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Question ID: 627237

The following information can be displayed on a Primary Flight Display (PFD):


The combination that regroups all of the correct statements is:

Select 4 options from the below
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Explanation

The primary flying display tells you the important stuff you will need to know with regards to flying the aircraft. 1, 2, 3 and 4 are all clearly relevant. Ground speed is only really relevant for time predictions and navigation purposes.

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Question ID: 626190

In which of the following situations during initial take-off roll must a take-off warning of a transport aircraft provide an aural warning?


1) When the longitudinal trim is not within the approved range for a take-off.

2) When the take-off thrust is not fully applied.

3) When one engine fails.

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A

1), 3)

B

1)

C

1), 2), 3)

D

2)

Explanation

1 - Yes. If not in the approved range you may not have enough elevator authority to rotate the aircraft.
2 - No. You don't need to take off with maximum thrust.
3. No. You'll see a warning light, but hopefully you'd notice this anyway.
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Question ID: 622649

The lateral guidance modes of an autopilot system are:

Select 2 options from the below
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Explanation

Autopilot functions can be divided into two different categories:

• Basic modes – Stabilizing the aircraft around its center of gravity. The basic functions of the autopilot are provided by the inner loops.
• Guidance functions – Autopilot functions that control the path of the aircraft. The guidance functions are provided by the outer loops.

Autopilot basic stabilization modes:
• Pitch angle hold (attitude).
• Bank angle hold (attitude).
• Wings level hold.
• Vertical speed hold.

Autopilot guidance modes:
• Lateral Guidance – Track hold, LOC, FMS LNAV, heading hold.
• Vertical guidance – IAS hold, altitude hold, FMS VNAV, VOR hold, GS.
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Question ID: 129549

A stable platform inertial navigation system uses:

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A

two separate platforms with two accelerometers.

B

two separate platforms with two gyroscopes.

C

a single platform with two gyroscopes.

D

a single platform with two accelerometers.

Explanation

A 'Stabilised' platform INS system, is the old type system from the '70s. It could have 2 or 3 accelerometers, but if you remember that it always needs 3 gyros to remain aligned, then the question becomes easy. One gyro stabilised platform with 3 gyros and at least 2 accelerometers, one for E\W accel and one for N\S accel.

Explanation Provided by Peter Begley

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Question ID: 129548

The core purpose of an EFIS is to

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A

display engine instrument system schematics.

B

depict electronically an ADI and HSI.

C

display airspeed and vertical speed.

D

display instrument information and error messages.

Explanation

An EFIS Electronic Flight Instrument System is the modern way of showing information from the basic flight instruments including compass, on 2 electronic screens, the PFD Primary Flight Display, and the ND Navigational Display. The PFD includes the display of, Airspeed, Attitude, Altitude, Turn and slip, Heading and Vertical Speed, as well as FD Flight Director bars and the FMA Flight Mode Annunciator. The ND can display a full compass rose EHSI or an expanded version and is used to display information such as Localiser, VOR Radials, Weather, Terrain, TCAS and Routes. It can also be used during route planning via the CDU and FMC.

Explanation Provided by Peter Begley

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Question ID: 129543

Considering the properties of a magnet, which statements are correct/incorrect?

1. North and South poles may exist in isolation.

2. Magnetic flux density is greatest at the extremities of a magnet.

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A

1. Correct, 2. Correct

B

1. Incorrect, 2. Incorrect

C

1. Correct, 2. Incorrect

D

1. Incorrect, 2. Correct

Explanation

Unlike Electrical Charge which can be positive or negative completely, a magnet, or pole piece, has to have a North and a South end. Snap a magnet in two, and you'll get two magnets, each with a North and South end. So you cannot have an isolated North or South pole.
Since the lines of flux are closer together at the poles, then the statement about strength at the extremities is correct.

Explanation Provided by Peter Begley

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Question ID: 129542

Vibration sensors may use

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A

Tachometer and piezoelectric crystals.

