PRELIM Flashcards
It refers to a system that can significantly reduce workload during phases of flight. It also refers to a collection of systems that automate a plane’s operations.
AUTOPILOT
It tells your plane how to fly, including navigation, altitude, speed, and engine thrust, which controls the force by which the plane moves through the air.
Complex Computer Matrix
It describes a complete flight from departure to arrival.
Flight Plan
interface between the pilot and the FMS
Multipurpose Control and Display Unit (MCDU)
In cases of an autopilot, the FAA mandates that pilots be “________” for takeoffs and landings.
hands-on
on-board multi-purpose navigation, performance, and aircraft operations computer
Flight Management System (FMS)
capability to fly any desired flight path defined by waypoints
Area Navigation (RNAV)
Important component on the first aircraft autopilot
gyroscopic heading indicator & attitude indicator
Name of the Wright Brothers?
Wilbur & Orville Wright
Where was the first test flights of the Wright Brothers?
Kitty Hawk, North Carolina
Who and when was the credibility of autopilot demonstrated?
Lawrence Sperry, 1914
When was the first two gliders of the Wright Brothers flown?
1900 and 1901
Why did the first two gliders of the Wright Brothers fail?
there’s not enough lift and not fully controllable
The first aircraft autopilot was developed by _______ on _____.
Sperry Corporation, 1912
Who helped the brothers build a gasoline engine (that is light enough to propel an airplane and difficult controls)
Charlie Taylor
made it possible to fly during night and bad weather
a
Radio Navigation Aids
Other further developments of the autopilot include __________ and ________.
improved control algorithms, hydraulic servomechanism
gives inertial rotation data of an aircraft
laser gyro
When at rest, in a laser gyro, the two beams get to the sensor with the _________.
same frequency
What creates a difference of frequency between two beams?
aircraft rotation
After computation of the frequency difference, this output will provide _________ of the aircraft.
rotation information
It is measured by optical providing an analog output, which is sent to the analog to digital converter.
frequency difference
LASER is usually found in the ____________ along with CG of the aircraft.
center cabin floor panel
Give at least three disadvantages of auto pilot
-Automation – induced failures
-False alarms
-Boredom
-Over-reliance, complacency; willing to accept results without scrutinizing them first
-Reduced alertness of operator, by offering a false sense of security
Advantages of auto pilot
-Reduces manual workload and fatigue
-Relief from small errors
-Precision in the handling of routine tasks
-Increased productivity
If Laser Gyro fails, use the backup attitude gyro located on _____________.
cockpit instrument panel
If Laser Gyro fails, use the _______ located on cockpit instrument panel.
backup attitude gyro
wha is the pilot’s main role
maneuver the airplane from A to B safely and efficiently
Five sub-tasks of a pilot
-to operate, manage, and to monitor the engines and airplane control systems: Lights off Principle on Pushbutton Switches
-to avoid inadvertent encounters with either unfriendly terrain or with objects on the ground
-to navigate efficiently to the destination airport
-to ensure comfort to the passengers and crew by operating and monitoring such systems as pressurization and temperature control
-to communicate with company operations and with ATC
It contains the elements from which the flight plan is constructed.
Navigational Data Base (NDB)
contains all of the information required for building a flight plan
Navigational Data Base (NDB)
information required to build a flight plan
airways
airports
Standard Terminal Arrival (STAR)
consists of gyro, rate gyros, accelerometer, pitot-static system, and air temperature probes
detecting element
detect the movement of the aircraft about its three flight axes and the rate of that movement
detecting element
Pilots must understand the way databases are compiled and revised by the _______ and processed by the _________; updated every ___ days.
database provider, avionics mechanic, 28
considered to be internal controls or inner loop of the system
detecting element
brain of the system
computer amplifier
Basic AFCS consists of:
-sensing element
-command element
-output element
-computer/amplifier
considered to be external controls or the outer loop of the system
command element
consist of the pilot’s control panel and manually operated controls that include the pilot’s stick, rudder pedals, and navigation
command element
computes, amplifies, and processes the signal from the detecting and command element
computer amplifier
directs the output element to respond to the pilot’s and or system requirements
computer amplifier
consists of units, which move the control surfaces of the aircraft in response to the computer demands
output elements
Autopilot modes are capable of maintaining set of operating parameters using Flight Control Unit (FCU) which can include:
attitude hold
heading hold
vertical speed hold
altitude hold
Consists of the detection, amplification, correction, follow up, and the aircraft response loop
Basic AFCS Loop
It refers to a system of automatic controls which holds the aircraft on any selected magnetic heading and returns the aircraft to that heading when it is displaced from it.
