Free sample questions.

Corrections, explanations and corrections...

Have fun answering the questions below. With an account, your answers are saved in your progress report. Unlimited sessions to repeat as many times as needed and get your progress graph into the green. Progress and achieve your goals.

021 - Airframe and system > Pneumatics - Pressurisation and Air ConditioningIf the pressure in the cabin tends to become lower than the outside ambient air pressure the:
Negative pressure relief valve will open. Air cycle machine will stop. Negative pressure relief valve will close Outflow valve open completely.Explanation All pressurised aircraft have negative pressure relief valves that will open and enable cabin PRESSURE to increase at the same rate as ambient pressure should the cabin/ambient differential try to go negative.
Aircraft are structurally designed for a positive differential (cabin pressure higher than ambient).
Under normal operation the pressure controller can cope but in emergencies the negative pressure relief valves will function.

062 - Radionavigation > Basic Radio Propagation TheoryQuadrantal errors associated with aircraft Automatic Direction Finding (ADF) equipment are caused by:
Skywave/groundwave contamination. Signal bending caused by electrical interference from aircraft wiring. Misalignment of the loop aerial. Signal bending by the aircraft metallic surfaces. Explanation Admin :
QUADRANTAL ERROR:
NDB signals may reach the receiver aerial directly and also after being reflected by the aircraft body. Due to electrical circuits and current flowing through them there is an electromagnetic field surrounding the aircraft, in general alignment with its body.
This causes the incident radio waves to deflect near the ADF receiver aerial. The mixed signal affects the null position and the bearing indicated may be with large error.

The maximum effect is at quadrantal relative bearings:
045°, 135°, 225° and 315° relative to heading.

Modern installations are compensated for this error.

022 - Instrumentation > Sensors and InstrumentsThe measurement of the turbine temperature or of the TGT (Turbine Gas Temperature) is carried out at the:
High pressure chamber intake. Combustion chamber outlet. Combustion chamber intake. High pressure turbine outlet. Explanation Admin :
A thermocouple type thermometer is located between the HP turbine and LP turbine allowing the measurement of the turbine temperature.

061 - General Navigation > ChartsWhat is the time required to travel along the parallel of latitude 60°N between meridians 010°E and 030°W at a groundspeed of 480 kt?
1 h 45. 2 h 30. 1 h 15. 5 h 00.Explanation Admin :
Distance in longitude = 40°
At the equator, 1° = 60 NM

Distance in NM = 40° x 60 NM x cos latitude
Distance = 40° x 60 NM x cos 60°
Distance = 1200 NM

1200 / 480 kt = 2 h 30.

062 - Radionavigation > Global Navigation Satellite SystemsWhat is the minimum number of satellites required by a GPS in order to obtain a three dimensional fix?
4. 3. 24. 5.Explanation Admin :
To carry out three dimensional (3D) operation: 4 satellites.
To carry out two dimensional (2D) operation: 3 satellites.

021 - Airframe and system > System Design, Loads, Stresses, MaintenanceWhich of these statements about structural design principles are correct or incorrect?
1 - In structural design, FAIL SAFE implies the structure will never fail.
2 - In structural design, SAFE LIFE implies the structure will never fail during a declared time period or number of cycles.
I is correct, II is correct. I is incorrect, II is incorrect. I is correct, II is incorrect. I is incorrect, II is correct.Explanation In a 'fail safe' construction the components were designed in a way that the loads are shared among adjacent components.

If one component fails the adjacent components take-up the load for a limited period of time, enough to allow the detection at the next periodic inspection.

The philosophy of 'fail safe' is to anticipate a possible failure, with a minimum of harm.
In a 'safe life' construction, the components are given for a time period and/or number of cycles (X landings, X engine starts) and must be removed from service when the appropriate criteria are met.

The 'safe life' design technique is employed in critical systems which are either very difficult to repair or may cause severe damage to life and property.

Statement II is incorrect because you can not guarantee that a part will definitely not (will never ) fail within its calculated number of cycles or its period.

031 - Mass and Balance > Purpose of Mass and Balance ConsiderationsThe centre of gravity of an aircraft :
Viewed at last exams May only be moved if permitted by the regulating authority and endorsed in the aircraft's certificate of airworthiness. Must be maintained in a fixed position by careful distribution of the load. Can be allowed to move between defined limits. Is in a fixed position and is unaffected by aircraft loading.Explanation Centre of Gravity (CG) is that point through which the force of gravity is said to act on a mass and always acts parallel to the gravity vector.