B

Tachometer only.

C

Piezoelectric crystals only.

D

Piezoelectric crystals or magnets.

Explanation

A vibration sensor on an engine either uses the old system of a magnet in a coil between two springs, or a piezoelectric crystal and a proof mass, which compresses the crystal with vibration. Either system generates small amounts of electrical energy to allow the amplitude of the vibration frequency to be measured. There are no units for vibration.

Explanation Provided by Peter Begley

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Question ID: 129540

Which of the following describe a bar magnet?

1. Opposite poles attract
2. The North pole of a freely suspended bar magnet would turn towards North, which is a South magnetic pole
3. Magnetic force is strongest in the centre of the magnet
4. Magnetic force is strongest a short way in from the poles of the magnet
5. Opposite poles repel
6. A freely suspended magnet would dip down towards the near pole

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A

3, 4, 5, 6

B

1, 2, 4, 6

C

1, 3, 4, 5

D

2, 4, 5, 6

Explanation

The hardest part of this question is the fact that the Earth's North Pole is actually a South Magnetic Pole. This is why magnet North Poles are attracted to it.
However, if you know that 5. is wrong (opposite poles don't repel) then only answer D can be correct.

Explanation Provided by Peter Begley

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Question ID: 121103

According to the range of pressure to be measured (low, medium, high), different types of pressure sensors are used



Classify the following sensors by order of increasing pressure for which they are suitable



1 bellows type

2 Bourdon tube type

3 aneroid capsule type

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A

2, 1, 3.

B

3, 1, 2.

C

3, 2, 1.

D

1, 2, 3.

Explanation

Aneroid
Bellows
Bourdon
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Question ID: 120331

Mach meter readings are subject to

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A

temperature error.

B

setting error.

C

position error.

D

density error.

Explanation

Mach meter take information from Pitot tube and the static port. Since pitot tube and static port is exposed to the air, they can experience a drop in pressure due to aerodynamic turbulence. This error is called position error.

Explanation Provided by Sondre Olsen

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Question ID: 106762

The following information can be displayed on the Navigation Display (ND) of a modern EFIS-equipped jet transport aircraft

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A

ARC or MAP (with current heading up), ROSE (covering 45 degrees on either side of the instantaneous track) and PLAN (map orientated to Magnetic North)

B

ARC or MAP (covering 45 degrees on either side of the instantaneous track), ROSE (with current heading up) and PLAN (map orientated to Magnetic North)

C

ARC or MAP (with current heading up), ROSE (covering 45 degrees on either side of the instantaneous track) and PLAN (map orientated to True North)

D

ARC or MAP (covering 45 degrees on either side of the instantaneous track), ROSE (with current heading up) and PLAN (map orientated to True North)

Explanation

ARC is the Airbus Expanded Nav mode so must be 45° either side of the nose. MAP is Boeing and can be full rose or 45° Plan mode is normally always full rose and True North up

Explanation Provided by Peter Begley

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Question ID: 106755

According to AMC 25.11 concerning the electronic display systems, when exceeding the limits of the flight envelope, the colour accepted to alert the flight crew is

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A

red.

B

magenta.

C

amber.

D

yellow.

Explanation

As you are exceeding a limit, a warning message is created. The colour associated with a warning is red.

Explanation Provided by Kush Gola

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Question ID: 106723

The inputs to the GPWS (Ground Proximity Warning System), are

Select 5 options from the below
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Explanation

Item 1 includes Vertical Speed which is required for Mode 1 Excessive Vertical Speed. The Radio Altimeter is used a lot when the aircraft is below 2450 feet. The Undercarriage and Flaps are part of Mode 4 Aircraft not in Landing Configuration (and partially Mode 2) and the NAV/GS is used in Mode 5 Deviation Below Glideslope. Also, don't forget that the ADC feeds barometric altitude into the GPWS for Mode 3, Loss of Altitude after Take Off or Go Around.

