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Worksheets2.2.2.2
Total questions: 81
Worksheet time: 41mins
The auto flight system (AFS) calculates orders to automatically control the (level 1)
Flight controls and the engines.
The Yaw Damper and the engines.
The Primary Flight Display and the Navigation Display.
During auto flight system controls flight control and thrust system, side sticks and thrust levers (level 1)
Do not move.
Move automatically.
Move automatically at high speed.
The auto flight system is designed around four computers: (level 1)
02 Flight Management and Guidance Computers (FMGCs) and 02 elevator aileron computers (ELACs).
02 Flight Management and Guidance Computers (FMGCs) and 02 Flight Augmentation Computers (FACs).
02 Flight Management and Guidance Computers (FMGCs) and 02 spoiler elevator computers (SECs).
During AFS operation, side sticks and thrust levers: (level 2)
Move automatically,
Do not move automatically,
Move accordance with AFS order.
The main parts of the AFS are: (level 1)
FM, FG, FAC
FM, ADIRU, FAC
FM, MCDU, FAC
How many FMGC are installed in A320/A321 A/C? (level 1)
1
2
3
Which are the Automatic Flight System (AFS) calculates? (level 1)
The AFS calculates orders to automatically control the flight controls and engines,
The AFS calculates orders to send to FCU and MCDU,
The AFS calculates orders to automatically control the side sticks and thrust levers.
The auto flight system computes orders and sends them to the: (level 1)
Electrical Flight Control System (EFCS) and Air Data & Inertial Reference Systems (ADIRs).
Full Authority Digital Engine Control (FADEC) and Air Data & Inertial Reference Systems (ADIRs).
Electrical Flight Control System (EFCS) and to the Full Authority Digital Engine Control (FADEC).
The MCDUS are used for: (level 1)
Long-term control of the aircraft.
Short-term control of the aircraft.
Maintenance activity only
The FIDS function is active in: (level 1)
The FAC 1
The FAC 2
The FAC 1 or FAC 2 if FAC 1 has a failure
The basic functions of the FACS are the: (level 1)
Rudder control and the flight envelope protection.
Engines control and the flight envelope protection.
Rudder control and the Flight Management.
The FMGC functions can be controlled from: (level 1)
The MCDUs and rudder trim control panel.
The FCU and rudder trim control panel.
The FCU and MCDUs.
The FMGC functions are: (level 1)
Flight guidance and flight envelope protection
Flight management and Flight guidance
Flight management and flight envelope protection
Which unit will let the pilots control the functions of the FMGCs (Flight management and guidance computers)? (level 1)
The FCU (Flight Control Unit),
The MCDUs (Multipurpose Control and Display Units),
The FCU and MCDUs.
Which part of FMGCs (Flight management and guidance computers) gives the functions related to the aircraft control? (level 1)
The FM part (Flight Management),
The FG part (Flight Guidance),
The FE part (Flight Envelope).
The basic functions of the flight augmentation computer (FAC) are: (level 1)
Yaw damper, rudder trim, rudder travel limitation, flight envelope protection and FIDS (Fault Isolation and Detection System).
Yaw damper, rudder trim and rudder travel limitation.
Yaw damper, rudder travel limitation and flight envelope protection.
The rudder travel limiting unit limits the deflection of the rudder according to the: (level 1)
Aircraft vertical speed.
Aircraft speed.
Wind speed.
The fault isolation and detection system (FIDS) allowed interface between the auto flight system and the centralized fault display system (CFDS): (level 1)
Only available in FAC 1.
Only available in FAC 2.
Available in FAC1 and FAC 2
The trim function of FAC is: (level 1)
Rudder trim
A pitch trim
Rudder trim and pitch trim
Rudder travel limitation is a function of: (level 1)
FAC only
FAC in normal and ELAC in alternate
ELAC only
The Management part of FMGC mainly provides: (level 1)
Navigation, performance optimization, radio navigation tuning and information display management
Flight plan selection with its lateral and vertical functions. Navigation, performance optimization, radio navigation tuning and information display management.
