Test
ATP EASA Qatar 3 RED
Preguntas del test (61)
1R 62.6.5.0 (4845)
What is the minimum number of satellites required by a GPS in order to obtain a
three dimensional fix?- A4
- B3
- C5
- D6
2R 62.6.5.0 (4846)
What is the minimum number of satellites required for a Satellite-Assisted
Navigation System (GNSS/GPS) to carry out two dimensional operation?- A3
- B4
- C6
- D5
3R 62.6.5.0 (4852)
Which of the following coordinate systems is used by the GPS receiver to determine position (Latitude, longitude and altitude)?- AWGS 84
- BED 87
- CED 50
- DEUREF 92
4R 71.1.1.0 (4904)
Flight crew members on the flight deck shall keep their safety belt fastened:- Awhile at their station.
- Bonly during take off and landing.
- Conly during take off and landing and whenever necessary by the commander in the interest
of safety. - Dfrom take off to landing.
5R 71.1.2.4 (4946)
A category II precision approach (CAT II) is an approach with :- Aa decision height of at least 100 ft
- Ba decision height of at least 200 ft
- Ca decision height of at least 50 ft
- Dno decision height
6R 71.1.2.4 (4948)
A category I precision approach (CAT I) is an approach which may be carried out with a runway visual range of at least :- A550 m 1800FT
- B350 m
- C800 m
- D500 m
7R 71.1.2.4 (4949)
A category III A precision approach (CAT III A) is an approach which may be carried out with a runway visual range of at least :- A200 m = 700 FT
- B100 m
- C250 m
- D50 m
8R 71.1.2.4 (4951)
A category I precision approach (CAT I) has :- Aa decision height equal to at least 200 ft.
- Ba decision height equal to at least 100 ft.
- Ca decision height equal to at least 50 ft.
- Dno decision height.
9R 71.1.3.1 (4989)
A jet-powered aircraft, flying above the optimum altitude will have :- Areduced range
- Bincreased manoeuvring limits
- Cincreased flight envelope
- Dincreased Mach number stability
10R 71.1.3.3 (5032)
The MNPS (Minimum Navigation Performance Specification) airspace extends vertically between flight levels:- A285 and 420.
- B280 and 400.
- C280 and 390.
- D275 and 400.
11R 71.1.3.3 (5046)
At which levels may Reduced Vertical Separation Minimum (RVSM) be used within
NAT region?- ABetween FL290 and FL410.
- BBetween FL275 and FL400.
- CBetween FL245 and FL410.
- DBelow FL290.
12R 71.2.0.0 (5061)
According to the recommended ""noise abatement take-off and climb procedure A"" established in ICAO, DOC 8168 Volume I part V, Chapter 3, thrust reduction to climb power, has to be done as soon as the aircraft reaches :- A1 500 ft
- B3 000 ft
- C2 000 ft
- D1 000 ft
13R 71.2.2.0 (5070)
The greatest possibility of ice buildup, while flying under icing conditions, occurs
on :- AThe aircraft front areas.
- BThe upper and lower wingsurfaces.
- CThe upper and lower rudder surfaces.
- DOnly the pitot and static probes.
1471.2.2.0 (5082)
During an aircraft de-icing/anti-icing procedure:- Athe anti-icing and de-icing fluids are applied hot.
- Bthe de-icing fluid is applied without heating and the anti-icing fluid is applied hot.
- Cthe anti-icing and de-icing fluids are applied cold.
- Dthe anti-icing fluid is applied without heating and the de-icing fluid is applied HOT
15R 71.2.4.0 (5104)
When setting up a minimum noise climb, the minimum height at which a power reduction shall be allowed is :- A300 m (1000 ft)
- B450 m (1500 ft)
- C150 m (500 ft)
- D600 m (2000 ft)
16R 71.2.4.0 (5108)
According with the ""noise abatement take-off and climb procedure B"", as established in DOC 8168 - Ops Volume 1, part V, aircraft must climb at V2 + 10 to 20 kt, until reaching :- A1 000 ft
- B500 ft
- C1 500 ft
- D3 000 ft
17R 71.2.5.0 (5111)
To use passengers oxygen in case of severe cabin smoke is:- Auseless because the toxical cabin smoke is mixed with the breathing oxygen.
- Bpossible and recommended.
- Cuseless because breathing oxygen would explode under smoke conditions.
- Duseless because the oxygen units do not operate under smoke conditions.