 

Explanation Provided by Peter Begley

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Question ID: 106695

The stall warning system of a large transport airplane includes

Select 3 options from the below
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Explanation

An aeroplane can only stall when its angle of attack exceeds a certain value, depending on the aeroplane. Therefore, it needs an angle attack sensor. The slats and flaps affect this angle, so this also needs to be known. A computer is also needed to process these inputs and send a signal to activate the warning system.

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Question ID: 106606

The role of the FMS (Flight Management System) is to

Select 3 options from the below
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Explanation

The FMS contains two databases only - the navigation database and the performance database. The navigation database contains SIDs and STARs and aids with flying between waypoints (3). This means the pilot can pay less attention to navigation and more attention on flying the aircraft, thus reducing the pilot's workload (4). The performance database allows the FMS to determine the most optimum/economical flight level for best fuel efficient (5).

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Question ID: 106510

When engaged in the FMS lateral navigation mode (LNAV) the autopilot uses

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A

the FMS computation of the aircraft position and the FMS active (TO) waypoint bearing.

B

the FMS active (TO) waypoint coordinates.

C

the path angle command computed by the FMS.

D

the roll or heading command computed by the FMS.

Explanation

LNAV mode will guide the aircraft along the lateral by using roll and heading commands.
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Question ID: 106508

The computer of the autopilot system uses, among others, input signals from the
1) ADC.
2) attitude reference system.
3) ILS receiver.
4) mode control panel.The combination that regroups all of the correct statements is

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A

1, 2, 3, 4

B

2, 3, 4

C

1, 2, 3

D

1, 4

Explanation

All for are essential for the autopilot to function properly.
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Question ID: 106505

The correction of the control surface deflection made by the automatic pilot calculator in order to stabilize the longitudinal attitude will be all the more significant as the
1) difference between the reference attitude and the instantaneous attitude is high.
2) rate of change of the difference between the reference attitude and the instantaneous attitude is high.
3) temperature is low.
4) pressure altitude is high.The combination re-grouping all the correct state

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A

2, 3, 4

B

1, 2, 3

C

1, 2

D

1, 2, 3, 4

Explanation

Work through these one by one - which of these would require a larger control surface deflection.
1 - Yes - If your current pitch is far from your desired pitch, you will need to apply a bigger correction than if you're almost at your desired pitch.
2 - Yes - If your pitch is increasing at 1° per second and you want to be pitching at 5° per second, the autopilot will need to apply a large correction.
3 and 4 - No -These aren't accounted for by the autopilot. Although temperature and altitude affect the force for a given control surface deflection, it will use 1 and 2 to determine if the deflection is sufficient and adjust accordingly.
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Question ID: 106496

Among the following functions of an autopilot, those related to the aeroplane stabilization are
1) pitch attitude holding.
2) indicated airspeed or Mach number holding.
3) horizontal wing holding.
4) displayed heading or inertial track holding.
5) VOR axis tracking.The combination regrouping all the correct statements is

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A

1, 3

B

1, 2, 4

C

1, 3, 4

D

1, 3, 4, 5

Explanation

The Inner Loop of the autopilot (which is a closed loop) is responsible for aircraft stabilisation in pitch and roll. Simply it is a pitch attitude holder and wing leveller. When you select flight path modes on the MCP (Outer Loops) such as HDG, ALT, LNAV etc, the Inner loop is influenced to do more than just stabilisation, but it is still on.

Explanation Provided by Peter Begley

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Question ID: 106255

The data outputs from the ADC (Air Data Computer) are
1) barometric altitude.
2) Mach number.
3) CAS.
4) TAS.
5) SAT.The combination that regroups all of the correct statements is

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A

2, 3, 4

B

1, 4

C

1, 2, 3, 4, 5

D

1, 3, 5

Explanation

The data outputs from the ADC are
1) Baro altitude.
2) Mach number.
3) CAS.
4) TAS.
5) SAT.
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