ATPL Objective Examination Study Guide

ATPL Examination Overview and General Instructions

This examination document pertains to ATPL Questions and has a total duration of 60 minutes. The primary instruction for candidates is to answer all 30 objective questions provided on the designated answer sheet. A passing mark for this subject is established as greater than or equal to $75\%$. Candidates are specifically cautioned not to smear or write directly on the question paper during the examination process.

Aerodynamics and Principles of Flight

When increasing the bank angle of an aeroplane while speed brakes are extended, the roll control spoilers exhibit specific behaviors. The possible movements for these spoilers under such conditions include: (a) moving on the down-going wing only, (b) moving on the up-going wing only, (c) moving up on the down-going wing and moving down on the up-going wing, or (d) moving down on the down-going wing and moving up on the up-going wing.

Aerodynamic forces acting on an aerofoil section involve specific relationships between lift, drag, and the angle of attack. The examination presents four options for these relationships: (a) lift and drag increase linearly with an increase in angle of attack, (b) lift and drag act perpendicular to each other only at one specific angle of attack, (c) lift and drag increase exponentially with an increase in angle of attack, or (d) lift increases linearly and drag increases exponentially with an increase in angle of attack.

The coefficient of lift for an aircraft can be modified through various mechanical or physical changes. Specifically, it can be increased through flap extension or alternatively by (a) increasing the True Airspeed ($TAS$), (b) increasing the Calibrated Airspeed ($CAS$), (c) increasing the angle of attack, or (d) decreasing the 'nose-up' elevator trim setting.

Swept wing aeroplanes are known to exhibit a specific pitch-up behavior at the stall. This phenomenon is attributed to factors such as (a) negative camber at the wing root, (b) separated airflow at the wing root, (c) spanwise flow from the root to the tip on the top surface of the wing causing the tip to stall before the root, or (d) the rearward movement of the Center of Pressure ($CP$).

The optimum angle of attack for an aerofoil represents a critical performance metric. It is defined as either (a) the angle of attack required to maintain level flight, (b) the angle of attack at which the Centre of Pressure is located at the quarter chord position, (c) the angle of attack at which the maximum lift/drag ratio ($L/D$) is achieved, or (d) the angle of attack at which the aerofoil generates maximum lift.

When a pilot maintains an aeroplane in straight and level flight at a constant Indicated Airspeed ($IAS$), the deployment of flaps affects the induced drag. The results of flap deployment include (a) the induced drag increases, (b) the induced drag decreases, (c) the induced drag increases or decreases depending on the specific aircraft, or (d) the induced drag is not significantly affected.

A high aspect ratio wing possesses distinct structural and aerodynamic characteristics. These include (a) producing no induced drag, (b) having a long chord and a short span, (c) suffering greater wing flexing than a low aspect ratio wing, or (d) producing increased spanwise flow from the root to the tip on the upper surface.

Air Law, Regulations, and Operational Procedures

An applicant for an Airline Transport Pilot License (Aeroplane), or $ATPL(A)$, must demonstrate specific piloting abilities. These requirements include the ability to pilot (a) training aircraft, (b) multi-crew aircraft equipped with a Flight Engineer, (c) multi-crew aircraft under Instrument Flight Rules ($IFR$), or (d) night flights carrying passengers.

Operational medical requirements change for pilots based on age. For a holder of an $ATPL(A)$ who is over $60$ years of age and engaged in multi-pilot commercial air transport, the frequency of medical examinations is adjusted. The possibilities provided are: (a) the 12-month period reduces to $6$ months, (b) the 24-month period reduces to $12$ months, (c) the 6-month period reduces to $3$ months, or (d) the 9-month period reduces to $3$ months.

Reduced Vertical Separation Minimum ($RVSM$) regulations mandate that certain equipment must be operative for flight. This equipment includes 2 Air Data References ($ADR$) and 2 Display Management Computers ($DMC$), 1 Flight Control Unit ($FCU$) channel, and 2 Primary Flight Displays ($PFD$). One item that is listed as an exception (not strictly required by $RVSM$ regulations according to the options) is Auto-Thrust.

Regulations regarding alcohol consumption for crew members are strictly enforced. Alcohol must not be consumed by a crew while on duty or during a specific timeframe preceding the reporting time for flight duty or standby duty. This timeframe is either (a) $8$ hours, (b) $10$ hours, (c) $12$ hours, or (d) $16$ hours.

In the event of a hijack situation, pilots are required to select a specific transponder code to signify the emergency to Air Traffic Control. The codes listed are (a) $7700$, (b) $7600$, (c) $7400$, or (d) $7500$.

International Civil Aviation Organization ($ICAO$) standard procedures define maximum holding speeds for aircraft. Up to an altitude of $14000\,ft$ under normal conditions, the maximum speed is (a) $230\,kt$, (b) $220\,kt$, (c) $240\,kt$, or (d) $255\,kt$.

The Certificate of Airworthiness is a critical document that contains specific information about an aircraft. However, certain information is not included in this document, which could be (a) Nationality, (b) Categories and/or Operation, (c) Weight, or (d) Manufacturer's designation of aircraft.

