Inglês - Estruturas e Sistemas

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ESTAS INFORMAÇÕES SÃO PROPRIEDADE DA TRÍADE TREINAMENTO E NÃO PODEM SER UTILIZADAS 
OU REPRODUZIDAS SEM AUTORIZAÇÃO ESCRITA DA MESMA. 
Manual de Treinamento 
INGLÊS TÉCNICO 
INGLÊS 
 
TÉCNICO 
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AIRFRAME 
 
 
Part II: Text Exercises 
 
The Airframe is the basic structure of a plane, including fuselage, wings, 
empennages, etc. 
Left Wing 
Fuselage 
Right Wing 
Horizontal 
Stabilizer 
Wing / Fuselage 
Fairing 
Engine 
Vertical 
Stabilizer 
Forward Passenger 
Door 
Rear Passenger 
Door 
Emergency 
Door 
The fuselage is the main portion of the aircraft to which the wing, horizontal and 
vertical stabilizers are attached. 
The main function of the fuselage is to provide accommodation for the passengers 
and crew, as well as room for baggage in the overhead bins and in the forward 
and aft cargo compartments. 
The fuselage contains several systems and main structural components. 
The fuselage is divided basically in three parts: 
 
 Forward Fuselage 
 Center Fuselage 
 Rear Fuselage. 
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Forward Fuselage: it is the anterior part of the fuselage, and basically provides 
accommodations for pilots to fly the aircraft. 
 
Center Fuselage: it is the part of the fuselage that provides accommodations for 
flight attendants and passengers. 
 
Rear Fuselage: provides continuity to the fuselage, and connects the Center 
Fuselage to aircraft’s Tail Cone. 
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There are other important structural parts at the Fuselage: 
Frame 
Skin 
Stub 
Stringer 
Crossbeam 
Spar 
Skin 
Bulkhead 
 The Frames are vertical rings that give shape to the aircraft. 
 
 The Skin of the aircraft is a metallic component that covers the external 
 structure of the aircraft, and gives aerodynamics smoothly. 
 
 The Crossbeam is the rigid beam that provides support to cabin floor. 
 
 The Spar is a reinforced part of the aircraft that provides longitudinal support 
 to aerodynamics efforts. 
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 The Stringer provides longitudinal complementary support to aerodynamics 
 efforts. 
 
 The Bulkhead is a structural component that divides the aircraft into two 
 different compartments, closes the pressurized compartment and provides 
 structural strength. 
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EMPENNAGE 
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The Empennage is installed at Rear Fuselage and provides stability and control to 
Pitch and Yaw attitudes. 
The Vertical and Horizontal tail structures can hold inertial and aerodynamic 
loads, providing support to Rudder and Elevators. 
 
The Vertical Stabilizer is stationary, while the Horizontal Stabilizer is movable and 
operates as pitch trim. 
The Elevators are hinged at the trailing edge of the Horizontal Stabilizer, and the 
Rudder is hinged at the trailing edge of the Vertical Stabilizer. 
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WING 
 
The Wings are the main aerodynamic structure of an airplane. It creates lifting 
forces to sustain the airplane when flying. 
The wings can also storage fuel and place components as landing gear, engine 
and flight control surfaces. 
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RIB 
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The Wing main structure is made from aluminum alloy, and includes Spars, Ribs, 
Leading Edge and Trailing Edge. 
 
The Winglets are structural parts installed at wing tips, to prevent the creation ofvortex. 
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WING STUB 
 
The wings of an aircraft have many structural interfaces: 
The Wing Stub is a structural box at Center Fuselage, where the wing is installed 
at the aircraft. 
 
The Stub can be divided in two parts: 
 
 The Main Box provides Wing-to-Fuselage interface, and can storage extra fuel. 
 
 The Rear Box is the Main Landing Gear Compartment. 
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Wing to Fuselage Fairings (WFF) consist in many composite panels, which 
give a better aerodynamic shape to the wing-to-fuselage junction. 
 
They round wings corners and close the gaps. They also protect the systems and 
components attached to the wing stub-fuselage lower region. 
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DOORS 
 
There are many doors at Embraer aircrafts: 
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The Main Door is that one where the passenger and the crew enter the aircraft. At 
E-Jets Family, we have two main doors, the Forward Passenger Door and the 
Afterward Passenger Door. 
 
