Flight Controls Flashcards
The primary flight control system consists of:
A
The primary flight control system consists of:
(1) Ailerons and the multi function roll spoilers for roll axis control.
(2) Elevators for pitch axis control.
(3) Rudder for yaw axis control.
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2
Q
The secondary flight control system consists of:
A
The secondary flight control system consists of:
(1) Horizontal stabilizer.
(2) Flaps and Slats.
(3) The Multi-function spoiler (when used as speed brakes or
ground spoilers).
(4) Dedicated ground spoilers.
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3
Q
What is the only primary flight control that is not FBW (Fly-By-Wire)? *
A
What is the only primary flight control that is not FBW (Fly-By-Wire)? *
Ailerons
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4
Q
Pitch trim limits
A
-2
+13
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5
Q
What controls PITCH?
A
PITCH CONTROL
Elevator
Horizontal Stabilizer
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6
Q
What is the difference between normal mode and direct mode?
A
What is the difference between normal mode and direct mode?
There are no higher level functions available in direct mode
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7
Q
Elevator
A
Elevator
Electrically controlled
Hydraulically actuated
PCU (Power Control Unit) – a hydraulic actuator (replaces conventional control cables)
ACE (Actuator Control Electronic) – the electronic unit controlling the PCU
8
Q
What are the higher level functions associated with pitch?
A
What are the higher level functions associated with pitch?
1. Gain on airspeed (as airspeed increases, pitch deflection decreases)
2. Elevator thrust compensation (pitch control is maintained during thrust changes)
3. AOA limiting
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9
Q
Horizontal Stabilizer
A
Horizontal Stabilizer
Electrically controlled
Electrically actuated
HSA (Horizontal Stabilizer Actuator) – the electric motor that moves the horizontal stabilizer
ACE (Actuator Control Electronic) – the electronic unit controlling the HSA
FCM (Flight Control Module) – a computer interface for higher level functions
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10
Q
Higher level function for the horizontal stabilizer is to:
A
Higher level function for the horizontal stabilizer is to:
Keep the airplane trimmed via the autopilot and deployment of the speed brakes
11
Q
What is the priority for the trim system?
A
What is the priority for the trim system?
Back-up
Captain
First Officer
Autopilot
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12
Q
How is roll controlled?
A
How is roll controlled?
Ailerons and multi-function spoilers (outer 3 spoilers on each wing)
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13
Q
Ailerons
A
Ailerons
Mechanically controlled (no Fly-By-Wire)
Hydraulically actuated
PCU (Power Control Unit) – a hydraulic actuator controlled by conventional cables
14
Q
How many panels are on each wing? What are their functions?
A
How many panels are on each wing? What are their functions?
5 panels
3 outboard multi-function spoilers are used to assist
Roll control
Speed brakes open up to 30*
Ground spoilers 3,4,5 40*
2 inboard spoilers are only used as Ground spoilers 1,2 open up to 60*
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15
Q
When will the speed brakes automatically close even if the lever shows deployed?
A
When will the speed brakes automatically close even if the lever shows deployed?
Slat/Flaps selected to 2 or greater
Airspeed below < 180 kts.
TLA greater > 70°
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16
Q
What is the flap/slat extension/retraction sequence?
A
What is the flap/slat extension/retraction sequence?
Slats extend first
Flaps retract first
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17
Q
Will loss of airspeed data cause the flight controls to go into ‘DIRECT’ mode?
A
Will loss of airspeed data cause the flight controls to go into ‘DIRECT’ mode?
Yes
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18
Q
How are the flight controls trimmed?
A
How are the flight controls trimmed?
Roll & Yaw Ailerons and Rudder surface repositioned to a new ‘neutral position
Pitch Horizontal Stabilizer
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19
Q
Will the multi-function spoilers function in ‘DIRECT’ mode?
A
Will the multi-function spoilers function in ‘DIRECT’ mode?
Yes, for roll only and at a default fixed gain (Airspeed and Flap setting)
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20
Q
Will the speed brakes / ground spoilers function in ‘DIRECT’ mode?
A
Will the speed brakes / ground spoilers function in ‘DIRECT’ mode?
No
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21
Q
What happens to the flight control system when the RAT is the only AC power source?
A
What happens to the flight control system when the RAT is the only AC power source?
Horizontal stab trim operates at LO SPEED
Slat / flap system operates at LO SPEED
22
Q
Hydraulic actuators control the respective flight control
surfaces. These are referred to as _____
Power Control Units (PCUs).
_______are controlled electronically using Fly-by-Wire (FBW)
technology.
