10
A FADEC takes measurements of engine speed,
  • Pressure
  • Temperature
  • Temperature and pressure
11
A FADEC does not have which of the following
  • Control of thrust reverser operation
  • Automatic control of engine fire bottles
  • An automatic starting capability
12
A supervisory EEC sends its output to the
  • HMU/FFG
  • Fuel valve
  • EGT thermocouple unit
13
Electronic Engine Control is powered in flight by
  • The N1 Tachogenerator
  • The transfer busbar
  • The N2 Tachogenerator
14
An EEC's main purpose is to
  • Convert engine sensor inputs to digital format, reduce costs & improve performance
  • Convert engine sensor inputs to digital for display purposes in glass cockpit
  • Reduce pilot workload, improve performance and use less fuel
15
Electronic Engine Control is powered in flight by
  • N1 Tachogenerator
  • The transfer Busbar
  • N2 Tachogenerator
16
A FADEC system controls
  • Air data and inertial reference system
  • Engine limit protection
  • Throttle lever position
17
An Electronic engine control is powered in flight by
  • Supply from the transfer busbar
  • N1 Tachogenerator
  • N2 Tachogenerator
18
In a FADEC system, automatic handover of electrical supply occurs
  • On start up
  • When A & B channels are healthy
  • To Channel A only
19
A FADEC system takes measurements from engine speed,
  • And pressure
  • Tempreature and pressure
  • And tempreature
20
FADEC uses RPM and
  • Airspeed and pressure
  • Tempreature and airspeed
  • Pressure and tempreature
21
Electronic speed control switches on an APU are set at
  • 35%, 75% and 100%
  • 35%, 95% and 100%
  • 35%, 75% and 110%
22
In a FADEC system, the signal to the HMU is the difference between
  • Computed N1 and actual N2
  • Actual N1 and computed N1
  • Computed N2 and actual N1
23
FADECs operate by
  • 1 controlling 1 operating
  • 2 units each capable of independent control
  • 2 controlling 1 operating
24
If a FADEC loses its ADC input, in the short term it will
  • Go into hard redundancy
  • Go to limit protection mode
  • Go into soft redundancy
25
If an engines FADEC system loses air data permanently the pilot will
  • Select alternate pitot static
  • Turn that EEC off
  • Switch to alt on the relevant EEC
26
If the EEC fails to receive any ADC inputs. What will it do
  • Switch off the engine
  • Revert to a hard revisionary control mode
  • Revert to a soft revisionary control mode
27
If the FADEC fails totally, the pilot will
  • Be warned with a light illumination
  • Get no warning
  • Get a warning in the headset
28
In a FADEC engine with a hydromechanical fuel system, how is fuel flow controlled
  • By oil hydraulics
  • By fuel pressure
  • By electro-hydraulic servo valves
29
A supervisory electronic engine control is a system that receives engine operating information and
  • Adjusts a standard hydromechanical fuel control unit to obtain the most effective engine operation
  • Develops the commands to various actuators to control engine parameters
  • Controls engine operation according to ambient tempreature, pressure and humidity
30
In a FADEC system automatic handover of electrical supply occurs
  • To A channel only
  • When A & B channels are healthy
  • On start up
31
In a FADEC system the signal to the HMC is the difference between
  • Computed N1 and actual N2
  • Computed N2 and actual N1
  • Actual N1 and compute N1
32
An electronic engine control unit is powered in flight by
  • N2 Tachogenerator
  • N1 Tachogenerator
  • Supply from the transfer busbar
33
In a FADEC system, active control switchover occurs
  • On engine start-up only
  • When channels A and B are healthy
  • On shutdown
34
In a FADEC system, what determines which channel is in control
  • Whichever is the best channel
  • A is always in control, B is on standby
  • Cockpit selection
35
In a FADEC what is the result of Channel A failing to receive informatoion from a sensor
  • Channel A will take the information from the backup sensor
  • Channel B will assume control
  • Channel A will take the information from Channel B
36
On a FADEC engine the EEC
  • Has electronic control of the hydro-mechanical fuel control unit in all modes
  • Has electronic control of the hydro-mechanical fuel control unit in some modes
  • Has mechanial control of the hydro-mechanical fuel control system
37
Primary power for an electronic engine control is
  • On side 115V AC bus bar supply
  • 115V AC essential bus
  • A Permanent Magnet Alternator
38
Prime function of the EEC is