The Service Doors is the door where the ground service team fills the galleys with 
foods and drinks. At Embraer 170 / 190 Family, we have two service doors either. 
 
The Baggage Door is the door that closes the Baggage Compartment. We have 
the Forward Baggage Door that closes the Forward Baggage Compartment, and 
the Afterward Baggage Door, for the Afterward Baggage Compartment. 
 
The Emergency Door is the door where, in case of emergency, the passengers can 
leave the aircraft quickly. At E-Jets Family, the Emergency Doors are both Main 
Doors and both Service Doors. 
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The Main Flight Controls were developed to control the aircraft at the three flight 
axis: longitudinal, lateral and vertical. 
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The Secondary Flight Controls are composed basically by Trim Tabs, located at 
ailerons, elevators and rudder. They help Main Flight Controls to control the 
aircraft and to remove undesirable flight tendencies. 
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The Hyper Lifting Surfaces provide lifting for the aircraft, even in low speeds. They 
are basically composed by Flaps and Slats. 
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Slat Inboard 
Slat Outboard 
Flap Outboard 
Flap Inboard 
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The Flaps are surfaces installed at wing trailing edge, used to generate lift in low 
speeds. The Slats are surfaces installed at wing leading edge, used to elevate 
wing critical angle of attack when the aircraft angle of attack is high. 
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The Spoilers are hinged surfaces installed at wing upper part. They can be used to 
reduce airspeed (Speed Brake Function) by activating the Multi Function Spoilers. 
The Spoilers can also be used to eliminate lift (Lift Dumping Function), by 
activating the Ground Spoilers. 
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Speed Brake 
Lift 
Dumping 
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There are many components at the Flight Control System: 
 
 The Bellcrank is a device used to change the direction of an applied force. 
 The Cables are metal rope used in control systems. 
 The Pulley is a grooved wheel used to change the direction of a moving cable. 
 The Stop is the device that prevents excessive movement of a control. 
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_________________________________________________________________Tension is the degree of tightness to which a cable is stretched. 
 The Travel is the movement or the extension of movement of the control 
 surfaces. 
 The Turnbuckle is a device inserted in a length of cable to adjust its tension. 
 The Handle is a device used by pilots to change aircraft attitude during the 
 flight, in pitch and roll commands. 
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There are two types of aeronautical internal combustion engines: jet engines and 
reciprocating or propeller engines. 
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The propeller engine imposes a low acceleration at a large mass of air. The jet 
engine imposes a high acceleration at a low quantity of air. 
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The Engine Reverse System consists in a kit of doors in the shape of shell. When 
activated, the doors change the escaping gases direction to forward, producing a 
backwards reaction. 
This system helps the aircraft to decrease ground speed after landing. 
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The Nacelle is the compartment where engines are installed at the aircrafts. 
The Pylon is the structure that holds the engine. At Embraer E-Jets Family, pylons 
are installed at the wings. At Regional Family, pylons are installed at Rear 
Fuselage. 
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Engine System general components and characteristics are: 
 
 The Accessory Gearbox is a component that drives equipments such as 
 pumps and generators. 
 
 The Bearing is a mechanical device that reduces friction and carries the weight 
 of moving mechanical parts. 
 
 Compression is the pressure created when the air volume is reduced in a 
 cylinder. 
 
 The Connecting Rod connects the piston to the crankshaft, providing it power. 
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 The Cowling is a removable metal cover that protects the engine from outside 
 elements. 
 
 The Crankcase (bloco) is the part of the reciprocating engine that holds the 
 crankshaft. 
 
 The Crankshaft (cambota)is the part of reciprocating engine that receives 
power from connecting rods. 
 
 The Cylinder is the chamber in which a piston of a reciprocating engine moves. 
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 The Idle is the position of the throttles when the engines are running smoothly. 
 
 The Ignition System supplies the spark to fire the fuel-air mixture in the 
 Cylinder. 
 
 The Manifold Pressure is a measure of the power of an engine. 
 
 The Mixture Ratio is the measure comparing the weight of fuel with the weight 
 of air, supplied to the combustion chamber of an engine. 
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 The Reduction Gearbox is a component to reduce the speed of the propeller. 
 
