Which of the following loads of the gear is the biggest one
Vertical load
Friction
Gear recoil
Aerodynamic loads
What is the bleeding system that is used on fighter aircrafts?
a) High pressure system with a heat exchanger with ambient air
b) High and low pressure system with a heat exchanger between them
c) High and medium pressure system with an anti-return valve
d) Answer c and also with a heat exchanger with the fan flow
The Kreuger flap is placed at:
Leading edge
Trailing edge
Wing tip
c/2 of the chord
Factor affecting the fatigue
With more temperature less fatigue
Traction is the load that causes more fatigue
Corrosion decreases fatigue
Welding decreases fatigue
Choose the more correct option about these De-Icing system types:
There are three types: cyclical, wets, and evaporative.
In aviation there are only anti-icing systems, not de-icing.
There are mainly three types: cyclic, by evaporation and wets. The latter are in danger of ice forming downstream.
All of the above are false.
One of main uses of the pneumatic system is:
a) Movement of the control surfaces (flaps, slats…)
b) Cabin pressurization and air conditioning
c) Pitot tube anti-icing
d) As a help to the afterburner
According to the structure levels. Which level if fails ensures no catastrophic failure but limited operations.
Primary
Secondary
Tertiary
Non of them
About the Anti-Icing system of the pitot set:
It is based on a fluid heating system.
It consists of an electrical resistance system inside the pitot tube.
It is based on an electrical heating system of the outer surface of the pitot tube.
It is false that there is an anti-ice system in the pitot complex since the formation of ice in it is not contemplated.
Which of the following is not one of the rules that a pneumatic system must comply with?
a) It should exist a shut-off valve in case of emergency
b) The bleed quantity should be the minimum
c) It should be situated far from engine
d) A system should be integrated to report the status of the valves
Which structure is damage tolerant
Fail safe structure
Life safe structure
Jar 23 structure
Primary structure
Choose the incorrect option referred to the Electro Expulsive De-Icing System:
The system is based on an electromagnetic wave that induces a current on the edge surface.
It is effective against very thin ice, even 0.7mm.
The system has a high consumption.
a) and b) are correct, c) is incorrect.
What is the name of the aids to the vertical fly of the Harrier, which are situated on wingtips and use bleed air?
a) Puffers
b) Slots
c) Directional nozzle
d) This system doesn’t exist
Select the incorrect type of joints
Mechanical
Adhesive
Metals
Anodized
About the Anti-Ice systems:
The El-Thermal and Bleed Air systems are capable of removing thinner ice than the Pneumatic Boots and Expulsive systems, and they also have shorter life cycles.
El-Thermal and Bleed Air systems have infinite life cycles, but Pneumatic Boots and Expulsive systems can remove thinner ice.
El-Thermal and Bleed Air systems have infinite life cycles and also remove thinner ice than Pneumatic Boots and Expulsive systems.
All four systems have infinite life cycles but the El-Thermal and Bleed Air systems can remove thinner ice.
The pneumatic systems:
a) They can replace to the hydraulic system in any case
b) Usually they have more applications than the hydraulic system
c) They require high working pressures
d) All of above are false
Which is not an advantage of composites
Ptfe
Gfrp
Cfrp
aramid
Choose the correct option:
The first point where icing occurs is generally in the ice detection system, due to its characteristics such as fine edges and the stagnation point condition.
The first point where ice formation takes place is at the wing ends.
A preventive measure when flying in icy conditions is the use of the autopilot.
The “Vibrating rod ice detector” is the most effective and extended flight ice detection system.
The statements a) and d) are correct.
One of the advantages of the pneumatic system is:
a) It need low pressures for work
b) It don’t need a return route, the air is available at the atmosphere
c) It’s rare to have leaks
d) All of above are advantages
Fatigue reduction
Weight
Properties
Maintenance
The propeller De-Icing system involves a reduction in aerodynamic capacities as well as mass unbalanced that can cause vibrations.
The engine's antifreeze system normally mixes hot air with oil.