  • Control position of the bleed valves
  • Control fuel flow
  • Control position of the throttle lever
39
The EEC changes power settings by
  • Changing the airflow input
  • Changing the fuel flow input
  • Changing the throttle lever angle
40
The EEC controls thrust by
  • Moving the throttles
  • Controlling the bleed valves
  • Increasing fuel flow
41
EEC receives signals from RPM sensor and
  • Pressure sensors
  • Tempreature sensors
  • Tempreature and pressure sensors
42
The EEC is powered and able to operate via
  • The aircraft electrical system
  • Only a dedicated alternator
  • A dedicated alternator or the aircraft electrical system independently depending on conditions
43
The EEC uses
  • ARINC 429 formatted data
  • ARINC 629 formatted data
  • Uses either ARINC 429 or 629 formatted data
44
The fuel metering unit has direct inputs via
  • The EEC, fire controls handle and the engine master switch
  • The EEC and the fire control handle
  • Only the EEC
45
The fuel metering valve in the hydro mechanical unit of a FADEC system is operated by
  • Hydraulic servo pressure
  • Fuel servo pressure
  • Electrical servo
46
The HMU of a FADEC engine increases fuel flow by increasing
  • Hydraulic servo pressure
  • Air flow through the compressor
  • Servo fuel pressure
47
If a FADEC loses its ADC input. In the short term it will
  • Go into hard reversion
  • Go into soft reversion
  • Go to limit protection
48
If an engine FADEC system loses air-data permanently, the pilot will
  • Select alternate pitot static
  • Turn that EEC off
  • Switch to Alt on the relevant EEC
49
The maximum LP shaft RPM on a FADEC controlled engine is limited by
  • Input to a computer from a phonic wheel
  • Bleeding air from two VMO capsules
  • Thermocouples fitted in the intake
50
The primary purpose of a FADEC system is to
  • Change analogue inouts into digital information for glass cockpits
  • Save fuel, reduce crew worload, reduce maintenance and prolong engine life
  • Change analogue inputs into digital information for maintenace records
51
The primary purpose of an EEC is
  • To save fuel, reduce workload and reduce maintenance costs
  • To change the analogue inouts into digital format to provide glass cockpit information and reduce flight crew workload
  • To change analogue inputs into digital format to reduce flight crew workload and provide maintenance information
52
What is the purpose of the two resolvers in the throttle control unit
  • To activates the thrust reversers. There is one resolver for each
  • To convert the thrust lever deflections into signals for the ECU
  • To convert the thrust lever deflections into signals for the HMU
53
In a FADEC engine with a hydromechanical fuel system, how is fuel controlled
  • By fuel pressure
  • By electro-hydraulic servo valves
  • By oil hydraulics
54
When an EEC channel reset occurs
  • Standby channel will be active
  • Only channel A is selected
  • Channel B is selected
55
When does the FADEC perform active transfer
  • With weight-off-wheels
  • On start up
  • On connection of ground power
56
In a FADEC system automatic handover of electrical supply occurs
  • To A channel only
  • When A & B channels are healthy
  • On start up
57
In a FADEC system the signal to the HMC is the difference between
  • Computed N1 and actual N2
  • Actual N1 and computed N1
  • Computed N2 and actual N1
58
When the full authority engine electronic control unit is changed by, the rating plug
  • Is replaced every time
  • Stays with the unit
  • Stays with the engine
59
With the EEC in control the throttle levers are always
  • Anywhere between the fully fwd and fully aft positions
  • In the fully forward position
  • In the fully aft position
60
Which statement is most true about a FADEC system
  • It sets up the throttle position to give efficient EPR/thrust
  • It controls fuel flow efficiently
  • It controls all the engine systems efficiently
61
In a FADEC system, how are the power supply windings for Channel A and Channel B wound
  • Two independant generators
  • One generator and one winding
  • On one generator with 2 seperate windings
62
In a FADEC system, what determines which channel is in control
  • Whichever is the best channel
  • By cockpit selection
  • Channel A is always in control, Channel B is on standby
63
In a FADEC system, what does the EEC measure along with RPM
  • Pressure
  • Pressure and temperature
  • Temperature
64
In a FADEC system, what does the EEC measure along with RPM
