Detection devices fitted at both fittings which signal the Flight Control Computers of failure are NOT :

Secondary Middle Load Path Detection Device (SMLPDD)

About the Electrical Back up :

2 rate gyro units and 2 accelerometer per BCM

Which answer is TRUE concerning Back Up Control Module (BCM) supplying ?

THS Actuator through the blue supplied hydraulic motor

Functions of the FCGUs ?

Calculate the different flight control laws, Command/Monitoring function

Concerning EBHA, what is WRONG :

EBHA accumulator pressure is released when it's not energized

Concerning the Position Transducer Unit (PTU) :

Sensor at RH pedals transmits to the PRIM 1, 2 and 3

Concerning the Rudder, In case of loss of 1 Hydraulic circuit, what is WRONG :

One EBHA changes to Hydraulic mode, and the other stays in Damping Mode

The Torque shaft transmission system of the Flaps is used for :

Direction changed by 90° to drive the Ball Screw Actuators (BSAs)

In Normal conditions, concerning the ailerons :

Conventional hydraulic servo actuator (S/C)

The Trimmable Horizontal Stabilizer Actuator (THSA) is powered by 1 of 3 motors that individually are powered by :

Blue and Yellow, and electronically in case of loss of Hydraulic System

When Back Up Power Supply (BPS) are inhibited :

Electro valve is supplied with the power Inhibition signals from PRIM 2/3

Concerning the FCCs, The computation function does NOT :

Computes of the control surfaces position

The Pedal Feel and Trim Unit (PFTU) has :

3 Rotary Variable Differential Transducers (RVDT)

In Damping Mode, what is WRONG :

Electro Hydraulic Servo Valve (EHSV) will provide a supply and return path

Flap Load Relief Function :

When the VFE is no longer exceeded, the flaps automatically extend again

The stabilizer of the THS is attached by :

2 attachment at the rear, 1 further to the THA screwjack near the fwrd edge

What is NOT true about the Pedal Damping and Friction Unit :

Gives mechanical input from the surface and cnvert into electrical signal

In extreme conditions, flights laws NOT provide protections in order to :

Flight envelope and Maneuver Load Alleviation

Objectives of the Electrical back up ; What is WRONG ?

Standby when all PRIM SEC loss but Electrical generation still supplies

The Flight Back up Control System is composed of :

4 Back up Power supply and 1 back up control Module

Auxiliary Functions of the PRIM :

Spd brake, grnd spoiler, maneuver load allviatin, direct lift, Beta target

Flight Controls Law Priority

Normal, Alternate, Direct, Abnormal

THS : In hydraulic failure :

Electrical Motor Control Unit (EMCU) convert 115VAC to 270VDC

The yellow hydraulic system supplies :

Spoiler 4, 5 LH and Spoiler 1, 2, 4 RH

What is false concerning Normal flight enveloppe ?

Ensure engine asymmetry conditions

Concerning servo controls of the spoilers :

The servo controls of spoilers 3, 4 and 5 are the same

What is NOT a function of the FCDC ?

Compensation of A/C configuration, speed changes, airbrakes movements

About Alternate law :

Same control as the normal law but some FE protections are not available

Concerning the Flight Control Guidance Units (FCGU) :

The two FCGU installed inside each PRIM/SEC are necessary

The Electrical Flight control system computation block is composed of :

Hardware, Sofware and Feedback sensors

Calculate the flight control laws and related functions in normal condition

The Spoiler Servo control actuator has different operating mode :

Hydraulic, Retracted failure, blocking, and maintenance

Which sentence is FALSE ?