Statements a) and b) are correct.
All the statements are false.
The bleed air comes from:
a) Engine compressor in jet engines
b) Turbocharges in no jet engines
c) Engine turbine in jet engines
d) a and b are true
The aluminium alloy most used in aviation is
70-75
60-65
40-45
30-35
Choose the incorrect option:
A key solution against damage from electric shock (lightning) on aircraft is to make the structure as a whole a good electrical conductor.
Approximately an aircraft suffers 1 lightning strike per 1500 flight hours.
Continuity in the structure of the aircraft in addition to ensuring that it acts as a "mesh" have no importance in terms of lightning strikes.
Normally tests and simulations are carried out to determine the areas most susceptible to damage.
The air bleeding from the engine:
a) Must go through a conditioning system before being used
b) Can be used directly from the engine
c) Usually it is only use during the aircraft is on ground
The best aircraft shape for supersonic flight is made considering:
Smooth contours to minimize drag
Cylindrical shape to minimize drag
Area rule to minimize drag
Wingspan rule to maximize lift
Regarding the “Static Precipitation” phenomenon, it can be stated that:
The phenomenon takes place because the structure is positively charged.
The phenomenon occurs due to the negative charge of the structure, and is based on the electrical asymmetry that takes place between the different parts of the aircraft.
The discharges can cause electronic noise in the systems, and even greater damages if these are of great intensity.
b) and c) are correct.
What is the structure that better resists the pressure?
Cylindrical
Square
Triangular
Sphere
When a Kreuger flap is actioned the curvature/geometry of the aerodynamic profile is modified, whereas with a Slat this does not occur:
True
False
False, the Kreuger flap does not change the curvature of the aerodynamic profile
False, with the Slat the same thing happens
The monocoque structure is usually used in:
Airlines aircrafts
Missiles
Military aircrafts
Light gliders
The most popular flap extension mechanism is:
Paddling
Articulated Rods
Rails
None of them
Semi-monocoque advantages over monocoque is:
Easyly to repair
Reduced weight
More tolerant to damage
All of the above
The main advantage of an hydraulic system over an electrical system for the extension of the landing gear/flaps is
Less cost
It provides a faster actuation
It provides a greater force
Less weight
Torsion is suported by:
Skin
Stringers
Formers
All of the above, which is called torsion box
The main problem that the first analog Fly-By-Wire had was:
Unreliable system due to actuator
The system crashed when receiving conflicting commands between pilot and actuator
Delay between command and action on control surfaces
Very heavy wiring and electrical system
All the passengers must leave the aircraft with 50% operative doors in:
30 seconds
90 seconds
Two minutes
Three minutes
Power By Wire (FBW) works with a ________ electrical system
Single phase (monophasic)
Two phase (bifasic)
Three phase
Spars, ribs, stringers and skin are:
Structural elements
Engine elements
Electric elements
Fire protection elements
The main difference between Integrated Actuator Package (IAP) and Power By Wire (PBW) is that the PBW’s electric motor constantly pressurizes the hydraulic system. While the IAP, has an hydraulic engine that pressurizes the system at the request of the actuator.
False, the IAP does not have an actuator
False, the PBW does not have an electric motor.
Braced monoplaces are used for
High-speed aircrafts
Low-speed aircrafts
Supersonic aircrafts
Acrobatic aircrafts
The Electro-mechanical Actuator (EMA) has not yet been tested on primary controls of an aeroplane:
False, it was first tested on 2017
True, and it is never going to be tested due to its complexity
False, it was first tested on 2019
What can be considered such as the main advantage of biplane aircraft?
Double lift
Easiest production
Esthetical reasons
Structural strengths
The wing mounted landing gear is attached to:
a. Any part of the wing span
b. The main spar
c. The main span or any stringer, it doesn´t matter
d. There are no wing mounted landing gears
Cables in biplane aircraft were interesting because:
Compression efforts
Tension efforts
Both compression and torsion.