 The Spark Plug is a device inserted in the cylinder head and used to produce a 
 spark for igniting the fuel-air mixture. 
 
 The Tachometer is the instrument for measuring engine revolutions per minute 
 (rpm). 
 
 The Thermocouple is a device that converts heat into electricity for driving 
 instruments. 
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 The Compressor is the component of a jet engine that causes great quantities 
 of air to be taken in. 
 
 The Engine Exhaust System carries the hot waste gases from the cylinders to 
 the outside air. 
 
 The Piston moves inside the Cylinder, that is the chamber of combustion of areciprocating engine. 
 
 The Throttle is a device for regulation the output power of an engine, and the 
 position of the throttles when the engines are running smoothly is called Idle. 
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There are two main interface systems that help to run and control the engines 
operations: 
The APU (Auxiliary Power Unit) is a jet engine designed to supply electrical 
and pneumatic power to aircraft systems, in flight or on ground conditions. 
The APU is located at the tail cone and its fuel is furnished by aircraft’s fuel 
system. 
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The FADEC (Full Authority Digital Electronic Controller) is the engine main 
controller. 
It can flexibly engine operations and reduce pilots work loads with high level of 
reliability and safety. The FADEC can control and monitor engine main functions 
and indicates failures that allows maintenance specialist to dispatch the aircraft on 
time. 
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The Propeller is the most important part of a reciprocating engine. 
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In a transversal view, the propeller can be compared to a wing that produces 
lifting in horizontal direction, or traction. When the propeller pulls back the air, 
there will be a reaction on opposite direction. This reaction produces the aircraft 
forward movement. 
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The Propellers general components and characteristics are: 
 
The Propeller Blades are the components that cause the lifting effects on a 
reciprocating engine. 
 
To Feather is to turn the edges of the propeller blades of a dead engine into the 
wind to reduce drag. 
 
The Hub is the central part of a propeller that secures the blades. 
Overspeed occurs when a propeller RPM above the desired setting. 
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The Propeller Governor is a device for adjusting the angle of the propeller 
blades to hold a constant engine speed. 
 
Synchronize: To cause to operate at the same speed. 
 
Turbo-Props: Airplanes powered by turbo-prop engines. 
 
Pitch: The angle of the propeller blades. 
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Part II: Text Exercises 
 
The aircraft Fuel System is designed to storage and feed engines and APU with 
fuel. 
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The Fuel System is divided into the following subsystems: 
The storage subsystem includes tanks with ventilation. 
The distribution subsystem, that allows the operations of engine refuel and defuel. 
The indication subsystem, that gives information of fuel quantity and system 
failures. 
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Fuel System general components and characteristics are: 
 
The Booster Pump supplies fuel to engine-driven pump, the Ejector Pump 
maintains the collector tank always full, and feeds the engine, and the Auxiliary 
Pumps help the main pumps to feed the engine continuously. 
The Carburetor is a device that mixes and regulates the flow of fuel and air to 
the engine. 
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The Cross Feed System is a system on a multi-engine airplane that allows an 
engine on one side to use fuel from cells on the opposite side. 
The Fuel Selector valve allows the pilot to choose the source of fuel. 
Sediments are solid impurities in fuel that settle to the lowest point of the 
system. 
Wet Wing is a term used to describe a fuel system that uses the skinof the wing 
as walls to contain the fuel. 
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The Collector Tank is the stub tank; it ensures continuous fuel feed to the 
engine. 
The aircraft fuel passes though the Feed Lines, where the fuel goes straight to 
the aircraft engine. 
The Fuel Strainers are devices used for filtering solid impurities out of the fuel 
before it reaches the engine. 
The Shutoff Valve is an important component that cuts the engine fuel feeding, 
before reaching the engine. 
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VENTILATION SYSTEM 
 
The Ventilation System is an important interface system of the Fuel System. It is 
designed to maintain differential pressure between aircraft’s tanks and 
atmosphere, under all operational conditions, and either to prevent fuel sprinkle. 
 