010 - Air Law > Personnel licencingWhat are the limitations for a pilot licence holder aged 60 to 64, engaged in commercial air transportation operation?
He shall not act as a pilot of an aircraft engaged in commercial air transport. He shall not act as captain. The other pilot must be aged under 50 years. He must act as a member of multi-pilot crew. Explanation Regulation (EU) No 1178/2011
Aircrew Regulation

FCL.065 Curtailment of privileges of licence holders aged 60 years or more in commercial air transport

(a) Age 60-64. Aeroplanes and helicopters. The holder of a pilot licence who has attained the age of 60 years shall not act as a pilot of an aircraft engaged in commercial air transport except:

(1) as a member of a multi-pilot crew; and

(2) provided that such a holder is the only pilot in the flight crew who has attained the age of 60 years.

(b) Age 65. The holder of a pilot licence who has attained the age of 65 years shall not act as a pilot of an aircraft engaged in commercial air transport.

031 - Mass and Balance > Purpose of Mass and Balance ConsiderationsLoads must be adequately secured in order to:
Prevent excessive 'g'-loading during the landing flare. Avoid any CG movement during flight. Allow steep turns. Avoid unplanned CG movement and aircraft damage. Explanation CG will move during the flight, this change of CG can be planned. Loads must be adequately secured in order to avoid unplanned CG movement.

Tragic example:
On August 7, 1997, Fine Air flight 101, a Cargo DC-8-61F registration N27UA, en route from Miami to Santo Domingo, in the Dominican Republic, suffered sudden movement of cargo materials in the aft cargo hold while on take off. The aircraft's nose rose steeply due to the sudden uneven weight distribution caused by shifting boxes of denim material that had not been securely fastened.

The pilots, departing out of the runway 27R attempted to recover but the aircraft stalled and crashed onto a field adjacent the Miami City Rail Yard less than a mile from the airport.

The only deaths were those of the three aircrew members, a company security guard on the flight, and a man in a parking.

022 - Instrumentation > Alerting Systems, Proximity SystemsConsidering an airspeed indicator, a second stripped needle, if installed, indicates:
Never-exceed speed (VNE) or maximum operating speed (VMO), depending on which is the higher. Maximum operating speed (VMO). Never-exceed speed (VNE) or maximum operating speed (VMO), depending on which is the lowest. Never-exceed speed (VNE).Explanation

022 - Instrumentation > Magnetism - Direct Reading Compass and Flux ValveIn the northern hemisphere, during a take-off run in a westerly direction, a direct reading magnetic compass indicates:
An apparent turn to approximately the heading 255°. No apparent turn. An apparent turn to the south. An apparent turn to the north. Explanation Acceleration/Deceleration Errors are false compass indications of a swing to the North or South during speed changes of the airplane. This error is most pronounced when flying on a heading of East or West and decreases when flying closer to a North or South heading. In a direct North or South heading this error does not occur.
In the Northern Hemisphere, the compass swings towards the North during acceleration and towards the South during deceleration. In the Southern Hemisphere this error occurs the other way round. When the speed stabilises, the error disappears.

LEARN THIS FOR NORTHERN HEMISPHERE: ANDS !
A cceleration gives apparent turn to N orth.
D eceleration gives apparent turn to S outh.

070 - Operational Procedures > Special and HazardsIf smoke appears in the air conditioning, the first action to take is to:
Begin an emergency descent. Cut off all air conditioning units. Determine which system is causing the smoke. Put on the mask and goggles. Explanation Admin :

061 - General Navigation > Basics Of NavigationThe circumference of the earth is approximately:
21600 NM. 43200 NM. 5400 NM. 10800 NM.Explanation Admin :
360° x 60 NM = 21600 NM.

050 - Meteorology > ClimatologyFrom which direction do the trade winds blow, in the southern hemisphere?
N NE SW SE Explanation Admin :

034 - Performance H > GeneralAssuming an engine failure has occurred during take-off, a Performance Class 1 helicopter which plans a turn in the climb of more than 15° must be capable of clearing vertical obstructions by an extra:
35 ft. 3 m. There is no additional margin to apply. 7R.Explanation CAT.POL.H.205 Take-off
...

b) The take-off mass shall be such that:
1) it is possible to reject the take-off and land on the FATO in case of the critical engine failure being recognised at or before the take-off decision point (TDP);
2) the rejected take-off distance required (RTODRH) does not exceed the rejected take-off distance available (RTODAH); and
3) the TODRH does not exceed the take-off distance available (TODAH).
4) Notwithstanding (b)(3), the TODRH may exceed the TODAH if the helicopter, with the critical engine failure recognised at TDP can, when continuing the take-off, clear all obstacles to the end of the TODRH by a vertical margin of not less than 10,7 m (35 ft) .