Wake turbulence separation is required between aircraft during takeoff based on their weight categories. For a medium aircraft taking off behind a heavy aircraft from an intermediate part of the same runway, the required separation time is (a) $2$ minutes, (b) $3$ minutes, (c) $1$ minute, or (d) $5$ minutes.

Meteorology and Atmospheric Conditions

Clear Air Turbulence ($CAT$) is a significant meteorological hazard that can be expected in specific locations. These locations include: (a) near a jet stream and in Stratus cloud, (b) with an upper level trough and in a col, (c) near a jet stream and around and above a $CB$ (Cumulonimbus) cloud, or (d) near a jet stream and with an anabatic wind.

The formation of a thunderstorm requires a specific set of meteorological conditions. These requirements are (a) a stratocumulus cloud with sufficient moisture, (b) a cumulus cloud with sufficient moisture associated with an inversion, (c) an adequate supply of moisture, instability, and a lifting action, or (d) water vapour and high pressure.

Thermodynamics in the atmosphere includes the process of change of state from a gas to a liquid. This process is defined as either (a) evaporation in which latent heat is absorbed, (b) evaporation in which latent heat is released, (c) condensation in which latent heat is absorbed, or (d) condensation in which latent heat is released.

Atmospheric pressure levels correlate to specific flight levels ($FL$) in the standard atmosphere. A pressure of $400\,hPa$ is approximately found at (a) $FL200$, (b) $FL300$, (c) $FL240$, or (d) $FL140$.

Meteorological symbols are used to designate various weather phenomena. Question 11 asks to identify the symbol representing a tropical revolving storm from four options: (a) Symbol b), (b) Symbol c), (c) Symbol d), or (d) Symbol a), where symbols labeled a through f are provided visually.

Density altitude is affected by variations in outside air temperature ($OAT$) compared to the International Standard Atmosphere ($ISA$). If the $OAT$ at a given pressure altitude is warmer than $ISA$, the density altitude is (a) lower than the pressure altitude, (b) the same as the pressure altitude, (c) higher than the pressure altitude, or (d) there is insufficient information to make a comparison.

Aircraft General Knowledge: Powerplants

In a high by-pass ratio turbo-fan engine, the fan is driven by a specific turbine component. This could be (a) the intermediate pressure turbine, (b) the $HP$ (High Pressure) turbine, (c) the rearmost turbine, or (d) the $HP$ compressor.

Twin spool engines feature both Low Pressure ($LP$) and High Pressure ($HP$) compressors. The rotational relationship between these components is described as (a) the $LP$ compressor rotates faster than the $HP$ compressor, (b) the $LP$ compressor sometimes rotates faster and sometimes slower than the $HP$ compressor, (c) the $LP$ compressor rotates slower than the $HP$ compressor, or (d) the $LP$ compressor rotates at the same speed as the $HP$ compressor.

The use of reverse thrust below recommended speeds can lead to several negative consequences. These include (a) overstressing of the gear oleos, (b) ingestion of the exhaust gases and foreign objects, (c) more fuel being provided to the burners, or (d) exceeding the Turbine Gas Temperature ($TGT$) limit, which causes the reverse thrust lever to return to the forward thrust position.

A compressor stall is a critical engine malfunction. It is characterized as (a) something overcome by increasing fuel flow, (b) a complete breakdown of the airflow through the compressor, (c) something that may only affect one stage or several stages of a compressor, or (d) a mechanical failure of the compressor.

Engine power settings are regulated by limitations. Maximum Continuous Power ($M.C.P.$) or Rated Power is described as being (a) unrestricted, but only if economical cruising power is set, (b) the maximum power the engine will give at any time, (c) limited to a 5-minute duration, or (d) entirely unrestricted.

Navigation and Flight Calculations

A ground feature was observed on a relative bearing of $315^{\circ}$ and then $3\,minutes$ later on a relative bearing of $270^{\circ}$. Assuming the Wind Velocity ($W/V$) is calm and the aircraft Groundspeed ($GS$) is $180\,kt$, the minimum distance between the aircraft and the ground feature is calculated to be (a) $12\,nm$, (b) $3\,nm$, (c) $6\,nm$, or (d) $9\,nm$.

In a navigation plotting problem, an aircraft is heading $345^{\circ}M$ with a variation of $20^{\circ}E$. A radar bearing is taken as $30^{\circ}$ left of the aircraft's nose from an island. The bearing that should be plotted from the island is (a) $140^{\circ}T$, (b) $155^{\circ}T$, (c) $160^{\circ}T$, or (d) $180^{\circ}T$.

To achieve a groundspeed maintained to reach a waypoint on time, one must calculate speed based on distance and time. If an aircraft is $135\,nm$ from a waypoint and has $22\,minutes$ remaining to achieve that waypoint on time, the required groundspeed is (a) $368\,kts$, (b) $352\,kts$, (c) $267\,kts$, or (d) $222\,kts$.

Groundspeed calculations can also involve conversions between distance units and time. If an aircraft travels $3.8\,kilometers$ in $1\,minute$ and $13\,seconds$, the groundspeed in knots must be determined. A provided conversion factor states that $1\,kt = 2\,km/h$. The possible answers are (a) $124\,kts$, (b) $130\,mph$, (c) $101\,kts$, or (d) $111\,kts$.