The Ventilation System main components are: air inlets named NACA, surge relief 
valve, float vent valve, pressure relief valve and flame arrester. 
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Shimmy Vibração 
Shock Absorber Amortecedor 
Standard Padrão, Comum 
Strut Perna de Força 
Tire Pneu 
Tricycle Triciclo 
Valve Válvula 
Wheel Roda 
Part II: Text Exercises 
The Hydraulic System is designed to supply aircraft with hydraulic power, to 
operate several units, in replacement of man power. 
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A standard Hydraulic System has basically the same components: 
 
The Hydraulic Fluid for strength transmission of power, the Reservoir to 
storage the hydraulic fluid; several Pumps to move the fluid through the lines; 
Actuators to change hydraulic flux into mechanic power; Lines to transport the 
fluid; and Valves to control hydraulic pressure and flux. 
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The Landing Gear Sub-system consists in providing the aircraft with ground 
support, and protects the airframe from landing impacts. It is normally retractable 
and in tricycle format, consisting in two main landing gears and one nose or 
auxiliary landing gear. 
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The Landing Gear System has leg structures, shock absorbers, brakes, retraction 
mechanisms, fairings, wheels and tires. It also has an emergency extension 
system that allows landing gear down movement, in case of the main system 
failures. 
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Hydraulic System general components and characteristics are: 
 
The Cylinder is a device that extends or retracts, when a pressure is applied. 
The By Pass Valve is used to deviation of the fluid flow. 
The Gasket is the usually metal or fiber used between two parts to prevent 
leaking of air or fluid. 
The Jack is a device used for raising the airplane so that its weight is taken off 
the wheels. 
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The Pump is a device for moving fluid. 
The Strut is a member of the Landing Gear that holds the wheel in place. 
Wheel is a device that allows the aircraft to run through the taxiway and landing 
way. 
The Check Valve allows the hydraulic flux to flow in only one direction. 
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Brakes were designed to decelerate, to stop, to park and to maintain the aircraft 
stopped, even with the engines running. The brakes are installed one in each 
main landing gear wheel, and it is actuated independently to the other assy. 
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The Disk is a round flat plate which turns with the wheel and against it when 
braking forces are applied. 
The Drum is a cylinder attachedto the wheel, against which braking forces are 
applied. 
The Pad is the small part that is pressed against the disc to give breaking action. 
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The Relief Valve prevents pressures from exceeding a pre-set amount. 
A Shimmy is the vibration of any wheel. 
The Antiskid is the electronic system that prevents the aircraft to skid after 
landing, allowing a safety deceleration, even in a hard activation of the system by 
the pilots. 
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PART II: EXERCISES 
The Air Management System is designed to supply comfort and life support to the 
passengers and the crew. It is divided into many other systems like: 
 Pneumatic System 
 Air Conditioning 
 Pressurization 
 Oxygen 
 De-Ice 
 Anti Ice. 
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The Pneumatic System works exactly like the hydraulic system, but instead of 
hydraulic fluid it is used air to generate power. It supplies air extracted from 
engines to air conditioning and anti-ice systems. 
The Regulating Valves are devices to regulate the pressure of the air extracted 
from engines. 
Shut Off Valve: cuts completely the air flux. 
The Pressure Sensor feels the level of pressure in the air and sends information 
to regulating valves. 
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ESTAS INFORMAÇÕES SÃO PROPRIEDADE DA TRÍADE TREINAMENTO E NÃO PODEM SER UTILIZADAS 
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Manual de Treinamento 
INGLÊS TÉCNICO 
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Temperature Sensor: it senses air temperature an send informations to the 
