100+ Free CAA NZ Basic Turbine Knowledge (Aeroplane) Practice Questions

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Practice Questions100 questions

2026 Statistics

Key Facts: CAA NZ Basic Turbine Knowledge (Aeroplane) Exam

50 Qs

Total multiple-choice questions on the exam.

CAA NZ / Aspeq Examination Guidelines

90 Mins

Time duration allowed to complete the paper.

Aspeq Exam Schedule

70%

Minimum passing score required.

CAA NZ Advisory Circular AC61-1

$108 NZD

Exam fee per attempt.

Aspeq NZ Fee Schedule

3 Modules

Principles, Engine Systems, Controls & Limiters.

CAA NZ BTK Syllabus

CAA NZ BTK Aeroplane is a 50-question, 90-minute examination requiring a 70% pass mark for pilots operating turbine-powered aeroplanes in New Zealand.

Sample CAA NZ Basic Turbine Knowledge (Aeroplane) Practice Questions

Try these sample questions to test your CAA NZ Basic Turbine Knowledge (Aeroplane) exam readiness. Each question includes a detailed explanation. Start the interactive quiz above for the full 100+ question experience with AI tutoring.

1Which fundamental thermodynamic cycle describes the operational process of a continuous-flow gas turbine engine?

A.Brayton cycle

B.Otto cycle

C.Diesel cycle

D.Carnot cycle

Explanation: Gas turbine engines operate on the constant-pressure Brayton cycle, which consists of four continuous, non-overlapping processes: induction, compression, constant-pressure combustion, and expansion/exhaust.

2What is the main operational advantage of a free-turbine turboprop engine compared to a single-shaft turboprop engine?

A.The propeller can turn independently of the gas generator spool, resulting in lower starter load

B.The engine consumes significantly less fuel during high-altitude cruise

C.The propeller is permanently locked to the high-pressure compressor shaft

D.It eliminates the requirement for a reduction gearbox

Explanation: In a free-turbine engine (like the PT6A), the power turbine driving the propeller is mechanically independent of the compressor/gas generator shaft. This allows the starter to rotate only the gas generator during start, drastically reducing starter motor torque requirements.

3What is the primary function of the compressor section in a gas turbine engine?

A.To increase the pressure and density of air before it enters the combustion chamber

B.To extract thermal energy from expanding combustion gases

C.To atomize fuel and mix it with high-velocity air

D.To expand exhaust gases to create forward jet thrust

Explanation: The compressor draws in ambient air and compresses it through successive stages, increasing its static pressure and density prior to entering the combustion section for efficient fuel burning.

4What is the primary purpose of the diffuser section positioned downstream of the compressor?

A.To decrease air velocity and increase static pressure before combustion

B.To increase air velocity and decrease static pressure before the turbine

C.To mix fuel evenly with high-speed air prior to ignition

D.To cool high-temperature air before it enters the turbine

Explanation: The diffuser is a divergent passage located between the compressor and combustor. Its purpose is to slow down high-velocity discharge air from the compressor, converting kinetic energy into static pressure for stable combustion.

5What is a typical pressure ratio achieved per stage by a centrifugal compressor?

A.4:1 to 5:1

B.1.1:1 to 1.2:1

C.15:1 to 20:1

D.30:1 to 40:1

Explanation: A single centrifugal compressor stage typically achieves a pressure ratio between 4:1 and 5:1 (or up to 8:1 in modern advanced designs), whereas an axial compressor stage achieves only about 1.1:1 to 1.25:1 per stage.

6Which turbine engine component extracts mechanical energy from expanding exhaust gases to drive the engine compressor?

A.Turbine rotor assembly

B.Combustion chamber

C.Exhaust nozzle

D.Propeller reduction gearbox

Explanation: The turbine rotor converts thermal and kinetic energy of hot expanding combustion gases into mechanical shaft power to drive the compressor and engine accessories.

7What is the primary aerodynamic function of nozzle guide vanes (stators) located immediately upstream of a turbine rotor stage?

A.To accelerate gas velocity and direct flow at the optimal angle onto turbine rotor blades

B.To slow down gas flow to prevent rotor blade flutter

C.To mix fuel evenly with hot gases before entering the turbine rotor

D.To increase static pressure of the gas stream prior to expansion

Explanation: Nozzle guide vanes form convergent passages that convert static pressure into kinetic energy (accelerating the gas) and direct high-velocity gas onto the turbine rotor blades at the correct angle of entry.