  • Pressure
  • Pressure and temperature
  • Temperature
65
In a FADEC system, what is the result of Channel A failing to receive information from a sensor
  • Channel B will assume control
  • Channel A will take the information from Channel B
  • Channel A will take the information from the back up sensor
66
The engine rating plug
  • Is permanently connected to the Engine casing
  • Is pemanently connected to the EEC
  • Is connected to the EPR transmitter
67
In- Flight the engine EEC controls
  • Throttle position
  • EGT
  • Fuel flow
68
On a FADEC engine
  • A channel uses a seperate winding of the control alternator to Channel B
  • A and B channel use the same phases of the motor
  • A channel uses control alternator and Channel B uses aircraft bus power
69
On a FADEC engine the EEC
  • Has electronic control of the hydro-mechanical fuel control in some modes
  • Has electronic control of the hydro-mechanical fuel control unit in all modes
  • Has the mechanical control of the hydro-mechanical fuel control system
70
On a FADEC engine, the channel reset
  • Always selects A channel
  • Selects B channel
  • Selects standby which becomes active on the next start
71
On an engine powered by a FADEC, each engine has
  • 1 FADEC with one channel active and the other channel on standby
  • 2 FADEC with one FADEC active and the other on standby
  • 1 FADEC with one channel active and the other channel monitoring with its output drivers de-energised
72
Supervisory EEC sends its output to the
  • Fuel valve
  • HMU/FFG
  • EGT thermocouple circuit
73
Thrust rating on an FADEC controlled engine can be changed by
  • Varying the ballast resistor in the EGT system
  • Changing the engine rating plug
  • Varying the EPR datum plug
74
The air data inputs to the FADEC ECU fails. The result will be
  • Uncorrected data from hard wired analogue sensors is utilised
  • A lack of flight data
  • The ECU reverts to the fail-safe mode
75
The EEC receives its primary power from
  • 115V AC main BUS
  • 115V AC emergency BUS
  • Seperate permanent magnet alternator
76
The main advantage of FADEC is
  • It changes TLA to most efficient EPR rating
  • It has electrical control of hydro mechanical unit in all modes
  • Efficiency is always maximum
77
The maximum LP shaft RPM on a FADEC controlled engine is limited by
  • Thermocouples fitted in the intake
  • Bleeding air from two VMO capsules
  • Input to a computer from a phonic wheel
78
The primary purpose of an EEC is
  • To change analogue inputs into digital format to provide glass cockpit information and reduce flight crew workload
  • To change analogue inputs into digital format to reduce flight crew workload and provide maintenance informaion
  • To save fuel, reduce crew workload, and reduce maintenace costs
79
What are the two basic groups of modern fuel control systems
  • Automatic and manual
  • Hydro-mechanical and electronic
  • Pneumatic and pressure
80
What power supplies the EEC during normal operation
  • Main aircraft aircraft bus
  • A dedicated generator
  • Aircraft batteries
81
When an EEC channel reset occurs
  • Only channel A is selected
  • Channel B is selected
  • Standby channel will be active
82
When both FADEC channels are healthy they will alternate
  • As selected on the flight deck
  • When one channel fails
  • On each engine start
83
When does EEC channel change over occur
  • On engine start up
  • On fault
  • On engine shut down
84
When FADEC is in normal mode
  • Channel B will be in command
  • Channel A will be in command
  • Channel A or B will be in command
85
When re-light is required in flight on a FADEC engine, the pilot selects
  • One igniter
  • Both igniter
  • Igniter selected automatically
86
When the EEC supervisory circuit senses a fault on the engine, the fault annunciator light will be on and the EEC will
  • Remove fuel, down trimming signal only when EEC switch selected off
  • Remove fuel, down trimming signal only after landing
  • Remove fuel, down trimming signal immediately
87
Where does EEC get its air pressure and temperature signal from
  • Fault monitor
  • ADC
  • Thrust management computer
88
Where does FADEC get its air pressure and temperature signal from
  • Thrust management computer
  • Fault monitor
  • ADC
89
Which one of the following is not part of the metering system of the electronic engine computer
  • F.C.U
  • Thrust management computer
  • Fault monitor unit
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