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EGK Systems > Primary Controls > Flashcards

Primary Controls Flashcards

1
Q

Advantages of fly by wire

A

Lighter than conventional control systems
Reduces pilot workload
Offers advanced envelope protection
Even out control inputs in turbulence

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2
Q

Fly By Wire

A

Controls inputs from pilots controls and translated to digital signals fed to series of computer that compare and make decision

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3
Q

Safety Measures in FBW

A

Multiple Computers
Difference hardware
Different software
Different sensors

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4
Q

Airbus FBW

A

X 3 Primary x2 secondary

Normal law - AOA protection etc
Alternate Law - x2 failures basic control law
Direct Law - Complete computer failure direct with controls
Mechanical Law - Control pitch/trim/rudder

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5
Q

Boeing FBW

A

X 3 primary computers
Normal - full function
Secondary - loss of flight envelope protection
Direct - direct from pilots controls

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6
Q

Rudder ratio changer

A

Protect fin from excessive rudder loads from pilot
Limited at higher speeds

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7
Q

Trim Runaway Protection

A

Double pole trim both need to be pressed together to operate trim jack motor

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8
Q

Q Feel System

A

Receives dynamic pressure info from pitot static system and used to control hydraulic load jack inside Q feel unit

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9
Q

Spring Feel System on fully powered flight controls

A

Connected to the control column
When deflected one way opposite spring stretches with opposing force

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10
Q

Electro-Hydraulic systems

A

Electro-Hydraulic Actuator (EHA) - Hydraulic pump driven by high power stepper motor. Pump electrically signalled to control operation. NO HYDRAULIC LINES

Electro-Mechanical Actuator (EMA) - entirely driven by electric motors - restricted to secondary flight controls

EBHA - Basically EHA with a back up EHA

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11
Q

Manual Control

A

Used on light ac
Stainless steel cables run from each control via pulley wheels
Turnbuckles for tension

Reversible system

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12
Q

Non reversible system

A

Movement of control surface cannot move control column

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13
Q

Primary Controls

A

Elevator
Ailerons
Rudder
Roll Spoilers

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14
Q

Partially Powered Controls

A

Hydraulic actuator attached in parallel to direct link between pilots control and control surface.

Actuator controlled by hydraulic servo linked to control system.

Reversible connection

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15
Q

Fully Powered Controls

A

Removes direct link between control and control surface - relies on hydraulic actuator

PFCU - Power flying control unit

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16
Q

Reasons for trim

A

Changes in CG, Changes in speed and Changes of power

17
Q

Blow Back System

A

Blow back valve relieve excessive loads before load causes damage to controls

Rudder applied force changes with speed

18
Q

Advantages of a variable incidence tailplane

A

Large horizontal stabiliser through very small angle to reduce drag
Elevator retains its full range of motion

Less drag in trimmed state
Trimming does not reduce range of pitch control

19
Q

Fairing Role

A

Cover aileron actuator

20
Q

Disadvantages of FBW

A

Sensor failure causing wrongly triggered interference of valid pilot inputs

21
Q

Disadvantage of side stick controls

A

Make it difficult for one pilot to see and understand what other is doing. Inputs are averaged

22
Q

Gust LOCK

A

Device that limits the movement of control surface when parked

23
Q

Reasons for being trimmed in pitch

A

Varying CG position
Changes of speed
Changes of power

24
Q

Primary stop controls

A

Set the range of movement of the control surface

25
Q

Flutter is and preventions

A

Flutter of control surface is divergent oscillatory motion of control surfaces caused by natural frequency interaction of forces and stiffness of structure.

Flutter occurs when external forces is applied to the ac with periodic frequency that is equal to the natural structural frequency of that ac

Flutter can be avoided by remaining in flight envelope and speed limitation in turbulent conditions

26
Q

Zero force position changes on

A

Ailerons trim
Rudder trim

27
Q

Zero position force does not change on

A

PET:

Pitch controls
Elevator
Trim

28
Q

3 ways to limit rudder deflection

A

Rudder ratio changer - limits deflection at high speeds

Variable stops - rudder peals and rudder physically reduced

Block back - applies constant movement force to rudder dictated by pedal deflection deflecting rudder depending on speed of the airflow

29
Q

THS is usually controlled by

A

Hydraulically actuated jack

30
Q

Fairings cover

A

Aileron actuators and flap tracks

31
Q

How is redundancy achieved on fully powered primary flight controls

A

Duplex parallel control runs per control axis linked to control surfaces actuator which supply hydraulic systems

32
Q

If failure of wiring on fly by wire ac what happens

A

Use a different actuator with a different computer

33
Q

Rudder trim does what

A

Moves the rudder and the rudder pedals in the corresponding direction

34
Q

Aileron trim system does what

A

Control wheel turns in the direction of trim

35
Q

Elevator trim does what

A

Control column does not move - zero force position does not change

36
Q

Direct Law

A

Pilot controls are not augmented by internal computers
Exact control sent direct to hydraulic servo valves
Autopilot lost
Aural and visual warning will remain for over speed/stall

37
Q

Trimming of aileron and rudder in an irreversible control system

A

Achieved by adjusting the zero force point of the feel system

38
Q

Route of operation of fly by wire

A

Pilot operates control —— primary flight computer convert to electrical output —— actuator control electronics covert electrical signal to analogue signals —- sent to power control unit —— hydraulic actuator moves flight control surface

EGK Systems (15 decks)

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