Automatic Pilot
functions to cancel the input signal by applying an opposite signal proportional to the command required to bring the aircraft to the desired attitude
follow up signal
keeps the aircraft stabilized around its horizontal and lateral axes
Automatic Pilot
provide for one, two, or three stabilized planes.
Autopilot systems
Movement within each plane is _______, rather centered on axis.
about an axis
three principal axes
longitudinal, lateral, vertical
runs nose to tail through the CG
longitudinal axis
axis on the x-axis
longitudinal
runs perpendicular to the other two axes intersecting them at the CG
vertical axis
runs parallel with a line from wing tip to wing tip and intersects the x-axis at the CG
lateral axis
axis on the z-axis
vertical
axis on the y-axis
lateral
On ________, the power to move the control surfaces is provided by the muscles in the pilot’s arms and legs.
small light aircraft
The control column is physically connected to the control surfaces by ________.
cables
Wide bodied aircraft will corporate some form of _________ to move control surfaces.
power assistance
On __________, it is physically impossible to move the control surfaces by muscle alone.
larger aircraft
The __________ is provided by actuators or servo and these devices can operate from either mechanical input or electrical output.
power assistance
fifth element of many advanced autopilot systems
feedback or follow-up
When an aircraft fails to meet the conditions selected, an _____ is said to have occurred.
error
This refers to signals sent as corrections are being made by the output elements to advise the autopilot of the progress being made.
feedback or follow-up
This is the basis for autopilot system operation.
error correction
A _________ uses information about the rate of movement of the aircraft, and move control surfaces to counter the rate of change that causes the error.
rate-based autopilot
Two basic ways modern autopilot systems do for error correction
position-based autopilot, rate-based autopilot
manipulates the aircraft’s controls so that any deviation from the desired attitude of the aircraft is corrected.
position-based autopilot
is done by memorizing the desired aircraft attitude and moving the control surfaces so that the aircraft returns to that attitude.
position-based autopilot
What type of autopilot system do most large aircrafts use?
rate-based autopilot
Its basis is “Gyro, accelerometers, and others and other sensor equipment can detect the uncommand attitude changes far more accurately and then provide an electrical output to an actuator or servo.”
Fly-By-Wire Principle
When the pilot moves the control column or rudder pedals, an electrical signal from the stick or ________ is transmitted to an electrically operated actuator and the control surface is deflected by pilot’s input.
pedals transducer
When the pilot moves the control column or rudder pedals (a commanded attitude change), an electrical signal from the stick or pedals transducer is transmitted to an electrically operated actuator and the control surface is deflected by pilot’s input. In this electrically operated system, it is _________, not _________, which control the actuator or servo operation.
electrical signals, mechanical inputs
The _________ of the aircraft provide the flight control computer with inputs of heading, attitude, waypoints, etc.
avionics system
The avionics system of the aircraft provide the flight control computer with inputs of heading, attitude, waypoints, etc. and the flight control computer repositions the actuator with electrical signals to maintain the aircraft on the programmed flight path. What is this called?
autopilot
The ____________ repositions the actuator with electrical signals to maintain the aircraft on the programmed flight path.
flight control computer
Give at least one advantage of fly-by-wire principle
-improved reliability
-damage tolerance
-more effective control of a necessary highly maneuverable plane
Give at least one disadvantage of fly-by-wire principle
-redundancy (airline operator)
-complexity
-cost
Gyro-sensing units are connected to flight instruments that indicate _______, _______, ______, or _____.
direction, rate of turn, bank, pitch
The automatic pilot system flies the aircraft by using electrical signals developed in ___________.
gyro-sensing units
If the flight attitude or magnetic heading is changed, _____________ are developed in the gyros.
electrical signals
The electrical signals developed in the gyros when the flight attitude or magnetic heading is changed are sent to the autopilot computer/amplifier and are used to control the operation of _________.
servo units
A servo for each of the three control channels converts electrical signals into ________, which moves the control surface in response to corrective signals or pilot commands.