The roll orders have NOT priority on the speed brake function

studbud

ATA 27

50 termsStudBud Administration19 plays

Imported from external platform

Flashcards50 cardsFPractice quizPHost liveL

Questions 50

Answers

1
How many position for the flaps ?
5
Imagines tu te trompes
6
2
Detection devices fitted at both fittings which signal the Flight Control Computers of failure are NOT :
Secondary Lower Load Path Detection Device (SLLPDD)
Secondary Upper Load Path Detection Device (SULPDD)
Secondary Middle Load Path Detection Device (SMLPDD)
3
Master computer priority ?
PRIM 1, PRIM 3, SEC, PRIM 2
PRIM 1, PRIM 2, PRIM SEC, PRIM 3
PRIM 1, PRIM 3, PRIM 2, SEC
4
About the Electrical Back up :
1 rate gyro unit and 1 accelerometer
2 rate gyro units and 2 accelerometer per BCM
2 rate gyro, 2 accelerometer in the radome
5
Which answer is TRUE concerning Back Up Control Module (BCM) supplying ?
Left Elevator through servo control supplied by the yellow hydraulic system
THS Actuator through the blue supplied hydraulic motor
Left Aileron through the servocontrol supplied by the blue hydraulic system
6
Functions of the FCGUs ?
Monitor only the information sent by the PRIM
Calculate the different flight control laws, Command/Monitoring function
Command the flight control only
7
Concerning EBHA, what is WRONG :
Maintenance mode is NOT POSSIBLE when Hyd. power sup. is still available
EBHA of spoiler 1 can stay hot for long time after activation
EBHA accumulator pressure is released when it's not energized
8
What are the components of the Electrical Flight Control ?
PRIM, FCDC, BCM
PRIM, FCCs, BCM
PRIM, FCGU, BCM
9
Concerning the Position Transducer Unit (PTU) :
Sensor at RH pedals transmits to the PRIM 1, 2 and 3
Sensor at RH pedals transmits to the PRIM 1, 2 and 3 and SEC
Sensor at LH pedals transmits to the PRIM 1 2 and 3
10
Concerning the Rudder, In case of loss of 1 Hydraulic circuit, what is WRONG :
Failure leads to the loss of hydraulic mode on one EBHA
One EBHA changes to Hydraulic mode, and the other stays in Damping Mode
The failed EBHA changes to Damping Mode
11
The Torque shaft transmission system of the Flaps is used for :
Speed increase
Direction changed by 45° to the BSAs and speed reduction
Direction changed by 90° to drive the Ball Screw Actuators (BSAs)
12
In Normal conditions, concerning the ailerons :
Electrical Back-up Hydraulic Actuators (EBHA)
Conventional hydraulic servo actuator (S/C)
Electro Hydrostatic Actuator (EHA)
13
Spoilers 1 are actuated by :
EBHA and Conventional Servo
EBHA
EHA only
14
The Trimmable Horizontal Stabilizer Actuator (THSA) is powered by 1 of 3 motors that individually are powered by :
Blue Hydraulic and Electrical way at the same time and yellow for back up
Blue Hydraulic and Yellow Hydraulic, and electrically to be faster
Blue and Yellow, and electronically in case of loss of Hydraulic System
15
When Back Up Power Supply (BPS) are inhibited :
Hydraulic flow to the Back-up Power Supply is reduced
Electro valve is supplied with the power Inhibition signals from PRIM 2/3
Internal hydraulic flow of 1 BPS is higher than 0.7 liters/min
16
Concerning the FCCs, The computation function does NOT :
Computes of the control surfaces position
Computes the Autopilot (AP) orders through the automatic flight function
Computes the manual flight-control laws
17
The Pedal Feel and Trim Unit (PFTU) has :
2 Rotary Variable Differential Transducers (RVDT)
1 Rotary Variable Differential Transducers (RVDT)
3 Rotary Variable Differential Transducers (RVDT)
18
FCGUs communicate with each other in :
Direct links
Digital links
ARINC 429 links
19
The Rotary Variable Differential Transducers (RVDT) give information to :
PRIM 2, 3, SEC and BCM
PRIM 2, SEC and BCM
PRIM 1 and 3 and BCM
20
Wing tip Brake is NOT for :
Flaps symmetry
Overspeed
Runaway
21
In Damping Mode, what is WRONG :
EHA is in active mode and moves the surface
Accumulator adjusts the variation of the fluid volume in the actuator
Electro Hydraulic Servo Valve (EHSV) will provide a supply and return path
22
EHA in Servocontrol failure are in :
Hydraulic mode
Damping mode
Active mode
23
Flap Load Relief Function :
When the VFE is no longer exceeded, the flaps automatically extend again
Flaps manually retract to the next retracted flaps configuration
limits loads on the flaps if min. speed with flaps extended is exceeded.
24
The stabilizer of the THS is attached by :
3 attachment at the rear, 1 further to the THA screwjack
2 attachment forward, 2 further to the THA screwjack near the fwrd edge
2 attachment at the rear, 1 further to the THA screwjack near the fwrd edge