18R 71.2.5.0 (5139)
A class B fire is a fire of:- Aliquid or liquefiable solid
- Bsolid material usually of organic nature
- Celectrical source fire
- Dspecial fire: metal, gas, chemical product
19R 71.2.6.0 (5142)
When flying in straight and level flight at FL 290 for some considerable time a small leak develops in the cabin which causes a slow depressurisation, this can be seen on the cabin rate of climb indicator which will indicate :- Aa rate of climb
- Ba rate of descent of approximately 300 fpm
- Czero
- Da rate of descent dependent upon the cabin differential pressure
20R 71.2.6.0 (5149)
The time of useful consciousness in case of an explosive decompression at an altitude of 40 000 ft is:- A12 seconds.
- B30 seconds.
- C5 minutes.
- D1 minute.
21R 71.2.7.0 (5161)
One of the main characteristics of windshear is that it :- Acan occur at any altitude in both the vertical and horizontal planes
- Boccurs only at a low altitude ( 2000 ft) and never in the vertical plane
- Coccurs only at a low altitude ( 2000 ft) and never in the horizontal plane
- Dcan occur at any altitude and only in the horizontal plane
22R 71.2.7.0 (5162)
Which one of the following magnitudes will be the first to change its value when penetrating a windshear ?- AIndicated airspeed.
- BPitch angle.
- CVertical speed.
- DGroundspeed.
23R 71.2.8.0 (5179)
For the purpose of wake turbulence separation, what is the ICAO minimum radar
separation distance if a heavy aeroplane is following directly behind another heavy
aeroplance on the approach to the same runway ?- A7.4 km (4 NM)
- B9.3 km (5 NM)
- C11.1 km (6 NM)
- D3.7 km (2 NM)
24R
71.2.8.0 (5187)
For purpose of wake turbulence separation, what is the ICAO minimum radar 431 separation distance and minimum time if a medium aeroplane (less than 136000
kg and more than 7000 kg) is following directly behind a heavy aeroplane on the
approach to the same runway ?- A9.3 km (5 NM) and 2 minutes
- B11.1 km (6 NM) and 3 minutes
- C7.4 km (4 NM) and 2 minutes
- D9.3 km (5 NM) and 3 minutes
25R 71.2.8.0 (5188)
For purpose of wake turbulence separation, what is the ICAO minimum radar separation time if a light aeroplance (7000 kg or less) is following a medium aeroplane (less than 136000 kg but more than 7000 kg) on the approach to landing ?- A3 minutes
- B4 minutes
- C5 minutess
- D2 minutes
26R 71.2.8.0 (5190)
For the purpose of wake turbulence separation, what is the minimum separation time that is permitted when a light aircraft is taking off behind a heavy aircraft from an intermediate part of the same runway ?- A3 minutes
- B4 minutes
- C5 minutes
- D2 minutes
27R 71.2.8.0 (5193)
According with DOC 4444 (ICAO), a wake turbulence non-radar separation minima
of 3 minutes shall be applied :- Ato a departing MEDIUM aircraft following a HEAVY aircraft arrival when operating on a
runway with a desplaced landing threshold - Bto LIGHT aircraft taking-off behind a MEDIUM aircraft from an intermediate part
of parallel runway separated by less 760 m - Cto an arriving LIGHT aircraft following a MEDIUM aircraft departure when operating on a
runway with a desplaced landing threshold, if the projected flight paths are expected to cross - DBetween a LIGHT aircraft and a MEDIUM aircraft making a missed approach and the LIGHT
aircraft utilizing an opposite-direction runway for take-off
- Ato a departing MEDIUM aircraft following a HEAVY aircraft arrival when operating on a
28R 71.2.8.0 (5194)
According DOC 4444 (ICAO), a wake turbulence non-radar separation minima of 2 minutes shall be applied to :- ALIGHT aircraft taking-off behind a MEDIUM aircraft from an intermediate part of the same
runway - BLIGHT aircraft landing behind a MEDIUM aircraft
- CMEDIUM aircraft landing behind a HEAVY aircraft
- DMEDIUM aircraft taking-off behind a HEAVY aircraft from an intermediate part of a parallel
separated by less than 760 m
- ALIGHT aircraft taking-off behind a MEDIUM aircraft from an intermediate part of the same
29R 71.2.8.0 (5195)
In accordance with DOC 4444 (ICAO) when a MEDIUM and a LIGHT aircraft are
using the same runway, or parallel runways separated by less than 760 m, (in
approach or departure phases of flight), shall be applied a wake turbulence radar
separation minima of :- A5 NM
- B4 NM
- C3 NM
- D2 NM
30R 71.2.8.0 (5196)
According with DOC 4444 (ICAO), a wake turbulence non-radar separation minima
of 3 minutes shall be applied to :- AMEDIUM aircraft landing behind a HEAVY aircraft
- BLIGHT aircraft landing behind a MEDIUM aircraft
- CLIGHT aircraft taking-off behind a MEDIUM aircraft from a parallel runway separated by
less than 760 m. (using whole runway) - DLIGHT aircraft taking -off behind a MEDIUM aircraft when aircraft are using the same
runway
31R 71.2.9.0 (5200)
In case of a serious threat based on the presence of a bomb on board a pressurized
aircraft and disregarding any fuel considerations:- Ayou dexcend to the flight level corresponding to the indicated cabin altitude or
the safety altitude if higher and take preventive steps by putting yourself in a
landing approach configuration. - Byou climb to the maximum flight level which does not need the use of pressurization.