The main advantage was drag reduction
In general, cantilevered wings require a rigidization that consist of:
a. The joint of two spars from the wing to the main longeron of the fuselaje
b. The addition of auxiliar spars
c. Both A and B are correct
d. None of the previous is correct
Which efforts were responsible of excessive angle of attack accidents:
Compression
Tension
Torsion
G forces
One advantage of low wing is:
a. Shorter landing gear with lower weight
b. Fuselage closer to ground
c. Prevent floating (ground effect) when landing
d. Both B and C are correct
The internal force within the structure that opposes the external force is:
Buckling
Strain
Stress
Strain or stress indifferently
One advantage of high wing:
Buckling effect appears due to ______ efforts:
One disadvantage of high wing is:
a. Blocks pilot´s visibility in small aircrafts
b. Bigger engines are allowed
c. Requires structures to accomodate the landing gear
d. Both A and C are correct
Which of that reduces buckling effect:
Thinner coating
Thicker coating
More distance between anchor points
It is specific and fix for each material
The element used to attach the engine to the wing is called
a. Pylon
b. Spar
c. Formeron
d. Rib
Which could be a good reaction to stop buckling effect:
Do not touch aerodynamic controls
Climb or descent immediately
Increase or reduce speed
Turn 90 degrees left or right
Comparing the tailplane structure with a wing´s one:
a. The tailplane has more ribs and les stringers to provide it more torsion rigidity
b. Both structures are exactly equal
c. In fighters the tailplane has formerons to give the fuselaje more rigidity
d. All the previous are false
What is not considered such as a function of the airframe:
Protect passengers and payload
Resist applied loads
Provides thrust to the aircraft
Defines aerodynamic shape
Most fighter planes tailplanes are categorized as:
a. Conventional
b. T-tail
c. Twin tail
d. H-tail
C-101 landing gear has the following configuration
Tricycle.
Quadricycle
Bicycle
Multi-bogey.
1. Choose the incorrect answer. The advantages of HYDR.SYSTEMS are:
a. Self-Lubricant System
b. Easy instalation
c. Low cost
d. Useful for small forces
El tipo de llanta más utilizada en las aeronaves es:
Llantas “well base”, similares a las utilizadas en automoción.
Llantas “detachable flange”.
Llantas del tipo “Split hub”, que se se dividen en dos partes para facilitar el montaje y desmontaje de los neumáticos.
Ninguna de las anteriores.
2. Choose the incorrect HYDRAULIC vs PNEUMATIC:
a. The power of pums can work up to pressure ratio of 650, but the power of the pneumatic system is limited.
b. Pneumatic systems have stop time while hyudralic systems work continuously.
c. Hyudralic system has greater pressure losses due to viscous effects, and pneumatic dissipate more heat due to compressibility effects (hyudralics are generally more efficient)
d. Hyudralic system has greater pressure losses due to compressibility effects, and pneumatic dissipate more heat due to viscous effects (hyudralics are generally more efficient)
Most used tyres in aeronautical are:
Common tyres as used in automotive.
Radial tyres, which are more resistant.
Both, regarding it is front tyre or principal gear
None of the above
3. Desired properties, choose the incorrect:
a. Low viscosity
b. High viscosity
c. Resistance to heat
d. Good lubricant properties
Drawing used in tyres most commonly is:
Longitudinal, In order to improve the surface resistance during the braking
Both directions as in automotive
any of them because it is just aesthetic
None is the above
4. Types of HYD fluids:
a. Vegetable-based, mineral-based, sintethic base
b. Vegetable-based, water-based, sintethic base
c. Vegetable-based, oil-based, sintetic base
d. Vegetable-based, fuel-based, hyudaulic base
Aquaplaning or hydroplanning occurs in aeronautical when:
It rains to much and the aeroplane surface gets wet
When the amount of water accumulated in front of the tyre is enough to lift it and make it lose its adhesion
Every time the runway is wet
5. Basic elements of hydraulic systems are, choose the incorrect:
a. Reservoir
b. Pump
c. Selector Valve
d. Triple Acting clylinder
aeroplanes have different kind of control surfaces
Primarias: alerones, estabilizadores horizontal y vertical. Primary: ailerons, horizontal and vertical stabilisers
Secondary: flaps and aero brakes .