Flight plan selection with its lateral and vertical functions, autopilot, flight director and AUTOTHRUST.
The Fault Isolation and Detection System (FIDS) is activated with: (level 1)
FAC in position 1 only,
FAC in position 2 only,
Both FACs in position 1 and 2.
The FCU allowed: (level 1)
The modification and the display of flight plans.
The engagement of the autopilot, Flight Director and AUTOTHRUST functions.
The modification of the parameters associated with the flight management functions.
FCU provides the short term interface as: (level 1)
Engagement of the autopilot, flight director and A/THR functions.
Engage/disengage AP, disengage A/THR, select cabin landing altitude.
Select air speed, heading, cabin landing altitude.
The flight management part mainly provides the flight plan selection with its: (level 1)
Vertical functions.
Lateral functions.
Lateral and vertical functions.
The FCU is used for: (level 1)
Long-term control of the aircraft.
Short-term control of the aircraft.
Back up control for sidestick
The Multipurpose Control and Display Units (MCDUs) are used for: (level 1)
Medium-term control of the aircraft,
Short-term control of the aircraft,
Long-term control of the aircraft.
The flight guidance part provides: (level 1)
The autopilot, Flight management and AUTOTHRUST functions.
Performance optimization, Flight Director and autothrust functions.
The autopilot, Flight Director and AUTOTHRUST functions.
The functions of the FG part are: (level 1)
AP, FD, A/THR
AP, FD, flight plan
AP, FD, A/THR, flight plan
The FD is displayed on: (level 1)
PFD
PFD and ND
ND
The flight director (FD) displays the guidance commands on: (level 1)
Both Navigation Displays (NDs).
Both Primary Flight Displays (PFDs).
Lower ECAM Display.
What is purpose of FD? (level 1)
Helps pilot to monitor the AP orders if AP engaged
Displays the Flight orders which would be followed if AP not engaged
Helps pilot to monitor the AP orders if AP engaged and Displays the Flight orders which would be followed if AP not engaged
The AP (Autopilot) is function of: (level 1)
The Flight Guidance part,
The Flight Management part,
The Flight Envelope part.
For maintenance purposes, the autopilot can be engaged on ground with: (level 1)
Both engines running.
Both engines shut down.
Hydraulic power available.
The autopilot can be engaged: (level 1)
For at least 5 seconds after lift-off.
In cruise only.
At top of climb.
The second autopilot can be engaged when: (level 1)
Cruise mode engaged.
Approach mode engaged.
Approach mode engaged and ILS is armed.
The AP function gives orders to control: (level 1)
The position of the control surfaces on the pitch, roll and yaw axes.
The nose wheel steering
A or b is corrected
With aircraft in cruise phase and AP1 (Auto Pilot) is engaged. Can you engage the AP2? (level 1)
Yes, but the AP1 will disengage,
No, the AP1 has higher priority in cruise phase,
Yes, both APs can be engaged at the same time in cruise phase.
The AP (Auto Pilot) can be engaged? (level 1)
In flight, provided the aircraft has been airborne for at least 5 seconds,
On ground with both engines shutdown,
In flight, provided the aircraft has been airborne for at least 5 seconds or on ground with both engines shutdown.
Each PFD show –FD2 mean that: (level 1)
no FD symbols can be displayed on PFD1 and FD2 is engaged on the F/O side.
FD2 is engaged on both PFD.
FD 2 symbol cannot displayed on PFD2
The flight director (FD) functions engage automatically: (level 1)
As soon as the system is electrically supplied and logic conditions are fulfilled.
As long as no AP/FD mode is active.
When the take-off mode engaged.
The Flight Director is engaged: (level 1)
By pressing the FD P/B on the FCU
Automatically at system power rise
By selecting a mode on the FCU
The A/THR (Auto thrust) function can be engaged: (level 1)
Manually from the dedicated P/BSW (Push button switch) from the FCU (Flight Control Unit),
Automatically when some conditions are fulfilled.