Elevators, rudders, roll spoilers as well as all secondary flight
control systems, including the horizontal stabilizer, flaps and slats,
ground spoilers and speed
brakes,
The Ailerons not fly by wire are commanded by conventional
control cables that run from each control wheel back to a
pair of hydro-mechanical actuators.
A
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23
Q
Manual pilot trim commands are limited to ____
A
Manual pilot trim commands are limited to ____
3 s
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24
Q
Fly-by-wire is an electronic system designed to operate the
flight controls replacing the _____ of a conventional airplane.
A
Fly-by-wire is an electronic system designed to operate the
flight controls replacing the _____ of a conventional airplane.
25
Q
The EMBRAER FBW system is composed of a set of ___
Actuator Control Electronics (ACEs) and ___ Flight Control
Modules (FCMs):
A
The EMBRAER FBW system is composed of a set of ___
Actuator Control Electronics (ACEs) and ___ Flight Control
Modules (FCMs):
9 ACE
Three Primary-ACEs (P-ACE). active/Stby
Two Slat/Flap ACEs (SF-ACE). active/active
One Horizontal Stabilizer ACE (HS-ACE).
Three Spoiler ACEs (S-ACE).
4 FCM
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26
Q
Speed Brakes
A
Speed Brakes
3 outer panels (Multifunctionspoilers 3,4,5)
When handle is in the open position the speed brakes will auto close if:
Slat/flap selection is 2 or greater
Airspeed < 180 kts.
TLA (Thrust Lever Angle) > 70°
27
Q
Ground Spoilers
A
Ground Spoilers
All panels 1,2,3,4,5
1,2 60* 3,4,5 40*
Operational on ground only
Deploy via:
Weight-On-Wheels (WOW)
Wheel speed above 45kts air airspeed above 60kts
Thrust Lever Angle (TLA) below 26*
Retract via rollout:
Wheel speed auto retract below 45kts or at least 5 sec
Thrust Lever Angle (TLA) below 26*
Retract via GoAround:
Thrust Level Angle greater than 35*
28
Q
YAW CONTROL Rudder
A
Electrically controlled
Hydraulically actuated
PCU (Power Control Unit) – a hydraulic actuator (replaces conventional control cables)
ACE (Actuator Control Electronic) – the electronic unit controlling the PCU
FCM (Flight Control Module) – a computer interface for higher level functions
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29
Q
Higher level functions for yaw are:
A
Higher level functions for yaw are:
Yaw damp
Turn coordination
Gain on airspeed – as airspeed increases, rudder deflection decreases
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30
Q
What happens to artificial feel if flight controls are disconnected?
A
What happens to artificial feel if flight controls are disconnected? Artificial feel is felt at 1⁄2 the normal load
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31
Q
Slats/Flaps
A
Slats/Flaps
Electrically controlled
Electrically activated
PDU (Power Driver Unit) – the electric actuators that moves the flaps/slats on their track
ACE (Actuator Control Electronic) – the electronic unit controlling the PCU
8 leading-edge slats (4 per wing)
3 positions (0, 15 and 25*)
4 double-slotted/fowler-type flaps (2 per wing)
7 positions 0,1,2,3,4,5,Full
The rule to remember…slats extend first and flaps retract first
A skew sensor protects the flaps from an asymmetric condition
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32
Q
The Controller Area Network BUS (CAN BUS) is the communication link between the FCMs and the P-ACE units while the Avionics Standard Communication Bus (ASCB) provides data exchange between all FCMs, and with other components of the avionic system.
A
,
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33
Q
The Power Up Built in Test (PBIT) reduces the flight control system exposition to latent faults, ensuring that the system components remain capable of executing their functions
A
.
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34
Q
Hydraulic Power Up Built in Test takes
A
1 minute to complete and will be interrupted if any flight
control surface is moved while the test is in progress
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35
Q
The Electrical PBIT is automatically performed during power up after the airplane is powered by any AC source and takes approximately ____ to complete. The Electrical PBIT will be interrupted if any electric hydraulic pump is turned ON
A
3 min
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36
Q
Hydraulic Power Up Built in Test takes
A
1 minute to complete and will be interrupted if any flight control surface is moved while the test is in progress
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37
Q
FLIGHT CONTROLS
Lever position Slat position Flap position Detent/Gated
0 0° 0° Detent/Stop
1 15° 5° Detent
2 15° 10° Detent
Lever position Slat position Flap position Detent/Gated
3 15° 20° Detent
4 25° 20° Gated/Stop
5 25° 20° Detent
Full 25° 35° Detent/Sto
A
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