8What combustion chamber layout is used in Pratt & Whitney PT6A turboprop engines to minimize overall engine length?

A.Reverse-flow annular combustor

B.Multiple-can combustor

C.Straight-through can-annular combustor

D.External pulsejet combustor

Explanation: The PT6A engine utilizes a reverse-flow annular combustion chamber. Air flows backward into the combustor, reverses direction during combustion, and flows forward through the turbine stages, significantly shortening overall engine length.

9What percentage of total air entering a gas turbine combustor is used as secondary (cooling) air?

A.Approximately 70% to 75%

B.Approximately 20% to 25%

C.Approximately 5% to 10%

D.100%

Explanation: Only about 25% to 30% of total compressor discharge air is used for primary combustion. The remaining 70% to 75% serves as secondary air for liner wall cooling, flame dilution, and temperature pattern shaping before entering the turbine.

10What type of exhaust nozzle profile is standard on subsonic turbojet and turboprop aircraft?

A.Convergent nozzle

B.Divergent nozzle

C.Convergent-divergent nozzle

D.Variable geometry bellmouth nozzle

Explanation: Subsonic aircraft use a convergent exhaust nozzle, which accelerates exhaust gas velocity up to a maximum speed of Mach 1.0 (choked flow) at the nozzle exit duct.

About the CAA NZ Basic Turbine Knowledge (Aeroplane) Exam

The CAA NZ Basic Turbine Knowledge (Aeroplane) exam tests candidates on gas turbine engine principles, engine systems (FCU/FADEC, fuel, oil, start cycles, stall/surge, bleed air, anti-ice), and operational controls (levers, beta range, reverse pitch, autofeather, and engine limiters).

Assessment

50 multiple-choice questions administered electronically in 90 minutes.

Time Limit

90 minutes

Passing Score

70%

Exam Fee

$108 NZD (Civil Aviation Authority of New Zealand (exams via Aspeq))

CAA NZ Basic Turbine Knowledge (Aeroplane) Exam Content Outline

35%

Gas Turbine Engine Principles

Brayton cycle, turboprop/turbojet/turbofan operational principles, axial and centrifugal compressors, combustion chamber configurations, turbine stage mechanics, and exhaust nozzles.

40%

Engine Systems

Fuel control units (FCU) and FADEC, fuel and oil systems, ignition and start cycles (hung, hot, wet starts), compressor stalls and surge, bleed air utilization, and engine anti-ice systems.

25%

Operational Controls & Limiters

Power, condition, and propeller levers, beta range and reverse pitch operation, autofeather systems, and engine limiters (ITT, TGT, N1, N2, Torque).

How to Pass the CAA NZ Basic Turbine Knowledge (Aeroplane) Exam

What You Need to Know

Passing score: 70%
Assessment: 50 multiple-choice questions administered electronically in 90 minutes.
Time limit: 90 minutes
Exam fee: $108 NZD

Keys to Passing

Complete 500+ practice questions
Score 80%+ consistently before scheduling
Focus on highest-weighted sections
Use our AI tutor for tough concepts

CAA NZ Basic Turbine Knowledge (Aeroplane) Study Tips from Top Performers

1Understand the thermodynamic processes in the Brayton constant pressure cycle (compression, combustion, expansion, exhaust).

2Master the operational causes and indications of hung start, hot start, and wet start, along with immediate pilot memory actions.

3Differentiate between axial and centrifugal compressors, including pressure ratios per stage and susceptibility to stalls.

4Learn the function of condition levers, beta range, and autofeather logic in turboprop aircraft like the Beech King Air or Dash 8.

5Memorize the key engine parameters monitored to prevent thermal or structural damage: ITT/TGT, N1, N2, and Torque limits.

Frequently Asked Questions

What is the CAA NZ Basic Turbine Knowledge (Aeroplane) exam?

It is a specialized theory examination administered by Aspeq on behalf of the Civil Aviation Authority of New Zealand (CAA NZ) for pilots operating turbine-powered aircraft.

What is the passing score and time limit?

The passing score is 70% and the exam duration is 90 minutes.

Where is the exam taken?

The exam is a computer-based test (CBT) taken at authorized Aspeq exam centers across New Zealand.

What core topics are examined?

Topics include gas turbine engine principles (Brayton cycle, compressors, turbines), engine systems (FCU/FADEC, oil, start cycles, stall/surge), and operational controls/limiters.

How much does the exam cost?

The exam sitting fee is $108 NZD.