- Cyou go down to the level corresponding to the indicated cabin altitude and keep the
airplane in a clean configuration until the final approach. - Dyou carry out an emergency descent to reach the safety altitude.
- Ayou dexcend to the flight level corresponding to the indicated cabin altitude or
3271.2.10.0 (5214)
For aeroplanes having a seating capacity of more than 44 passengers, it must be shown by actual demonstration that the maximum seating capacity, including the required number of crew members, can be evacuated from the aeroplane to the ground in :- A90 seconds
- B132 seconds
- C60 seconds
- D120 seconds
33RED 71.2.13.0 (5251)
The maximum validity of a SNOWTAM is :- A24 hours
- B12 hours
- C6 hours
- D3 hours
34R 71.2.13.0 (5255)
In the JAR OPS, a runway is considered damp when:- Aits surface is not dry, and when surface moisture does not give it a shiny appearance.
- Bit is covered with a film of water of less than 3 mm.
- Cit is covered with a film of water of less than 1 mm.
- Dsurface moisture gives it a shiny appearance.
35R 71.2.13.0 (5254)
A braking action of 0.25 and below reported on a SNOWTAM is :- Apoor
- Bunreliable
- Cmedium
- Dgood
36R 81.1.3.1 (5307)
The lift formula is:- AL= CL 1/2 RHO V² S
- BL= W
- CL= CL 2 RHO V² S
- DL= n W
37R 81.1.6.0 (5355)
What will happen in ground effect ?- Athe induced angle of attack and induced drag decreases
- Bthe wing downwash on the tail surfaces increases
- Can increase in strength of the wing tip vortices
- Da significant increase in thrust required
38R 81.1.6.0 (5356)
If an aeroplane flies in the ground effect- Athe lift is increased and the drag is decreased.
- Bthe effective angle of attack is decreased.
- Cthe induced angle of attack is increased.
- Ddrag and lift are reduced.
39R 81.1.6.4 (5357)
Floating due to ground effect during an approach to land will occur :- Awhen the height is less than halve of the length of the wing span above the
surface - Bwhen the height is less than twice the length of the wing span above the surface
- Cwhen a higher than normal angle of attack is used
- Dat a speed approaching the stall
- Awhen the height is less than halve of the length of the wing span above the
40R 81.1.6.4 (5358)
Ground effect has the following influence on the landing distance :- Aincreases.
- Bincreases, only if the landing flaps are fully extended.
- Cdoes not change.
- Ddecreases.
41R 81.1.8.2 (5377)
The stall speed :- Aincreases with an increased weight
- Bdecreases with an increased weight
- Cdoes not depend on weight
- Dincreases with the length of the wingspan
42R 81.1.8.2 (5381)
The following factors increase stall speed :- Aan increase in load factor, a forward c.g. shift, decrease in thrust.
- Ba higher weight, selecting a higher flap setting, a forward c .g. shift.
- Cincreasing bank angle, increasing thrust, slat extension.
- Da lower weight, decreasing bank angle, a smaller flapsetting.
43R 81.1.8.2 (5383)
The stall speed increases, when: (all other factors of importance being constant)
a)
b)
c)
d)- Apulling up from a dive.
- Bweight decreases.
- Cminor altitude changes occur e.g. 0-10.000 ft.
- Dspoilers are selected from OUT to IN.
44R 81.1.8.4 (5393)
Compared with stalling airspeed (VS) in a given configuration, the airspeed at which stick shaker will be triggered is:- Agreater than VS.
- B1.20 VS.
- C1.30 VS.
- D1.12 VS.
45R 81.1.8.5 (5409)
One disadvantage of the swept back wing is it's stalling characteristics. At the
stall :- Atip stall will occur first, which produces a pitch-up moment.
- Bwing root stall will occur first, which produces a rolling moment
- Ctip stall will occur first, which produces a nose-down moment
- Dleading edge stall will occur first, which produces a nose-down moment
46R 81.1.9.0 (5414)
After take-off the slats (when installed) are always retracted later than the flaps. Why ?- ABecause SLATS EXTENDED gives a large decrease in stall speed with relatively
less drag. - BBecause SLATS EXTENDED provides a better view from the cockpit than FLAPS EXTENDED.