25
What is NOT true about the Pedal Damping and Friction Unit :
Gives friction torque to prevent unwanted pedal movements
Gives a resistive torque related to the pedal input speed
Gives mechanical input from the surface and cnvert into electrical signal
26
In extreme conditions, flights laws NOT provide protections in order to :
Reach the boundaries of the flight envelope
Reduce the risk of over-stressing
Flight envelope and Maneuver Load Alleviation
27
Objectives of the Electrical back up ; What is WRONG ?
Activated when electrical generation or distribution is totally lost
Standby when all PRIM SEC loss but Electrical generation still supplies
Activated when all PRIM and SEC are lost
28
The Flight Back up Control System is composed of :
1 Back up power supply and 1 back up control module
1 Back up power supply and 4 back up control module
4 Back up Power supply and 1 back up control Module
29
Auxiliary Functions of the PRIM :
Spd brake, Grnd Spoiler, Direct lift, Dmping elevation, ah frère, eject
Spd brake, Grnd Spoiler, Direct lift, Dmping elevation, beta target, eject
Spd brake, grnd spoiler, maneuver load allviatin, direct lift, Beta target
30
Power control unit of the flaps are driven by :
Blue Left side and Yellow Right side with no back up
Both Blue and Yellow only for normal operation
1 Blue and 1 yellow
31
Which one is FALSE ?
The System torque limiter is unlocked as soon as the overload disappears
Kink Gearbox Shaft angle: 10°
High Lift Control Computer (HLCC) comds the closure of the Power off brakes
32
Flight Controls Law Priority
Normal, Not-Normal, emergency, direct
Normal, Alternate, Direct, Abnormal
Normal, emergency, direct, abnormal
33
THS : In hydraulic failure :
Power motor supply Unit (PMSU) convert 115VAC to 270VDC
Electrical Motor Control Unit (EMCU) convert 115VAC to 28VDC to
Electrical Motor Control Unit (EMCU) convert 115VAC to 270VDC
34
The yellow hydraulic system supplies :
Spoiler 4, 5 LH and Spoiler 1, 2, 4 RH
Spoiler 1, 2, 5 LH and Spoiler 3, 4 RH
Spoiler 1, 2, 3 LH and Spoiler 3, 5 RH
35
What is false concerning Normal flight enveloppe ?
Assistance to Handling
Ensure engine asymmetry conditions
Stability and manoeuvrability
36
Concerning the FCCs locations :
PRIM 3 and SEC 2 in 1300VU
FCDC 1 and 2 in CPIOM C
PRIM 1 2 3 in 1000VU
37
Concerning servo controls of the spoilers :
The servo controls of spoilers 1, 2 and 3 are the same
The servo controls of spoilers 3, 4 and 5 are the same
The servo controls of spoilers 1 and 5 are the same
38
What is NOT a function of the FCDC ?
Concentration of the data sent by the FCCs, the FCU, and the BCM
Compensation of A/C configuration, speed changes, airbrakes movements
Flight control warning through the Flight Warning System (FWS)
39
About Alternate law :
Used when the aircraft attitude is out of the flight envelope limit
flight envelope protection is not available
Same control as the normal law but some FE protections are not available
40
Concerning the Flight Control Guidance Units (FCGU) :
The two FCGU installed inside each PRIM/SEC are necessary
Both for Controling and Monitoring
The first is for Control and monitoring and the second is for backup
41
The Electrical Flight control system computation block is composed of :
Hardware, Active sensors and BCM
Hardware, Sofware and Feedback sensors
Hardware, Sensors, feedback software
42
PRIM and SEC :
Host the C-PIOM C applications
Calculate the flight control laws and related functions in normal condition
Calculate the flight control laws and related functions in emergency
43
The conventional Servocontrol (S/C) at both the Ailerons and Elevators has two operating modes :
Active and Standby
Hydraulic and Damping
Active and Damping
44
How many screw jacks for the Flaps :
6 (3 per wing 2 active and 1 backup)
2 per flaps
8 (4 active, 4 in back up)
45
How many FCGU ?
10
2 per computer
2 for PRIM 1 2 3 only
46
How many FCDC ?
2
1 per PRIM
1 per CPIOM B
47
The Spoiler Servo control actuator has different operating mode :
Hydraulic, Retracted failure, blocking, and maintenance
Hydraulic, Damping, Back up, speed break
Hydraulic, Damping, retracted failure, blocking and maintenance
48
Which sentence is FALSE ?
The roll orders have NOT priority on the speed brake function
The Maneuver Load Alleviation function has priority over speed brake fnctin
The direct lift function facilitates relative position control
49
How many Primary computers for flight controls ?
PRIM 1 2 3 4
PRIM 1 2 3 and SEC
PRIM 1 2 4 and SEC
50
T.O Config is
Level 2 alert
Level 3 alert
MEMO

ATA 27 Flashcards | StudBud