A and B are correct
A y B are false
6. Nowadays typical HYD pessures are:
a. 3000-4000 psi
b. 200-100 psi
c. 15000-25000 psi
d. 1000-10000 psi
controls in present aeroplanes, manufactured from the 90s, are:
By Fly-by-wire technology
with cables and pulleys
by power-by-wire technology
None of above
7. Linear actuartors = jacks
a. Convert fluid pressure into linear motion
b. Convert linear motieon into circular motion
c. Convert fluid motion into linear pressure
d. All are false
En determinados aviones, se utilizan unos alerones también para obtener efectos hipersustentadores. Estos reciben el nombre de:
Alerones.
Flaps.
Flaperones.
8. Selectors or flow control devices, choose the incorrect:
a. Rotary selectors
b. Linear or spool valve selectors
c. Electrical locks
d. Non-return valves (NRV)
FBL means:
Fly by Light and is based on the use of optic fibre
Fod by Landing
Fresh Beacon Light and its use as a navaid is crucial
Fly by Light
Las siglas EAP se corresponden con
Electronic Auto-Pilot, siendo el prototipo del F14
Experimental Aircraft Programme, siendo el prototipo de F22
Extreme Aerobatic Performance, siendo el prototipo del F35
Experimental Aircraft Programme, siendo el prototipo del EFA2000
El sistema FBL tiene entre sus ventajas
Es un sistema muy utilizado y desarrollado
Evita las interferencias electromagnéticas
Es más estético
Evita el uso de superficies de vuelo
Durante la WWII los sistemas anti-hielo incluían
El uso de anticongelante líquido que se rociaba sobre el borde de ataque a través de unas perforaciones en el mismo
El uso de anticongelante líquido que se rociaba en vuelo desde la cabina mediante el uso de mangueras
El uso de energía eléctrica que impedía la formación de hielo
No existió tal sistema durante la década de los 40
El coeficiente de resistencia de un ala con hielo
Disminuye siempre
Aumenta
No afecta a la performance
El hielo no puede adherirse al ala en vuelo
Los sistemas anti-hielo
No pueden prevenir la formación de hielo
Previenen la formación del hielo
Eliminan el hielo una vez formado
Son demasiado costosos para ser incluidos en vuelos comerciales
Los sistemas “de-ice”
El comandante de la aeronave
Puede despegar con hielo formado porque existen sistemas a tal efecto
Nunca ha causado un accidente el despegar con hielo cargado
Siempre puede despegar con hielo, aunque no tenga un sistema anti hielo para eliminarlo posterior al despegue
Es responsable de que la aeronave despegue sin ninguna formación de hielo en la aeronave
Which one of the following elements is not part of a liquid springs damping system in a landing gear?
a. Piston
b. Cylinder with silicon-based fluid
c. Gland
d. Tire
Oleo-pneumatic shock absorbers in landing gears
a. Are obsolete
b. Use oil and gas
c. Use a silicon-based fluid and gas
d. Only use a silicon-based fluid
The main function of torque links is to
a. Ensure that the wheel rotation plane is perpendicular to the surface
b. Provide prop ground clearance
c. Provide directional control in the ground
d. Avoid shimmy
The tail wheel in a conventional landing gear
a. Always can be rotated by the pilot from the cockpit
b. Can be directionally free
c. Can be locked with springs
d. Both b) and c) are correct
Which one from the following is a type of wheel steering system?
a. Banana
b. Banana with movable rod
c. Linear with movable rod
d. All the above are correct
Regulations demand landing gears not to experiment shimmy until
a. 0,5 · Vstall
b. 1,3 · Vstall
c. 100 knots
d. 200 knots
Hop dumpers
a. Are used in the bogies of landing gears
b. Avoid pitching oscillations during braking the airplane
c. Both a) and b) and correct
d. All the above are incorrect
Which of the following is a disadvantage of retractable gear housing in the wing?
