Free Practice Questions for CAA NZ AME Licence Exam - Turbine Engines (Subject 6)

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Key Facts: CAA NZ AME Licence Exam - Turbine Engines (Subject 6) Exam

50 Qs

Total multiple-choice questions on the exam.

CAA NZ / Aspeq Examination Syllabus

90 Mins

Time duration allowed for the examination.

Aspeq Exam Schedule

70%

Minimum passing grade required.

CAA NZ AC66-2.6

$108 NZD

Official examination booking fee.

Aspeq NZ Fee Schedule

Subject 6

CAA NZ AME Syllabus Designation for Turbine Engines.

CAA NZ Part 66

CAA NZ AME Subject 6 (Turbine Engines) is a 50-question, 90-minute examination requiring a 70% passing score for aircraft maintenance engineer certification in New Zealand.

Sample CAA NZ AME Licence Exam - Turbine Engines (Subject 6) Practice Questions

Try these sample questions to review concepts for the CAA NZ AME Licence Exam - Turbine Engines (Subject 6) exam. Each question includes a detailed explanation. Start the interactive quiz above for the full 100+ question experience with AI tutoring.

1Which thermodynamic cycle describes the ideal operational process of a gas turbine engine?

A.Otto cycle

B.Brayton cycle

C.Diesel cycle

D.Carnot cycle

Explanation: The gas turbine engine operates on the Brayton constant pressure thermodynamic cycle, consisting of continuous compression, constant-pressure combustion, expansion through the turbine, and exhaust heat release.

2In the basic jet engine net thrust equation Fn = m_dot * (Vout - Vin), what does 'm_dot' represent?

A.Mass flow rate of air passing through the engine per unit time

B.Fuel mass flow rate entering the fuel nozzles

C.Ratio of exhaust gas velocity to inlet air velocity

D.Density of the ambient atmosphere at flight altitude

Explanation: In the momentum thrust equation Fn = m_dot * (Vout - Vin), 'm_dot' represents the mass flow rate of air passing through the engine (typically expressed in kg/s or lb/s).

3How is the bypass ratio of a turbofan engine defined?

A.Ratio of turbine inlet temperature to compressor inlet temperature

B.Ratio of mass airflow bypassing the engine core to mass airflow passing through the core

C.Ratio of total compressor pressure rise to ambient static pressure

D.Ratio of fan rotor speed (N1) to high-pressure spool speed (N2)

Explanation: Bypass ratio (BPR) is defined as the ratio of air mass flow rate passing around the engine core through the bypass duct to the air mass flow rate entering the core engine combustor and turbine.

4What primary energy conversion occurs across the stationary stator vanes in an axial flow compressor stage?

A.Pressure energy is converted into kinetic energy to accelerate the airflow

B.Kinetic energy imparted by the rotor is converted into static pressure energy

C.Thermal energy from combustion is converted into mechanical shaft torque

D.Mechanical torque is converted into fuel atomization energy

Explanation: Stator vanes in an axial compressor form divergent passages that decrease air velocity, thereby converting kinetic energy imparted by the preceding rotor blades into static pressure energy while directing airflow at the correct angle to the next stage.

5What is the primary function of the diffuser in a centrifugal compressor?

A.To accelerate the air into supersonic flow before entering the combustor

B.To convert high-velocity kinetic energy from the impeller into static pressure energy

C.To cool the compressed air before it enters the combustion chamber

D.To mix fuel droplets evenly with incoming air prior to ignition

Explanation: The diffuser contains divergent passages radiating outward from the centrifugal impeller tip. As high-velocity air flows through these divergent passages, its speed decreases and kinetic energy is converted into static pressure energy.

6Which combustion chamber type consists of separate individual cylindrical flame tubes housed inside their own outer air jackets?

A.Annular combustor

B.Can-type (multiple-can) combustor

C.Can-annular combustor

D.Reverse-flow radial combustor

Explanation: A can-type (or multiple-can) combustion system features individual self-contained cylindrical burner cans arranged circumferentially around the engine axis, each with its own fuel nozzle and casing.

7What is a major advantage of an annular combustion chamber compared to a multiple-can combustor?

A.Easier individual chamber removal during line maintenance

B.Lower thermal efficiency due to increased surface area

C.Smaller frontal area and optimal power-to-weight ratio

D.Elimination of secondary cooling airflow requirement

Explanation: Annular combustors offer the highest thermal efficiency, shortest length, minimal frontal area, and lightest weight because they utilize a continuous annular volume without internal division walls.

8What is the purpose of flame interconnecting tubes (flame tubes) between individual cans in a can-annular combustor?