system controllers. 
The Precooler is a device that cools the hot air extracted from the engines 
Check Valve: forces the air flux to go in only one direction. 
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The Air Conditioning System was designed to maintain a comfortable air 
temperature inside aircraft cabin, heating or cooling the air as needed. And 
besides, the system supplies air flux to control aircraft pressurization. 
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The Heat Exchanger cools the system hot air at the same time it heats the 
aircraft fuel. 
The Water Separator removes condensed water from the system. 
The Heater is a device that heats the air as needed. 
The Thermostat is a device to regulate automatically the air temperature 
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ESTAS INFORMAÇÕES SÃO PROPRIEDADE DA TRÍADE TREINAMENTO E NÃO PODEM SER UTILIZADAS 
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Manual de Treinamento 
INGLÊS TÉCNICO 
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The Temperature Sensor feels the temperature of the air and sends information 
to the system controllers. 
The Blower moves the air inside the cabin. 
The Pack is the main component of the system. It adjusts air flux and pressure to 
desirable levels. 
Ventilation: function of the system that circulates fresh air at the cabin. 
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The Pressurization System operational principle simulates a pressure vessel, 
consisting in inserting pressurized air at a reinforced and sealed portion of the 
aircraft. An outflow valve controls pressure regulating air flow outside the cabin. 
Even though the aircraft can fly in high altitudes, the internal pressure can be set 
up to a comfortable level. 
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ESTAS INFORMAÇÕES SÃO PROPRIEDADE DA TRÍADE TREINAMENTO E NÃO PODEM SER UTILIZADAS 
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The Outflow Valve controls the cabin pressure. 
The Vacuum is total absence of air in a confined place. 
Inlet and Outlet is the way the air is allowed to enter or to exit the cabin. 
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The aircraft Oxygen System is divided into two parts, one that supplies oxygen 
to crew and another one that supplies oxygen to passengers. The oxygen is 
supplied through portable oxygen cylinders, provided with a regulator assembly, 
masks, flow indicator and plastic tubes. 
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_________________________________________________________________Ducts: Tubes that are used to carry oxygen. 
Masks: A short way of saying oxygen masks, which are worn on the face to 
supply oxygen at high altitudes. 
Oxygen Regulator: Controls the amount of oxygen flow into a mask. 
The Filler Valve allows external operations to fill oxygen cylinders. 
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ESTAS INFORMAÇÕES SÃO PROPRIEDADE DA TRÍADE TREINAMENTO E NÃO PODEM SER UTILIZADAS 
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Manual de Treinamento 
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The Pressure Gauge measures the input pressure inside the oxygen cylinders 
and indicates the pressure level of the oxygen 
Pressure Switch: Indicates to maintenance staff the pressure level of the 
oxygen. 
The Chemical Generator supplies passengers with oxygen generated by 
chemical reactions. 
The Oxygen Portable Bottles can carry oxygen that flight attendants use when 
walking by the cabin. 
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The Anti-Ice System works under certain atmospheric conditions, where ice can 
build rapidly on airfoils and air inlets, thus affecting the performance and 
efficiency of the aircraft in many ways. 
Pneumatic deicing systems use rubber deicers called boots, attached to the 
leading edge of the wing and stabilizers. 
During operation the tubes are inflated with pressurized air, and deflated in an 
alternating cycle, thus causing the ice to break off. 
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ESTAS INFORMAÇÕES SÃO PROPRIEDADE DA TRÍADE TREINAMENTO E NÃO PODEM SER UTILIZADAS 
OU REPRODUZIDAS SEM AUTORIZAÇÃO ESCRITA DA MESMA. 
Manual de Treinamento 
INGLÊS TÉCNICO 
The Air Management System general components and characteristics are: 
 
