Avionica UD4

Question

Which of the next instruments must be on any aircraft obligatorily :

Answer 1

a) Thermomether

Answer 2

c) Altimeter

Answer 3

d) All of the above

Answer 4

d) None of the above

Answer 5

a) Single-engine range

Answer 6

a) Machmeter

Answer 7

b) Vertical speed indicator

Answer 8

c) Altimeter

Answer 9

d) Turn indicator

Answer 10

a) Decreases air temperature

Answer 11

b) Increases air temperature

Answer 12

c) Can increase or decrease air temperature

Answer 13

d) Does not affect air temperature

Answer 14

a) Mercury thermometer

Answer 15

b) Thermistors

Answer 16

c) Thermocouples

Answer 17

d) Optical pyrometer

Answer 18

a) 60 minimum ETOPS

Answer 19

b) 120 min ETOPS

Answer 20

c) 180 min ETOPS

Answer 21

d) 370 min ETOPS

Answer 22

a) 6 grouping

Answer 23

b) T grouping

Answer 24

c) It uses digital displays

Answer 25

d) None of the above

Answer 26

a) Direction of travel and Speed (Air Data System)

Answer 27

b) Weight and balance of the aircraft

Answer 28

c) Engines limitations

Answer 29

d) Aircraft characteristics

Answer 30

a) Depend on a GPS

Answer 31

b) Depend on Radio Navigation aids

Answer 32

c) Compass belong to this kind of Instruments

Answer 33

d) All of the above are fake

Answer 34

a) is a rigid body with one principal moment of inertia much larger than the other two

Answer 35

b) is in high spin around its axis of maximum inertia.

Answer 36

c) is a special kind of compass

Answer 37

d) A and B are both correct

Answer 38

a) Flexibility and Precession

Answer 39

b) Rigidity and Precession

Answer 40

c) Hardness and Precession

Answer 41

d) The only main property is Precession

Answer 42

a) Is the resistance of the spin axis to stop tilting

Answer 43

b) If it increases, the necessary torque to tilt a body decreases

Answer 44

c) Coincides with the angular momentum

Answer 45

d) All of the above are true

Answer 46

a) Spinning and Tilting

Answer 47

b) Spinning and Precessing

Answer 48

c) Spinning, Tilting and Veering

Answer 49

d) Spinning, Tilting and Precessing

Answer 50

a) Their maintenance is expensive

Answer 51

b) Their electrical motor do not work at high altitudes

Answer 52

c) Depend on the aircraft hydraulics

Answer 53

d) Problems at high altitude to get high rotational speeds due to lower density

Answer 54

a) Real wander

Answer 55

b) Apparent wander

Answer 56

c) Transport wander

Answer 57

d) Precessing wander

Answer 58

a) Compass is a radio navigation aid that helps us to know the correct direction

Answer 59

b) In an Air Driven Gyroscope, there is a rotor with holes or ranures to generate movement and suction is made in the box where the gyroscope is placed

Answer 60

c) Real wander, fake wander, apparent wander, transport wander and transport grind wander are all types of gyro wander.

Answer 61

d) All the answers are correct

Answer 62

a) If gyro and compass mark differently, the pilot must obey the compass

Answer 63

b) If gyro and compass mark differently, the pilot must obey the gyro because it is a more modern instrument

Answer 64

c) The compass will be continuously rotating due to the high altitude

Answer 65

d) Under these conditions the only reliable instrument in the plane is the GPS

Answer 66

Provides both aural and visual warnings of an aircraft reaching, or deviating from a preselected altitude

Answer 67

It only provides aural warnings of an aircraft reaching, or deviating from a preselected altitude

Answer 68

It only provides visual warnings of an aircraft reaching, or deviating from a preselected altitude

Answer 69

Provides aural and visual warnings of an aircraft in order to avoid other aircrafts

Answer 70

a) Horizontality by hand with a roulette wheel or enslaving the gyro to the compass

Answer 71

b) Verticality could be fixed with a pendulum mechanism

Answer 72

c) A) and B) are correct

Answer 73

d) Modern gyros do not suffer from topple on vertical component, just suffer drift on the horizontal component

Answer 74

The data is based on the radio altimeter.

Answer 75

As long as the data is based on the radio altimeter and barometric rate of change of height, there is no info about rising ground rising directly ahead of the aircraft.

Answer 76

Rate of change of height is based on temperature variation.

Answer 77

It only works when autopilot is connected.

Answer 78

a) In slave mode, the gyro presents the information by self-correcting it with the compass.

Answer 79

b) In DG / FREE mode, it is necessary to correct the gyro with the compass indications

Answer 80

c) In compass mode, the pointer will be continuously oscillating, the information comes only from the compass

Answer 81

d) All the answers are correct

Answer 82

It determines instantaneous altitude of the aircraft above the terrain.

Answer 83

It makes use of the “frequency modulated ranging”.

Answer 84

It makes use of barometric pressure.

Answer 85

It uses a modulated continuous wave.