- CBecause VMCA with SLATS EXTENDED is more favourable compared to the FLAPS
EXTENDED situation. - DBecause FLAPS EXTENDED gives a large decrease in stall speed with relatively less drag.
- ABecause SLATS EXTENDED gives a large decrease in stall speed with relatively
47R 81.1.10.1 (5448)
When ""spoilers"" are used as speed brakes:- Aat same angle of attack, CD is increased and CL is decreased.
- BCLmax of the polar curve is not affected.
- Cthey do not affect wheel braking action during landing.
- Dat same angle of attack, CL remains unaffected.
48R 81.2.1.1 (5454)
The flight Mach number is 0.8 and the TAS is 400 kts. The speed of sound is:
speed of sound: mach / tas 0.8/400= 500- A500 kts
- B320 kts
- C480 kts
- D600 kts
49R 81.2.2.1 (5465)
Mcrit is the free stream Mach Number at which:- Asomewhere about the airframe Mach 1 is reached locally.
- Bthe critical angle of attack is reached.
- Cshockstall occurs.
- DMach buffet occurs.
50R 81.2.2.2 (5488)
When comparing a rectangular wing and a swept back wing of the same wing area and wing loading, the swept back wing has the advantage of :- AHigher critical Mach number
- BGreater strength
- CIncreased longitudinal stability
- DLower stalling speed
51R 81.2.2.3 (5491)
How does stalling speed (IAS) vary with altitude?- AIt remains constant at lower altitudes but increases at higher altitudes due to compressibility effects.
- BIt increases with increasing altitude, because the density decreases.
- CIt remains constant.
52R 81.2.2.3 (5493)
At higher altitudes, the stall speed (IAS):- Aincreases
- Bdecreases
- Cdecreases until the tropopause
- Dremains the same
53R 81.4.3.5 (5552)
A C.G location beyond the aft limit leads to:- Aa too high pulling stick force during rotation in the take off.
- Ban increasing static longitudinal stability.
- Ca better recovery performance in the spin.
- Dan unacceptable low value of the manoeuvre stability (stick force per g, Fe/g).
5481.5.1.1 (5580)
Rotation about the lateral axis is called :- Apitching.
- Brolling.
- Cslipping.
- Dyawing.
55R 81.5.2.4 (5583)
The centre of gravity moving aft will:- Aincrease the elevator up effectiveness.
- Bdecrease the elevator up effectiveness.
- Cnot affect the elevator up or down effectiveness.
- Dincrease or decrease the elevator up effectiveness, depending on wing location.
56R 81.5.5.0 (5599)
Which moments or motions interact in a dutch roll?
a)
b)
c)
d)- ARolling and yawing.
- BPitching and rolling.
- CPitching and adverse yaw.
- DPitching and yawing.
57R 81.6.3.2 (5643)
What wing shape or wing characteristic is the least sensitive to turbulence :- Aswept wings
- Bwinglets
- Cstraight wings
- Dwing dihedral
58R 81.8.1.5 (5672)
A jet aeroplane is rolled into a turn, while maintaining airspeed and holding
altitude. In such a case, the pilot has to:- Aincrease thrust and angle of attack.
- Bincrease thrust and keep angle of attack unchanged.
- Cincrease thrust and decrease angle of attack.
- Dincrease angle of attack and keep thrust unchanged.
59R 81.8.1.5 (5676)
The bank angle in a rate-one turn depends on:- ATAS.
- Bweight.
- Cload factor
- Dwind.
60R 81.8.2.10 (5683)
Why is VMCG determined with the nosewheel steering disconnected?- ABecause the value of VMCG must also be applicable on wet and/or slippery
runways. - BBecause the nosewheel steering could become inoperative after an engine has failed.
- CBecause it must be possible to abort the take-off even after the nosewheel has already
been lifted off the ground. - DBecause nosewheel steering has no effect on the value of VMCG.
- ABecause the value of VMCG must also be applicable on wet and/or slippery
61R
How does VMCG change with increasing field elevation and temperature?- Adecreases, because VMCG is expressed in IAS and the IAS decreases with TAS
constant and decreasing density - Bincreases, because at a lower density a larger IAS is necessary to generate the required
rudder force - Cincreases, because VMCG is related to V1 and VR and those speeds increase if the density
decreases - D1998-10-05 0:00
- Adecreases, because VMCG is expressed in IAS and the IAS decreases with TAS
Información
- Descripción
- Aviation Interview Test sobre ATP EASA Qatar 3 RED, creado por mmm mmm el 23/05/2018.
- Autor
- mmm mmm
- Idioma
- Español
- Visitas
- 294
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