CAT.POL.H.210 Take-off flight path
...

a) From the end of the TODRH with the critical engine failure recognised at the TDP:
1) The take-off mass shall be such that the take-off flight path provides a vertical clearance, above all obstacles located in the climb path, of not less than 10,7 m (35 ft) for operations under VFR and 10,7 m (35 ft) + 0,01 x distance DR for operations under IFR. Only obstacles as specified in CAT.POL.H.110 have to be considered.

2) Where a change of direction of more than 15° is made, adequate allowance shall be made for the effect of bank angle on the ability to comply with the obstacle clearance requirements. This turn is not to be initiated before reaching a height of 61 m (200 ft) above the take-off surface unless it is part of an approved procedure in the AFM.

081 - Principles of Flight > Subsonic AerodynamicsStatic pressure is acts:
Only in the direction of the total pressure. In all directions. Only perpendicular to the direction of the flow. Only in direction of the flow.Explanation Static pressure is atmospheric pressure measured at a point where there is no external disturbance, and the flow of air over the surface is perfectly smooth.

022 - Instrumentation > Flight Management System (FMS and FMGS)Concerning the FMS (Flight Management System), entering a cost index of zero results in:
Maximum range airspeed. Minimum range airspeed. Minimum airspeed. Maximum cruising airspeed.Explanation Cost Index is the ratio of time-related costs (crew salaries, maintenance, etc.) to fuel cost as one of the independent variables in the speed schedule computation:
Cost Index (CI) = flight time-related cost/fuel cost

The cost index allows airlines to weight time and fuel costs based on their daily operations.
A high 'Cost Index' will result in a high cruising speed.
A cost index of zero results in minimum trip fuel (you will fly at 'maximum range airspeed').

Cost index is about fuel cost, not quantity.

Cost index is a made up figure, which when input into the FMC is used to calculate ECON speed. The higher the cost index number, the faster the aircraft flies. Basically, the company decides on the cost of keeping the aircraft in the air, and includes all sorts of costs such as crew, aircraft operating costs, fuel etc... They then decide whether they want the aircraft to fly faster or slower and adjust the cost index as needed.

081 - Principles of Flight > Subsonic AerodynamicsIn a stationary subsonic streamline flow pattern, if the streamlines converge, in this part of the pattern, the static pressure (I) will ... and the velocity (II) will ... :
Viewed at last exams (I) increase, (II) decrease. (I) decrease, (II) decrease. (I) increase, (II) increase. (I) decrease, (II) increase. Explanation

Static pressure decreases in a venturi, and airflow speed increases.

062 - Radionavigation > RadarWhen Mode C is selected on the aircraft SSR transponder the additional information transmitted is:
Height based on QFE. Altitude based on regional QNH. Pressure-altitude based on 1013.25 hPa. Aircraft height based on sub-scale setting.Explanation Admin :
Mode C sends the aircraft's pressure altitude, provided by the altitude encoder.

010 - Air Law > Procedures for Air Navigation Services (PANS OPS)A circling approach is:
A visual manoeuvre to be conducted only in IMC. A flight manoeuvre to be performed only under radar vectoring. A visual flight manoeuvre keeping the runway in sight. A contact flight manoeuvre.Explanation DOC 8168, chapter 7 VISUAL MANOEUVRING (CIRCLING) AREA:
7.1 PURPOSE
...
7.2 VISUAL FLIGHT MANOEUVRE
7.2.1 A circling approach is a visual flight manoeuvre. Each circling situation is different because of variables such as runway layout, final approach track, wind velocity and meteorological conditions.
Therefore, there can be no single procedure designed that will cater for conducting a circling approach in every situation.

7.2.2 After initial visual contact, the basic assumption is that the runway environment should be kept in sight while at minimum descent altitude/height (MDA/H) for circling. The runway environment includes features such as the runway threshold or approach lighting aids or other markings identifiable with the runway.