a. Creation of additional aerodynamic drag
b. Loss of cargo volume
c. Loss of fuel space
d. There are not disadvantages
The disadvantage of liquid air cooling systems is:
a) They are expensive
b) They are toxic
c) They need a special seal
d) All are correct
The classic cabin temperature control system is carried out by:
a) The Martin Bridge
b) The Control Bridge
c) The Temperature Bridge
d) The Wheatstone Bridge
It is difficult to control the humidity of the air cooling system because:
a) At high altitudes the air is more humid
b) At high altitudes the air is drier
c) It is not difficult, it is very easy
d) It is not possible to control the air humidity of that system
Refering to the air cabin distribution in a transport plane, air velocities must be:
a) Between 10 and 12 m/min
b) Between 6 and 12 m/min
c) Between 5 and 10 m/min
d) Between 3 and 8 m/min
The maximum safe altitude for pilots without oxygen in
a) 15000 ft
b) 20000 ft
c) 25000 ft
d) 21000 ft
According to the regulation of JAR 23 and JAR25, the maximum cabin altitude for passengers is:
a) 7000 ft
b) 6000 ft
c) 10000 ft
d) 8000 ft
Types of cabin pressure control systems:
a) Pneumatic
b) Electro – pneumatic
c) Electronic
In which decompression level does the equalize to ambient pressure occur between 0 and 4 seconds?
a) Rapid decompression
b) Normal decompression
c) Explosive decompression
d) Slow decompression
Which of the next instruments must be on any aircraft obligatorily :
Thermomether
Clock
Altimeter
The organization with legal regulatory authority within the EU is:
EASA
JAA
FAA
The time that a plane is allowed to fly with one engine inoperative is called:
Single-engine range
ICAO
ETOPS
AAJMG
Which one is not an air data instrument:
Machmeter
Vertical speed indicator
Turn indicator
The RAM effect:
Decreases air temperature
Increases air temperature
Can increase or decrease air temperature
Does not affect air temperature
Which of the following thermometers is not usually used in aviation:
Mercury thermometer
Thermistors
Thermocouples
Optical pyrometers
Which is the minimum ETOPS to be allowed to cross the Atlantic:
60 min ETOPS
120 min ETOPS
180 min ETOPS
370 min ETOPS
Which is the instrument arrangement used in the C101:
6 grouping
T grouping
It uses difgial displays
Solar Heating
a) Affect military aircraft cockpit through windscreen and canopy
b) Is a problem in fighters due to the large transparent cockpit to give good all around vision and the high altitude levels for fliying
c) When is combined with kinetic heating and rubber immersion or g-suits, special cooling measurements must be taken
d) All above are correct
Airframe system heat loads such as ECS, Engine, and Hydraulic, Fuel or Electric systems can produce heat.
a) True
b) False
International standard atmosphere changes affects more significatly:
a) Fliying to other countries (for example from a fairly warm area to a tropical area)
b) Fliying local flights
c) Fliying inside of Spain
d) Fliying upside down
In general terms:
a) In low altitudes it is needed cooling
b) In cruise altitudes it is needed heating due to the low temperatures
c) Both are true
d) Both are false
Generally, aircraft flying in high Mach numbers
a) Need cooling
b) Need heating
c) Both are true depending on the season
Some cooling systems are:
a) Air cycle machines
b) Vapor cycle machines
c) The fridge machine
d) A and B are correct
Some heating systems are:
a) Hot air
b) Electrical heater
c) Combustion heater
Select the correct sentence:
a) CAU is the acronym of Cold Air Unit
b) CAU is the acronym of Cool Aircraft Unique
c) CAU is the acronym of Cold And Uncontrolled
d) All above are false
Some fighter jets use this system to change pitch and roll:
Flaps
Slats
Elevons
Spoilers
This plane use “canards” as flight control system:
C295
Eurofighter
C101
Super Puma
Cable operated control system:
Use electric pulses
Need hydraulic fluid to move control surfaces
Pilot must generate all the force to move the control surfaces
All are correct
In a hydraulic system, the PCU (Power Control Units):
Automatically activated when pilots fall asleep
Execute the control surface movement
It cannot be used on commercial planes
Guide the pilot how many degrees must change the attitude
Hydraulic power assist systems:
They can be reversible or irreversible
Cables must be tensed to avoid free-play effects
They can only be used in small planes
“Yoke” as joystick is frequent in:
Gliders
Commercial airplanes
Helicopters
Autogyros
Related to fuel system architecture:
a. Each fuel system is able to supply at least 100% of the fuel flow required
b. Fuel delivered at the same pressure every time
c. Must be fitted with a main pump + backup or emergency pump
d. a and c are true
Where are fuel tanks normally located?