A.To equalize fuel flow pressure across all fuel nozzles

B.To propagate flame from igniter-equipped cans to remaining cans during starting

C.To vent excess compressor bleed air into the turbine section

D.To balance hydraulic oil pressure across the engine bearings

Explanation: Interconnecting tubes connect adjacent flame tubes in can or can-annular systems, allowing combustion flame to rapidly propagate to all chambers when ignition occurs in the two cans equipped with spark igniters.

9What is the primary function of Nozzle Guide Vanes (NGVs) located upstream of the first stage turbine wheel?

A.To slow down gas flow and increase static temperature entering the turbine

B.To accelerate gas flow and direct it at the optimal angle onto turbine rotor blades

C.To strip moisture out of the combustion exhaust gases

D.To prevent compressor reverse flow during engine shutdown

Explanation: Nozzle Guide Vanes (NGVs) form convergent passages that accelerate the hot expanding exhaust gases from the combustor and direct them at the precise angle onto the turbine rotor blades to produce rotation.

10In an impulse turbine stage, where does the expansion and pressure drop of working fluid primarily occur?

A.Entirely across the stationary nozzle guide vanes

B.Entirely across the moving turbine rotor blades

C.Equally across both nozzle guide vanes and moving rotor blades

D.Across the exhaust cone convergent tailpipe

Explanation: In a pure impulse turbine stage, gas expansion and static pressure drop occur exclusively in the stationary nozzle guide vanes. The high-velocity jet then strikes the rotor blades without further pressure drop across the rotor blades.

About the CAA NZ AME Licence Exam - Turbine Engines (Subject 6) Exam

The CAA NZ AME Subject 6 Turbine Engines examination tests candidate engineers on gas turbine engine design, Brayton cycle dynamics, thrust equations, multi-spool compressor & turbine mechanics, combustor types, thrust reversers, FCU/FADEC, fuel/oil/ignition/starter systems, engine indication, and maintenance practices including borescope inspection and compressor washing.

Exam sponsor: Civil Aviation Authority of New Zealand (exams via Aspeq). The requirements and fees below concern the certification or admission exam, separate from our free practice resources.

Assessment

50 multiple-choice questions administered electronically in 90 minutes.

Time Limit

90 minutes

Passing Score

70%

Exam / Certification Fees

$108 NZD

Exam sponsor website

Fees, eligibility, and exam policies can change. Confirm them with the exam sponsor before applying or paying.

Official sources

Our practice resources: topics covered

We aim to reflect publicly available exam outlines and topic information in our study resources. Coverage, format, and difficulty may differ from the actual exam, and we cannot guarantee that every detail is accurate or current. Confirm exam requirements, fees, and policies with the official exam sponsor.

50%

Turbine Engine Design & Gas Dynamics

Brayton cycle thermodynamic principles, net/gross thrust calculations, bypass ratio, axial & centrifugal compressor design, combustor configurations, turbine nozzle guide vanes, single-crystal blades, and thrust reversers.

50%

Turbine Engine Systems & Maintenance

Hydro-mechanical FCU and FADEC architecture, fuel nozzles, dry sump oil systems, high-energy ignition units, starters, engine parameter indication (EPR, N1, N2, ITT/EGT, vibration), compressor washing, and borescope inspection.

Preparing for the CAA NZ AME Licence Exam - Turbine Engines (Subject 6) Exam

What You Need to Know

Passing score: 70%
Assessment: 50 multiple-choice questions administered electronically in 90 minutes.
Time limit: 90 minutes
Exam / certification fees: $108 NZD Official sources

Using Our Practice Resources

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CAA NZ AME Licence Exam - Turbine Engines (Subject 6): Suggested Study Strategy

1Master the Brayton constant pressure cycle PV and TS diagrams and efficiency relationships.

2Practice thrust calculations including mass flow, exit velocity, ram drag, and nozzle pressure thrust.

3Understand multi-spool compressor aerodynamics, stall margin control via VSVs and bleed valves.

4Study FADEC channel architecture, crosstalk sensor logic, and reversionary N1 control modes.

5Review borescope blending inspection criteria, thermal barrier coating spallation limits, and compressor wash procedures.

Frequently Asked Questions

What is the CAA NZ AME Subject 6 Turbine Engines exam?

It is an essential licence examination for aircraft maintenance engineers in New Zealand seeking Category P (Powerplant) rating endorsement under CAA NZ Rule Part 66.

What is the passing score and time limit?

The passing score is 70% and candidates are given 90 minutes to answer 50 multiple-choice questions.

Where are the exams conducted?

Exams are delivered electronically via Aspeq testing centres across New Zealand.

What mathematical calculations are tested?

Calculations include thrust equations (F = m_dot * (V_out - V_in)), bypass ratio calculations, overall pressure ratios, and specific fuel consumption (SFC).

How much does the exam cost?

The examination fee is $108 NZD per sitting.