Automatically or manually
How can we initiate power up test for FCU when AC is energized. (level 3)
Pull CB of one of the FCU and wait 7 minutes
Pull both CB of FCUs and wait 7 minutes
Pull both CB of FCUs and wait 1minute
Which computer can make power up test in flight? (level 3)
FMGC
FAC
FCU
Which AFS LRU (Auto Flight System Line Replaceable Unit) can make safety test on ground or in flight? (level 3)
The FCU (Flight Control Unit),
The MCDUs (Multipurpose Control and Display Units),
The FMGCs (Flight management and guidance computers),
The rudder trim control signal from the rudder trim control panel is sent to: (level 3)
the FM part of the FMGC
the FAC
the FG part of the FMGC
Which is correct statement when AP is not engaged? (level 3)
In normal configuration, the yaw damper order calculated by the ELAC provides turn coordination; dutch roll damping and engine failure compensation.
If both ELACs fail the yaw damper order calculated by the FAC provides turn coordination; dutch roll damping and engine failure compensation.
the FAC calculates the yaw damper order except in LANDING mode where it is computed by the Flight Management and Guidance Computer (FMGC).
The rudder travel limitation is computed by: (level 3)
The FAC.
The Rudder travel limiting unit.
The FMGC
IF AP is not engaged, which computer calculates yaw damper order? (level 3)
ELAC
FAC
FCU
If AP engaged, can we use rudder trim selector to trim rudder? (level 3)
yes, if AC in flight
No
Yes, if AC on ground
For the yaw damper actuator 1, the changeover logic get fail signal of selector valves or FAC 1 from: (level 3)
the hydraulic press switch.
The LVDT
The RVDT
Turn coordination calculation base on: (level 3)
ENG thrust
Information entered in MCDU
FGMC roll order.
Which computer calculates speed limit? (level 3)
FMGC
FAC
ADIRU
Which function of FAC is independent on FAC engagement? (level 3)
Flight envelop protection
Rudder control
Yaw damper
The mandatory parameter used by FAC for Alpha Floor protection is: (level 3)
A/C maximum speed
A/C minimum speed
A/C angle of attack
Which parameter FACS must be use to control the VMAX speed (level 3)
Landing gear level
Slat/Flap position
Rudder position
Low energy warning is available when: (level 3)
A/C altitude between 100 ft and 2000 ft and alpha floor condition is triggered.
The current thrust, it is not possible to recover a positive flight path angle through pitch control and A/C altitude between 100 ft and 2000 ft out of alpha floor condition.
AOA excessive value
When the A/THR function is engaged, A/THR is not active if: (level 3)
At least one thrust lever is above the FLX/MCT detent and both thrust levers are above the CL detent.
At least one engine is in FLX TO mode, with the alpha-floor protection not active.
The alpha-floor protection is active independently of the thrust lever positions
The FAULT light of FAC 1 pushbutton is controlled by: (level 3)
FWC
FAC1
FMGC
The A/THR engaged and not active, on the FCU, the A/THR pushbutton light is on and: (level 3)
The A/THR system controls the engines; the FMA displays the A/THR engagement status (in green) and the A/THR mode.
The thrust levers controls the engines, the FMA displays the A/THR engagement status (in cyan) and the manual thrust rating.
The A/THR system controls the engines; the FMA displays the A/THR engagement status (in white) and the A/THR mode.
When the A/THR functions is engaged, A/THR is not active if: (level 3)
at least, one thrust lever is between the CL detent (included) and 0 stop (included) and at the most, one thrust lever is between the FLX/MCT detent and the CL detent.
At least one thrust lever is above the FLX/MCT detent, or both thrust levers are above the CL detent, or at least one engine is in FLX TO mode, with the alpha-floor protection not active.
the alpha-floor protection is active independently of the thrust lever positions.
In case of the alpha floor protection is active, the AUTOTHRUST is: (level 3)
Engage and not active.
Active independently of the thrust lever positions.
Active depends on the position of the thrust levers.
Thrust mode is: (level 3)
when the AP controls the aircraft speed with the elevators, the A/THR has to control the engines by a fixed thrust demand.