The Boots are inflatable deicer. 
The Defroster is a device for removing frost or mist from the windshield. 
The Deicer is a system for removing ice after it has formed. 
The Windshield Wiper is a device used for removing rain from the windshield. 
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ELECTRICAL SYSTEM 
 
 
PART I: VOCABULARY 
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Several Vários, Diversos 
Short Curto Circuito 
Starter Motor de Partida ou de Arranque 
Switch Chave, contactor 
Take off Decolagem 
Taxi Light Farol de Táxi 
Voltmeter Voltímetro 
Wire Fio, Fiação 
PART II: EXERCISES 
The aircraft Electrical System consists in generation and distribution of electrical 
energy used to allow the functioning of several systems, including equipments, 
illumination circuits, and failure alarms. 
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ESTAS INFORMAÇÕES SÃO PROPRIEDADE DA TRÍADE TREINAMENTO E NÃO PODEM SER UTILIZADAS 
OU REPRODUZIDAS SEM AUTORIZAÇÃO ESCRITA DA MESMA. 
Manual de Treinamento 
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The Generation & Distribution System is the responsible to feed all aircraft 
systems with electrical power. 
 
The Generation & Distribution System is usually composed by batteries, 
generators, fuses, switches, relays, connectors, cables and wires, converters and 
circuit breakers. 
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The Electrical System general components and characteristics are: 
 
AC / DC are the abbreviations for Alternating Current and Direct Current 
The Alternator is an engine-driven device for producing AC Power. 
 
APU: Auxiliary power unit. 
The Battery is a device that stores and supplies the aircraft with DC Power. 
The Master Switch is the main switch for controlling the entire system. 
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The Bus Bar is a heavy wire that distributes power from the battery to each 
major circuit. 
The Circuit is the path over which electricity flows. 
Circuit Breakers are devices to disconnect an electrical circuit in case of 
overload. 
The Wires are electrical conductors for energy through all electrical system. 
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ESTAS INFORMAÇÕES SÃO PROPRIEDADE DA TRÍADE TREINAMENTO E NÃO PODEM SER UTILIZADAS 
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Manual de Treinamento 
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The Fuse is a device that melts when excessive current flows through it. 
The Generator is an engine-driven device for producing DC 
The Inverter is a device for changing DC into AC. 
A Short Circuit is the failure of an electrical current to flow through the entire 
circuit. 
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The Starter is a device for turning the engine to prepare it to run under its own 
power. 
The Voltmeter is an instrument for showing the difference of potential in 
electrical force between two points of a circuit. 
The Ground Power Unit (GPU) is the unit that generates electrical current to 
energize the aircraft on ground. 
The Harness is an assembly of wires and/or cables arranged in a way it may be 
installed or removed as unique unit. 
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The Aircraft lighting systems provide illumination for both exterior and interior 
use. Lights on the exterior provide illumination for such operations as landing at 
night, inspection of icing conditions and safety from midair collision. Interior 
lighting provides illumination for instruments, cockpit, cabin and other sections 
occupied by crew members and passengers. 
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ESTAS INFORMAÇÕES SÃO PROPRIEDADE DA TRÍADE TREINAMENTO E NÃO PODEM SER UTILIZADAS 
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The Landing Lights are installed at wings leading edges. They provide lighting 
for obstacles, and ground references during approaches, landing and take-off. 
The Taxi Light is installed at Nose Landing Gear and lights an adequate area in 
front off the aircraft. 
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The Navigation Lights provides position reference from one aircraft to another. 
The red light is installed at the forward part of left wing tip, the green light is 
installed at the forward part of right wing tip, and white lights are installed at rear 
part of both wing tips. 
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The Anti-collision Lights provides proximity reference from one aircraft to 
another. The white stroboscopic lights are installed at both wing tips. One red 
beacon is installed at upper fuselage and the other is at the lower fuselage. Both 
must be on when engines are running or when the aircraft is on movement. 
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ESTAS INFORMAÇÕES SÃO PROPRIEDADE DA TRÍADE TREINAMENTO E NÃO PODEM SER UTILIZADAS 
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The Inspection lights provide wings leading edges and engine air intakes 
illumination, to allow crew inspection for ice formation. 
The Logo Lights provide illumination for operator logo painted at vertical 
empennage. 
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The Cockpit Lights provide general and local illumination for all instruments, 
control panels, flood lights and reading lights. Instruments and panels lights are 
electronically dimmed by potentiometers located at front panel. 
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The Cabin Lights are composed by several flood lights, distributed proportionally 
by passenger’s cabin, and controlled by flight attendant controls. Lavatory, Galley 
and Main Door areas are provided by individual lights. The PSU - Passengers 
Service Units have reading light and call switch for each seat. 
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The Emergency Lights system is provided by individual power units, 
independent from aircraft’s electrical system. They allow crew and passengers to 
leave the aircraft safely, in case of night emergencies. 
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ESTAS INFORMAÇÕES SÃO PROPRIEDADE DA TRÍADE TREINAMENTO E NÃO PODEM SER UTILIZADAS 
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AVIONIC SYSTEM 
 