Answer 86

a) Turn indicator moves when Roll

Answer 87

b) Turn indicator moves when Yaw

Answer 88

c) Turn indicator moves when Pitch

Answer 89

d) Turn indicator moves when Roll or Yaw but doesn´t with pitch

Answer 90

The associated time difference signal is proportional to the range of the target.

Answer 91

It consist on a discontinuous wave.

Answer 92

The associated wave length signal is proportional to the range of the target.

Answer 93

It consists on a continuous with continuous frequency.

Answer 94

a) Turn co-ordinator is a turn, balance, and attitude indicator

Answer 95

b) In the Inertial Navigation System the velocity and position of the aircraft is obtained by measuring its acceleration and integrating it twice.

Answer 96

c) In Air Driven Gyroscopes, suction is made in the box where the gyroscope is placed

Answer 97

d) Gyros design is looking forward for high rigidity

Answer 98

Radar altimeter.

Answer 99

Pressure altitude.

Answer 100

Position related to ILS glide path.

Answer 101

a) It is particular for each plane because each aircraft creates its own magnetic field, the objective is to eliminate that error.

Answer 102

b) It is impossible to calculate the correction if gyro is working on slave mode

Answer 103

c) All the aircrafts create the same magnetic field. It depends on the altitudes

Answer 104

d) Any answer is correct

Answer 105

MODE 1: Excessive descent rate

Answer 106

MODE 2: Excessive terrain closure rate.

Answer 107

MODE 5: Below glide slope deviation.

Answer 108

MODE 7: Windshear.

Answer 109

a) In equilibrium the two slots are covered equally

Answer 110

b) In turn, one is almost free and the other almost covered. There comes sucking air.

Answer 111

c) Since the flow is not the same, a net force is created in the direction of the closed groove, therefore a moment is created, and the verticality is recovered.

Answer 112

d) All the answers are correct

Answer 113

It is an evolution of the GPWS to reduce controlled flight into terrain (CFIT) accidents.

Answer 114

It introduces additional elements: world terrain database, airstrips database and need of high precision positioning systems.

Answer 115

Some additional functions that are introduced are terrain clearance floor and terrain display system.

Answer 116

All are correct.

Answer 117

a) Red (maximum and minimum values), green (normal operation values), yellow (take off, caution or exceptional values)

Answer 118

b) There is no code

Answer 119

c) Red (maximum and minimum values), green (take off, caution or exceptional values), yellow (normal operation values)

Answer 120

d) Red (normal operation values), green (take off, caution or exceptional values), yellow (maximum and minimum values)

Answer 121

a) The Inductive works between 2.5 and 70 Mpa

Answer 122

b) The Inductive works between 2.5 and 70 pa

Answer 123

c) The Capacitive works between 2.5 and 70 Mpa

Answer 124

d) The Capacitive works between 2.5 and 70 pa

Answer 125

a) The Bourdon tube is used for low pressures

Answer 126

b) The Bourbon tube is used for high pressures

Answer 127

c) Mechanical pressure sensors don´t exist

Answer 128

d) A and B are FALSE

Answer 129

a) EGT means Eshaust Gas Temperature

Answer 130

b) EGT means Elevate Gas Temperature

Answer 131

c) ITT means Internal Turbine Temperature

Answer 132

d) JPT means Jet Pipe Temperature

Answer 133

a) The drag produced by the aircraft

Answer 134

b) The lift produced by the aircraft

Answer 135

c) The speed of the aircraft

Answer 136

d) The engine RPM

Answer 137

a) Systems to increase the efficiency of the propeller operation, and to provide automatic operation of the Constant Speed Unit and feathering mechanisms

Answer 138

b) Systems to reduce the efficiency of the propeller operation, and to provide automatic operation of the Constant Speed Unit and feathering mechanisms

Answer 139

c) Systems to increase the efficiency of the propeller operation, and not to provide automatic operation of the Constant Speed Unit and feathering mechanisms

Answer 140

d) Systems to reduce the efficiency of the propeller operation, and not to provide automatic operation of the Constant Speed Unit and feathering mechanisms

Answer 141

a) Damaged compressor/turbine Blades

Answer 142

b) Uneven temperatura distribution around turbine Blades

Answer 143

c) A and B are TRUE

Answer 144

d) A and B are FALSE

Answer 145

a) Venturi tube

Answer 146

b) Rotanting vane

Answer 147

c) Impeller or integrated type

Answer 148

d) All the above

Answer 149

Mach will remain constant and CAS will be lower, compared to the TAS.

Answer 150

Both IAS and Mach will be lower than the TAS.

Answer 151

CAS will be lower and Mach will be higher, compared to the TAS.

Answer 152

Both IAS and Mach will be higher than the TAS.

Answer 153

The local speed of sound depends on the temperature.

Answer 154

Both CAS and TAS will increase, compared to the Mach number.

Answer 155

Both IAS and TAS will increase, compared to the Mach number.

Answer 156

CAS will decrease and TAS will increase, compared to the Mach number.

Answer 157

A blockage of the pitot line when climbing leads to an overread (the airspeed shown is higher than the actual airspeed).

Answer 158

A blockage of the static line when descending leads to an underread (the airspeed shown is lower than the actual airspeed).