mechanical force
The components used in an Auto flight control system (AFCS) to move the aircraft’s control
surfaces are called ______ , ________or by the name of the control surfaces or channel
that it controls.
servomotors, servo actuators
All flight controls are hydraulically operated by the actuators which receive electrical signals
from the computer except the ______ and the _______
Rudder and the Trimmable Horizontal Stabilizer (THS)
powered by two servo controls
Aileron
are powered by their dedicated PCU
The Flaps and Slats surfaces
is powered by a single servo
Spoiler surface
is powered by 3 servo controls.
rudder surface
powered by 2 servo controls
elevator surface
The servo actuators convert these electrical signals into control surface movement by
converting the ________into ____________, which is usually done by torque motors
electrical,mechanical motion
moved by one actuator
THS
The _________ received from the AFCS are electrical. Therefore, the control of the _________ is
electrical.
signals, actuators
The servo actuators convert these electrical signals into control surface movement by
converting the electrical into mechanical motion, which is usually done by ______________
torque motors
Servomotors maybe connected in _________ or ________ with the AFCS.
series or parallel
A ____________ is
one that moves the control surfaces without moving pilot’s control
series servomotor
the ________________
moves control surfaces and the pilot’s control.
parallel servomotor
Three main types of actuators
-electric motor
-ecltro-pneumatic
-electro-hydraulic
the biggest feature of _____________ is high safety, cheap price and fast response speed.
Pneumatic Actuator
It uses compressed gas as the power source.
pneumatic actuator
Among the three types of actuators, _____________ has the advantages of fire proof, explosion proof, safe fault location and simple
operation.
pneumatic actuator
They are suitable for use in petrochemical, petroleum, and oil processing industries.
pneumatic actuator
The disadvantage of _________ is its poor stability, which is due to gas compressibility,
which makes ________ lack sufficient anti offset performance.
pneumatic actuator
the advantages of _________ are that it is
cost effective, easy to use, install and maintain and has relatively low technical requirements for
personnel.
pneumatic actuator
________ has a large output thrust
and high stability, but at the same time the
cost is lower than hydraulic actuator, which
is a cost-effective choice.
Electric actuator
receives electric signal,
which is prone to sparking problems.
Electric actuator
The parameter control of _________
is very accurate, but its structure is complex, the failure rate is higher than that of pneumatic actuator, and it requires professional personnel with higher technical level to operate and maintain it.
electric actuator
The downsides of ___________ include backlash, jamming and thermal management issues.
electromechanical actuators
A primary benefit of electromechanical
actuators compared to conventional
electrohydraulic actuators is their ______________.
elimination of hydraulic fluid
__________________ may appear to be an
optimal solution for more-electric and all-electric
aircraft, since they completely eliminate the need for
hydraulic fluid.
Electromechanical actuators
_________ can occur due to
gaps between interlocking gear teeth or screw
threads and results in positional inaccuracies.
It can increase as repeated wear cycles cause surface degradation.
Backlash
____________ is a risk for
electromechanical actuators due to potential failures involving screw components interfering or seizing up, preventing motion of the actuator.
Jamming
The performance advantages of __________ are many, such as large output thrust, good
offset resistance, precise control, fast response speed, stable operation and etc.
hydraulic actuator
Hydraulic actuator is driven by _________.
liquid
The liquid has the characteristics of _________ , _______________, and __________.
incompressibility, good anti offset ability and very stable adjustment
The disadvantages of _________ are the high cost and large volume. To run _______, hydraulic stations and oil pipelines are required.
hydraulic actuator
The ________ increases the risk of leakages and requires a large volume
of hydraulic fluid.
large hydraulic network
These are used in high performance aircraft and consist of two main types:
Power-Assisted
Power-Operated
The ___________ also requires a system of pipes to deliver pressurized hydraulic fluid to actuators distributed throughout the aircraft, adding additional weight and taking up
space.
central hydraulic network
In the _______________, the pilot’s control stick is connected to the control surface via a control
lever.
power-assisted system
The continuous energy
expenditure results in heating of the hydraulic fluid, requiring a ___________ to maintain
acceptable hydraulic fluid temperature.
cooling system
In a ___________, the pilot’s control column movements are interpreted by a flight computer that sends
electrical signals to actuator control electronics.
fly-by-wire
system
________ are displaced allowing the hydraulic fluid to flow to the left side of the actuating jack, which is secured to the structure
of the aircraft.
control valve pistons
__________ enabled aircraft manufacturers to integrate
more electrically powered actuators in airplane systems such as electro hydrostatic actuators
and electromechanical actuators.