PART I: VOCABULARY 
Aid, to Ajudar, auxiliar 
Airspeed Velocidade Aerodinâmica 
Altimeter Altímetro 
Antenna Antena 
Artificial Horizon Horizonte Artificial 
Avoid, to Evitar 
Bearing Direção, Afastamento Relativo 
Bus Coupler Acoplador de Barramento 
Clock Relógio 
Collision Colisão 
Communication Comunicação 
Course Curso 
Data Bus Barramento de Dados 
Diagnosis Diagnóstico 
Display Mostrador 
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Frequency Freqüência 
Glide Planeio 
Gyro Giroscópio 
Inner Interno 
Localizer Localizador 
Locator Localizador 
Magnetic Compass Bússola Magnética 
Maintenance Manutenção 
Marker Marcador, Sinaleiro 
Measure, to Medir 
Meteorological Meteorológico 
Middle Mediano, Intermediário 
Multifunction Funções Múltiplas 
Navigation Navegação 
Omni-Directional Em todas as direções 
Outbound Afastamento 
Outer Externo 
Path Trajetória, Trajeto 
Radial Radial, Raios (circunferência) 
Receiver Receptor 
Recorder Gravador 
Regulations Regulamentos, Regras 
Static Estático 
Traffic Tráfego 
Transceiver Transceptor 
Transmitter Transmissor 
Transponder Transponder 
Turn and Bank Curva e Inclinação 
Vertical Speed Velocidade Vertical 
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ESTAS INFORMAÇÕES SÃO PROPRIEDADE DA TRÍADE TREINAMENTO E NÃO PODEM SER UTILIZADAS 
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Manual de Treinamento 
INGLÊS TÉCNICO 
PART II: TEXT EXERCISES 
 
The Avionic System of an aircraft provides the resources needed to internal and 
external communications, navigation aids, instruments landing, aerial traffic, 
meteorological information, computer data processing, and automaticflight 
controls. 
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The aircraft Avionic System is composed basically by Flight Instruments, 
Navigation System, Computing System and Communication System. 
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ESTAS INFORMAÇÕES SÃO PROPRIEDADE DA TRÍADE TREINAMENTO E NÃO PODEM SER UTILIZADAS 
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The basic aircraft instruments are: 
 
The Artificial Horizon is used to show the attitude of an airplane, what is the 
position of its wings and fuselage in relation to the earth, frequently called 
attitude indicator. 
The Magnetic Compass is an instrument that points to the magnetic north of the 
earth. 
The Turn-and-Bank Indicator measures the rate of turn. It is also called as turn 
and slip. 
Glide Path: The descending path flown by an airplane on an ILS approach. 
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The Vertical Speed Indicator shows the rate of altitude change, when the aircraft 
is climbing. 
The Airspeed Indicator measures the speed of the aircraft through the air. 
The Altimeter is an instrument for measuring the aircraft altitude. 
The Digital Clock is a digital display that shows time, chronometer and calendar. 
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Multi-Function Display (MFD): Shows navigation graphic part, such as flight 
plans and maps, and pictorial parts of some systems, like flight controls, electrical 
and hydraulic system. 
 
Engine Indication And Crew Alerting System (EICAS): Shows warning 
messages and indications like engine status, fuel, landing gear, etc. 
 
Primary Flight Display: Digital display that shows pilot and copilot tactical flight 
indications, such as navigation and radio backup. 
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Some Navigation Devices are: 
 
Directional Gyro: A flight instrument stabilized by a gyroscope that shows the 
direction of flight. 
IFR: Instrument Flight Regulations. 
The Localizer is a part of the ILS that transmits a signal to indicate alignment 
with the runway. 
Middle Marker: The marker beacon placed about half mile from the end of 
runway, along the glide path. 
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Outer Marker: The marker beacon placed at the point of glide slope interception. 
The ADF (Automatic Direction Finder) indicates a local commercial radio station, 
nearby the runway. 
Back Course: An approach to a runway in an opposite direction to that from 
which a normal approach is made. 
Course Selector: The control on a VOR receiver that selects the desired radial 
from VOR. 
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The DME measures the distance between the aircraft and the next runway. 
ILS: (Instrument landing system) An instrument approach system. 
Outbound: To fly away from the radio facility. 
 