When the AP controls another aircraft parameter (e. g. altitude), the A/THR has to take care of the aircraft speed by a variable thrust demand to the engines.
only available in automatic landing when engine thrust has to be reduced to idle
Which statement is incorrect? (level 3)
Thrust mode: when the AP controls the aircraft speed with the elevators, the A/THR has to control the engines by a fixed thrust demand.
SPEED/MACH mode: when the AP controls another aircraft parameter (e. g. altitude), the A/THR has to take care of the aircraft speed by a variable thrust demand to the engines.
RETARD mode: only available in automatic landing or go-around when engine thrust has to be reduced to idle for the flare phase below 40 feet RA.
The 1FD2 indication is displayed on each flight mode annunciator (FMA) to show that: (level 3)
FD1 is engaged on CAPT side and FD2 is engaged on F/O side.
FD1 is engage on CAT and F/O side.
FD1 is engage on CAT and F/O side.
Both APS can be engaged as soon as the approach mode is selected on the flight control unit (FCU) (level 3)
AP1 has priority, AP2 is in standby
AP2 has priority, AP1 is in standby
First AP engaged has priority.
The A/THR function is, in fact, composed of two systems (A/THR1 and A/THR2), which are ready to be engaged at the same time, but only one system is selected. (level 3)
The selection of A/THR1 or A/THR2 depends on the engagement of the AP and FD.
A/THR1 is active and A/THR2 standby.
A/THR1 control Engine 1, A/THR 2 control Engine
Which ATHR control the engine in case of AP 2 active and both FD active (level 3)
ATHR 1
ATHR 2
Both ATHRs
When both APs are engaged. Which FMGC supplies (Flight management and guidance computers) both FMA (Flight Mode Annunciation)? (level 3)
FMGC 1 supplies both FMA,
FMGC 1 supplies FMA 1 and FMGC 2 supplies FMA 2,
FMGC 2 supplies both FMA if AP 2 was engaged first.
With AP2 is engaged, the FMA (Flight Mode Annunciation) will be supplied following: (level 3)
Both FMAs supplied by FMGC1,
Both FMAs supplied by FMGC2,
FMA1 supplied by FMGC1 and FMA2 supplied by FMGC2.
With at least one AP (Auto pilot) engaged. Which FMGC (Flight management and guidance computers) supplies both FMA (Flight Mode Annunciation)? (level 3)
The master FMGC,
The FMGC1,
The FMGC2,
Which window on the FCU (Flight Control Unit) always displays a target value selected by the crew? (level 3)
The ALT window,
The SPEED/MACH window,
The HDG/TRK window.
In flight AP can be engaged when: (level 3)
Aircraft in take off phase
Aircraft in climb phase
At least 5 seconds after lift-off
Where does the Navigation Data Base store? (level 3)
FM part of FMGC
FG part of FMGC
MCDU only
The position of the aircraft, used in flight plan, is computed by: (level 3)
FG part of the FMGC
The MCDU
FM part of the FMGC
What happens if we press instinctive disconnect P/B for more than 15sec? (level 3 )
A/THR will be inhibited recovery engagement in whatever reason.
A/THR will be inhibited recovery engagement for that flight whatever reason.
A/THR will be disconnected and can be re-engaged whenever.
The fuel and time prediction functions are performed by: (level 3)
FG part of the FMGCs
FM part of the FMGCs
The FAC
To perform the AUTOTHRUST (A/THR) function, the thrust limit computed by the: (level 3) (Not clear)
FMGCs which depends on the AP/FD mode.
FADECs, which depends on the position of the thrust levers.
FACs, which depends on the aircraft speed.
In the manual mode, the AP is not engaged and the ELAC (Elevator Aileron Computer) sends to the FAC (Flight Augmentation Computers): (level 3) (Not Clear)
The turn coordination and the dutch roll damping,
The engine failure compensation yaw orders,
The turn coordination, the dutch roll damping and the engine failure compensation yaw orders.
What is different between control loop of AP and ATHR (level 3) (Not Clear)
ATHR control single loop, AP double loop
AP and ATHR control double loop
AP control single loop, ATHR double loop