a. Fuselage
b. Wings
c. Vertical Stabilizer
d. a and b are true
What type of tank has problems with leakage and punctions?
Rigid tanks
Flexible tanks
Integral tanks
Related to Flame arrestors:
Prevent the overflow while fuelling
Allow expansion due to temperature changes
Prevent negative differential pressure
Avoid that the fuel vapors possible ignition propagate into the fuel tank
Related to Fuel Booster Pumps:
Prevent aeration
Avoid cavitation
Electrically driven
What are the different types of level sensors?
Float, Zener Diode, Capacitance, Ultrasonic, Optical
Float, Zener Diode, Capacitance, Ultrasonic
Float, Led Diode, Capacitance, Ultrasonic, Optical
Float, Capacitance, Ultrasonic, Optical
What is FOB?
Fuel On Booster
Fuel On Board
Fuel On Body
Related to Fuel Jettison:
Move fuel from the main wing and fuselage tanks to the collector tanks
Supply fuel to the engines
Assist in forcing the fuel under relatively low pressure from certain tanks to other more strategically placed
If an emergency or malfunction after TO happens, it throws a large portion of the fuel to reduce weight rapidly
In a hydraulic system, the redundancy consist in
A) Systems that allow the pilot to act on surfaces in different ways.
B) Include a system that the pilot will activate in an emergency.
C) Redundancy cannot be applied to hydraulic systems.
D) Doubling surface controls or acting elements.
Linear actuators installed on control surfaces are characterized by:
A) Give a rapid response
B) Support reasonably light aerodynamic loads
C) Both A and B are correct
D) Support large aerodynamic loads
Some advantages of electrical power assist (or power boost) systems are:
A) The power is infinite
B) Better results are obtained than with the other methods
C) It is not feasible to apply electrical power to the control of flight surfaces.
D) It does not require the presence of a high pressure hydraulic fluid.
Regarding to the stick force gradient...
A) If it is very high, the pilot will be more precise in the movements of the aircraft.
B) The stick force gradient will maintain the position established by the pilot when he releases the controls.
C) It can be proportional to air dynamic pressure, to flight control displacement or both of the previous.
D) This may be regulated by the pilot according to his preferences.
About the aerodynamic balancing/trim:
A) It is defined as techniques to reduce or cancel the force that is needed to act on control surfaces and obtain certain flight condition.
B) Can be produced with or without tabs.
C) It results useful at high speed and/or large control surface, when manual operation is difficult.
D) All of them are correct
Choose the correct option with regar to "tabs"
A) You can have a direct or indirect control over the tab
B) The tabs always work autonomously, without the pilot being able to do any kind of action on them.
C) Tabs can only be implemented on ailerons.
D) These types of systems are not used in current aviation.
About anti-tab
A) Its main function is to automatically trim the aircraft.
B) It's an indirect tab
C) They increase the necessary force to be applied by the pilot, increasing control.
D) Both B and C are correct
Regarding to Spring Servo Tab...