A Radial is a magnetic bearing extending from a VOR and to “go outbound” is to 
fly away from the radio facility. The VOR is the VHF (Very High Frequency) Omni-
directional Radio range. We use the Course Selector to control the VOR receiver 
that selects the desired radial from VOR. 
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The Global Positioning System (GPS) is a satellite navigation system that 
receives signals to compute aircraft global positioning, speed and time. 
The Radar Altimeter provides crew with aircraft ground altitude when 
approaching and landing. 
The Meteorological Radar main function is the detection of flight meteorological 
conditions in front of the aircraft. 
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The Emergency Locator Transmitter (ELT) is the equipment that provides 
automatic transmissions, by satellite, in case of aircraft collision. 
The Digital Voice & Data Recorder (DVDR) records and preservesall 
stipulated flight data parameters, and records the voice inside the aircraft. 
The Traffic Collision Avoidance System (TCAS) is an Independent system 
that monitors transponder equipped aircrafts course, witch have high potential 
risks of collision, and allows crew with the better escape maneuver. 
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ESTAS INFORMAÇÕES SÃO PROPRIEDADE DA TRÍADE TREINAMENTO E NÃO PODEM SER UTILIZADAS 
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Manual de Treinamento 
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Some of the Computing equipments that are used nowadays are: 
 
The Auto-Pilot is a system designed for automatically maintaining a pre-set 
course. 
Computer: A device used by pilots to solve navigational problems quickly. 
The Pitot-Static System operates the flight instruments that sense the 
movement and pressure of outside air. 
The Pitot Tube admits air to the instrument for measuring speed, and the Static 
Port is a lateral opening to obtain static air pressure. 
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Static Port: An opening to obtain static air pressure. 
The Data Bus is a digital way that allows communication between several 
computers. 
The Bus Coupler connects the data bus to all computers. 
The Central Maintenance Computer (CMC) is the computer that storages, 
manages and allows systems failure diagnosis. 
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Some Communication Devices are: 
 
The Transponder is an electronic device carried in an airplane that causes a 
distinctive pattern to appear on observing radar. 
The Antenna is a device for sending and receiving electromagnetic waves. 
The Receiver is a radio device for receiving radio signals, and the Transmitter is 
for sending radio waves. The Transceiver is a radio that is capable of sending 
and receiving electromagnetic messages. 
Static is an undesired noise on a radio. 
Transceiver: A radio that is capable of sending and receiving message. 
Transmitter: A radio device for sending radio waves. 
VHF is an abbreviation for very high frequency. 
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ESTAS INFORMAÇÕES SÃO PROPRIEDADE DA TRÍADE TREINAMENTO E NÃO PODEM SER UTILIZADAS 
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Manual de Treinamento 
INGLÊS TÉCNICO 
PART II: TEXT EXERCISES 
 
Aircraft Cabins: are designed to provide comfort to passengers and crew. 
Nowadays, pilots can seat in an aircraft, with high comfort levels, flying at 35,000 
feet, breathing pressurized air, at the temperature of 21° C, and provide this 
same comfort to passengers. 
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One typical cabin configuration is composed by flight compartment or cockpit, 
passengers’ compartment, galleys and wardrobes, toilets and baggage 
compartment. 
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The cockpit furniture is composed basically by two pilots’ seat with arm rest 
and seat belt, one observer seat, panels and consoles for flight operations, 
portable oxygen equipments, and a portable fire extinguisher. 
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The basic passengers compartment internal configuration has Pax seats side-
by-side, flight attendant seats, and passenger service units (PSU). The PSU is 
configured with loudspeakers, crew call pushbuttons, reading lights, oxygen 
masks dispenser, gasper air outlet, and the visual signals of “non smoking” and 
“fasten seat belts”. 
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The Pax cabin, depending on aircraft configuration, has reclining Pax seats with 
abdominal seat belts, food table for meals, a literature pocket and a lifejacket 
under the seat. 
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At Embraer Aircrafts, the Baggage Compartment can be located at the rear part 
of the aircraft, or under the Pax Cabin. They offer space for passengers’ luggage 
and other types of loads. 
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In the galleys flight attendants can storage food. They have oven to prepare hot 
meals and a refrigerator that allows serving cold drinks. In the galley is localized 
entertainment and announcements center to passengers. 
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The Lavatory is a reserved place in the aircraft, which provides passengers with 
some privacy. Usually it is located at aircraft rear section, and it is divided into 
sink section and toilet section. The Lavatory has the same visual and aural 
warnings that there are in Pax Cabin, and it still has smoke detectors. 
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