Fly-by-wire systems
The _________ instruct the operation of
either hydraulic control valves to set in motion hydraulic actuators or electric motors to move
electromechanical actuators.
control electronics
__________________ have excellent power density (kW/kg) at the equipment
level but poor power density at the power distribution network level.
Conventional electrohydraulic actuators
The pressure exerted on the piston causes the whole servo unit and control level to move _________ and because of the greater control effort produced, the pilot is assisted in moving the control surfaces
move left
calculates orders to automatically control the flight controls and
the engines.
Automatic Flight System (AFS)
The ____________ calculates the position of the aircraft using several aircraft sensors.
Automatic Flight System AFS
These actuators are powered by electricity produced by
engine- driven generators delivered over power-by-wire systems
electro hydrostatic actuators and electromechanical actuators.
The Auto Flight System (AFS) is divided into four main parts:
Flight Management (FM),
Flight Guidance (FG),
Flight Augmentation,
Fault Isolation and Detection System (FIDS).
AFS computes orders and sends them to the ________ and to the ________ to control flying surfaces and engines.
Electrical Flight Control System (EFCS), Full Authority Digital Engine Control (FADEC)
A _________ describes a
complete flight from departure to arrival; it gives vertical information and all intermediate waypoints.
The plan can be displayed on the EFIS or on the Multipurpose Control & Display Units.
flight plan
When the
AFS is not active, the above-mentioned components are controlled by the same systems but orders are generated by the_______ and ____________.
side sticks and thrust levers
A fundamental function of the AFS is to calculate the aircraft position. To compute the aircraft
position, the system uses several aircraft sensors, which give useful information for this purpose.
NAVIGATION
The FG part has 3 functions:
Autopilot (AP),
Flight Director (FD),
Auto thrust (A/THR).
A flight plan describes a
complete flight from departure to arrival; it gives vertical information and all intermediate waypoints. The plan can be displayed on the ______ or __________.
EFIS or on the Multipurpose Control & Display Units
The __________ has several functions linked to the flight plan such as lateral and vertical guidance associated with
performance
computation.
FM part
_________ calculates the signal for the flight controls in order to follow the selected modes.
Autopilot
Auto Pilot engagement
Two AP (Auto Pilot) pushbutton
switches located on Flight Control
Unit (FCU)
Provide short term control
These modes
can be adjusted using Flight Control Unit (FCU) which can include:
Attitude Hold
Heading Hold
Vertical Speed Hold
Altitude Hold
Two AP (Auto Pilot) pushbutton
switches located on __________
Flight Control Unit (FCU)
The ____________ is the primary entry/ display interface
between the pilot and Flight Management and
Guidance Computer
Multipurpose Control and Display Unit MCDU
Auto Pilot Disengagement
Side Stick Push Button
By force
AP Pushbutton on FCU
Primary Flight Display (PFD)
-show the flight parameter (basic 6 instruments) and its display Autopilot engagement.
Upper ECAM/ Engine Warning Display Divided into 2 sections:
Upper Area
Lower Area
-Shows the flight plan
Navigational Display
- Shows engine parameters
ECAM Upper Area
- Dedicated to warning
messages and memo.
ECAM LOWER AREA
The ________ display the guidance commands on both PFDs.
Flight Directors
displays symbols on the PFD which gives orders to the pilot to maintain the desired
parameters.
Flight Directors function
-shows 11 system pages
Lower ECAM/ System Display Pages (SD)
-The FD function displays symbols on the PFDs representing the ________ to be monitored by the pilot.
AP orders
The _________ fulfils the following functions through the control of the thrust: Speed or Mach hold, Thrust hold, Thrust
reduction during descent and during flare in final approach, Protection against insufficient speed linked to excessive angle of
attack.
AUTOTHRUST
Auto thrust Engagement for manual and automatic
Manual: Pressing the A/THR on FCU
Automatic: When the A/P is engaged in take off (TO) or Go Around (GA)
To fulfil the A/THR functions, the FMGCs communicate with the Full Authority Digital Engine Control (FADEC) via the ________ and the ________.
FCU and the Engine Interface Units (EIUs)