A) At high speeds they allow direct control over the Tab
B) At low speeds the spring constant decreases the necessary force
D) The spring reduces the necessary force on all kinds of actions
1. Which are the main variations of the four bars mechanism employed in retractable gears?
A. There is no classification, every aircraft employs its own mechanism.
B. Type A, B, C and D.
C. Type 1, 2, 3 and 4.
D. Type A, B y C, but only applied to aircraft’s main gear.
The mechanism that change the angle between the gear leg and the wheel axis when the gear is retracted is known as:
A. Rotator or planing link mechanism.
B. Type A2.
C. Type B.
D. None of the above.
Which are the main characteristics of the rotator or planing link mechanism?
A. Increase of weight.
B. Increase of complexity
C. Increase of maintenance.
D. All the above.
The most employed indicator of the gear placed in down and locked position is:
A. A flashing yellow light for the whole gear.
B. A green light for every mechanism: nose gear/s and main gear/s.
C. A check from the Tower prior to landing.
D. When the red light inside the landing gear control lever stops flashing and remains on.
Standard braking systems mainly work thanks to the conversion of aircraft’s forward motion into:
A. Heat energy.
B. Electric energy.
C. Magnetic energy.
D. Electromagnetic energy.
Braking systems are usually actuated though:
A. Electric power.
B. A steel cable connected to the cockpit.
C. Hydraulic systems.
D. The own aircraft’s weigh once it touches down.
Within a multi-disc braking system there are:
A. Rotor and stator discs.
B. Several discs with their own braking pads.
C. Discs on each side of the wheel.
D. None of the above (A,B & C)
When does the Anti-Skid system act?
A. When the wheel suffers a puncture.
B. Only when landing in snowy conditions.
C. When the windshear is above 20 knots.
D. When a wheel is locked though the braking.
Which of these answers is NOT a classification of landing gears?
Single main
Tricycle
Taildragger
Double wheel
The functions and requirements of the landing gear are:
a) Withstand side loads when landing and taxiing
b) Absorb landing loads and damp vibrations
c) Possess a high drag coefficient
What is the disadvantage of taildragger?
The pilot has poor visibility when landing due to the elevation of the nose
The plane tends to turn over
The nose wheel generates a positive moment (forward)
All answers above are correct
Track (vía) = Distance between the center of the treads of the main gears. If there are more than 2:
It will be considered the two closest from the symmetry plane
It will be considered the two further from the symmetry plane
It will be considered the average of the outer distance
It will be considered the average of the inner distance
The center of gravity of an airplane with tricycle configuration:
It is behind the main gear
It is in front of the main gear
It is indifferent
It depends on the plane
The gear in pods configuration is used in:
Fighter aircraft
Cargo airplanes
Passenger airplanes
That configuration does not exist
The extension and retraction of the landing gear can be:
Electric
Hydraulic
Pneumatic
Factors in landing are:
a) Mass
b) Vertical velocity at touch down
c) Horizontal velocity at touch down
What is the civil regulation that regulates the anti-icing on land?
JAR 23/25
RCAO
Law 5/2005
IG-004
In ground, what areas of the plane should be paid attention for ice?
The tires and wheels.
The windows of the cabin
The pitot tube
The control mobile surfaces, and their union with the fixed surfaces.
Where is hot air taken out in a reactor to inflate the pneumatic boots anti-icing system?
Compressor air
Pitot tube and static socket
Vacuum pump
Of the leading edge.
Where does hot air get out on a propeller airplane to inflate the pneumatic boots anti-icing system?
What advantage does the pneumatic boot have as an anti-ice system?
It is economical and weighs little
It is aerodynamic
It can be optimized by changing its shape
It is resistant to the king
At what time does the antifreeze deactivate to conserve engine power?
Landing
Takeoff and landing
Every 15 minutes, in flight
Taxes
What disadvantage do pneumatic boots have as an anti-icing system?
It is not very aerodynamic and is incompatible with slats
It is very expensive
It is very heavy
It is not effective
Which of these is not an antifreeze system?
Pneumatic boots
thermal antifreeze system
Electro-expulsion anti-icing system
Burning paste system
Por favor espera - en proceso…