Flight Controls Flashcards by Laura Hofherr

The primary flight control system consists of:

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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The secondary flight control system consists of:

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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What is the only primary flight control that is not FBW (Fly-By-Wire)? •

What is the only primary flight control that is not FBW (Fly-By-Wire)? •
Ailerons

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Pitch trim limits

+2
-13

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What controls PITCH?

PITCH CONTROL
Elevator
Horizontal Stabilizer

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What is the difference between normal mode and direct mode?

What is the difference between normal mode and direct mode?
There are no higher level functions available in direct mode

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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

FCM (Flight Control Module) – a computer inputting higher level functions

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What are the higher level functions associated with pitch?

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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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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Higher level function for the horizontal stabilizer is to:

Keep the airplane trimmed via the autopilot and deployment of the speed brakes

Prevent structural damage at high speeds

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What is the priority for the trim system?

What is the priority for the trim system?
Back-up
Captain
First Officer
Autopilot

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How is roll controlled?

How is roll controlled?
Ailerons and multi-function spoilers (outer 3 spoilers on each wing)

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Ailerons

Ailerons
Mechanically controlled (no Fly-By-Wire)
Hydraulically actuated

PCU (Power Control Unit) – a hydraulic actuator controlled by conventional cables

THERE ARE NO HIGH LEVEL FUNCTIONS ASSOCIATED WITH THE AILERONS

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How many panels are on each wing? What are their functions?

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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When will the speed brakes automatically close even if the lever shows deployed?

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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What is the flap/slat extension/retraction sequence?

What is the flap/slat extension/retraction sequence?
Slats extend first
Flaps retract first

Will loss of airspeed data cause the flight controls to go into ‘DIRECT’ mode?

Will loss of airspeed data cause the flight controls to go into ‘DIRECT’ mode?
Yes

How are the flight controls trimmed?

How are the flight controls trimmed?
Roll & Yaw Ailerons and Rudder surface repositioned to a new ‘neutral position
Pitch Horizontal Stabilizer

Will the multi-function spoilers function in ‘DIRECT’ mode?

Will the multi-function spoilers function in ‘DIRECT’ mode?
Yes, for roll only and at a default fixed gain (Airspeed and Flap setting)

Will the speed brakes / ground spoilers function in ‘DIRECT’ mode?

Will the speed brakes / ground spoilers function in ‘DIRECT’ mode?
No

What happens to the flight control system when the RAT is the only AC power source?

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

Slat / flap position is limited to ‘3’ to allow adequate airspeed for the RAT

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.

Manual pilot trim commands are limited to ____

Manual pilot trim commands are limited to ____
3 s

Fly-by-wire is an electronic system designed to operate the
flight controls replacing the _____ of a conventional airplane.

control cables

The EMBRAER FBW system is composed of a set of ___ Actuator Control Electronics (ACEs) and ___ Flight Control Modules (FCMs):

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

Speed Brakes

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° Speed brakes will not work in Direct Mode

Ground Spoilers

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* Ground spoilers will not work in Direct Mode

YAW CONTROL Rudder

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

Higher level functions for yaw are:

Higher level functions for yaw are: Yaw damp Turn coordination Gain on airspeed – as airspeed increases, rudder deflection decreases

What happens to artificial feel if flight controls are disconnected?

What happens to artificial feel if flight controls are disconnected? Artificial feel is felt at 1⁄2 the normal load

Slats/Flaps

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

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.

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

Hydraulic Power Up Built in Test takes

1 minute to complete and will be interrupted if any flight control surface is moved while the test is in progress

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

3 min

Hydraulic Power Up Built in Test takes

1 minute to complete and will be interrupted if any flight control surface is moved while the test is in progress

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