Answer 159

A leak in the pitot line will always lead to an underread.

Answer 160

A leak in the static line may lead to an overread.

Answer 161

ASI displays are limited to showing indicated airspeed.

Answer 162

The red line is the never-exceed airspeed (Vne).

Answer 163

The green arc ends in the maximum flap extended speed (Vfe).

Answer 164

The white arc starts in the maximum structural cruising speed (Vno).

Answer 165

Over-reading (showing an airspeed higher than the actual airspeed) could lead to a stall.

Answer 166

Under-reading (showing an airspeed lower than the actual airspeed) could lead to an overspeed.

Answer 167

In pressurized cabins, where ambient pressure is lower than the one inside the aircraft, a leaking static line leads to an overread.

Answer 168

Blockages of the pitot line may lead to speed variation indications when changing altitude.

Answer 169

The internal mechanics of the IVSI allow it to solve the problems that lag and g-forces create in the VSI.

Answer 170

The calibrated leak of the IVSI prevents the pressure inside the instrument from changing instantaneously.

Answer 171

Answer b) is correct. Also, it uses an accelerometer unit to create a slower differential pressure effect.

Answer 172

The VSI works by a diaphragm which expands or contracts during changes in static pressure.

Answer 173

It uses two cylinders with pistons that respond to nose up and nose down movements, respectively.

Answer 174

While highly reduced, lag is still a problem.

Answer 175

It is affected by acceleration forces (g-forces).

Answer 176

Answer c) is correct and an example would be when turning (turning error).

Answer 177

Transducers to convert physical signals into electronic signals are limited to DADCs.

Answer 178

The CADCs use an I-bar, E-bar mechanism.

Answer 179

The main tubes for pressure measurement in large aircraft may lead to pressure losses and errors.

Answer 180

Capacitive, inductive, piezoelectric or potentiometric are some of the types of transducer that DADCs use.

Answer 181

It doesn't require outter measures, so it can work 24/7 in any weather.

Answer 182

The error is cumulative.

Answer 183

If enough time is measured, error may become considerably great.

Answer 184

All of the above are correct.

Answer 185

Includes 2 springs and a weight.

Answer 186

The acceleration is related to the elongation of the springs.

Answer 187

Nowadays is not usually implemented on aircrafts.

Answer 188

All of the above are correct.

Answer 189

a dichromatic light beam that has been polarized at a single frequency.

Answer 190

a dichromatic light beam that has been polarized at multiple frequencies.

Answer 191

a monochromatic light beam that has been polarized at a single frequency.

Answer 192

a monochromatic light beam that has been polarized at multiple frequencies.

Answer 193

Laser ring.

Answer 194

Mechanical.

Answer 195

Based on gas expansion.

Answer 196

Double effect.

Answer 197

Mandela's effect.

Answer 198

Einstein's effect.

Answer 199

Sagnac's effect.

Answer 200

Mohombi's effect.

Answer 201

Independent Nitrogen Surfaces.

Answer 202

Inertial Notorious Systems.

Answer 203

Inertial Navigation Systems.

Answer 204

Individual Nation Secretary.

Answer 205

a - Move along with the plane.

Answer 206

b - Are enough for the measures (no outter measures required).

Answer 207

c - Only move in 1 axis.

Answer 208

d - a and b are correct.

Answer 209

Optical Fiber Gyroscope, Laser Ring Gyroscope, Mechanical Gyroscope.

Answer 210

Optical Fiber Gyroscope, Mechanical Gyroscope, Laser Ring Gyroscope.

Answer 211

Laser Ring Gyroscope, Optical Fiber Gyroscope, Mechanical Gyroscope.

Answer 212

Laser Ring Gyroscope, Mechanical Gyroscope, Optical Fiber Gyroscope.

Answer 213

a. specialized resolution advisory

Answer 214

b. vertical speed indicator

Answer 215

c. Accoustic warnings

Answer 216

d. all of above are correct

Answer 217

a. knowing the position of every aircraft

Answer 218

b. avoiding collisions

Answer 219

c. getting easier communications

Answer 220

d. all of above are correct

Answer 221

a. orange or yellow box

Answer 222

b. cameras

Answer 223

c. accelerometers

Answer 224

d. A and C are correct

Answer 225

a. propeller effect over fuselaje

Answer 226

b. stall attitude effect

Answer 227

c. loss of elevon control

Answer 228

d. roll of propeller

Answer 229

b. fuselage

Answer 230

c. cockpit

Answer 231

d. A and C are correct

Answer 232

a. Manifold pressure

Answer 233

b. engine pressure ratio

Answer 234

c. fuel and oil pressures

Answer 235

d. all of above are correct

Answer 236

a) Damaged compressor/turbine Blades

Answer 237

b) Uneven temperatura distribution around turbine Blades

Answer 238

c) A and B are TRUE

Answer 239

d) A and B are FALSE

Answer 240

a) Venturi tube

Answer 241

b) Rotanting vane

Answer 242

c) Impeller or integrated type

Answer 243

d) All the above

	Erstellt von Miguel Angel Escudero vor mehr als 4 Jahre

Nächster

Avionica UD4

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