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100+ Free Module 14 Propulsion Practice Questions
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Sample Module 14 Propulsion Practice Questions
Try these sample questions to test your Module 14 Propulsion exam readiness. Each question includes a detailed explanation. Start the interactive quiz above for the full 100+ question experience with AI tutoring.
1What is the primary function of a gas turbine engine inlet duct on a subsonic transport aircraft?
A.To increase air velocity and reduce static pressure before entering the compressor
B.To convert kinetic energy of the incoming air into static pressure with minimal total pressure loss
C.To mix bleed air with ambient air to prevent compressor stall
D.To meter the mass airflow directly into the combustion chamber
Explanation: A subsonic inlet duct acts as a divergent duct (diffuser), decreasing incoming air velocity while increasing static pressure to provide uniform, low-velocity airflow to the compressor face.
2In a high-bypass turbofan engine, which turbine section directly drives the low-pressure (LP) compressor and fan?
A.High-Pressure Turbine (HPT)
B.Intermediate-Pressure Turbine (IPT)
C.Low-Pressure Turbine (LPT)
D.Radial-flow power turbine
Explanation: The Low-Pressure Turbine (LPT) is mechanically connected via a concentric inner shaft to drive the low-pressure compressor (LPC) and the front fan module.
3What is the main purpose of nozzle guide vanes (NGVs) located immediately upstream of the first-stage turbine rotor?
A.To decrease gas pressure and increase velocity while directing flow at the optimum angle onto turbine blades
B.To compress the hot gases before entering the exhaust nozzle
C.To reduce thermal stress by cooling the turbine disc without altering gas direction
D.To prevent reverse airflow from the exhaust duct into the combustor
Explanation: Nozzle guide vanes form convergent passages that convert thermal and pressure energy into kinetic energy (accelerating gas velocity) while directing gas flow at the optimum angle onto the turbine rotor blades.
4Which type of combustion chamber layout consists of individual burner cans interconnected by flame tubes surrounding the engine shaft?
A.Annular combustor
B.Can-annular (cannular) combustor
C.Reverse-flow radial combustor
D.Single centrifugal combustor
Explanation: A can-annular combustor features multiple individual cylindrical cans arranged in a ring around the engine shaft, surrounded by a common air casing and connected by flame propagation tubes.
5What structural role do engine turbine shrouds perform in a modern gas turbine engine?
A.They form the outer boundary of the turbine gas path to minimize blade tip clearance losses
B.They support the engine main oil sump bearings directly from the fan case
C.They act as acoustic attenuation tiles to dampen low-frequency intake noise
D.They meter cooling bleed air into the primary exhaust stream
Explanation: Turbine shrouds form the stationary outer ring enclosure surrounding turbine blade tips, controlling tip clearances to maintain high aerodynamic efficiency and prevent gas leakage.
6What unit measures the total pressure of air at the engine intake face, commonly designated as station P2 or Pt2?
A.Compressor exit pressure sensor (P3)
B.Engine inlet total pressure probe / transducer
C.Turbine exhaust gas pressure probe (P5)
D.Ambient static port on the aircraft fuselage
Explanation: Station 2 (P2 or Pt2) total pressure is measured by an inlet pressure probe/transducer mounted in the engine inlet nose cone or intake ducting.
7What does the acronym FADEC stand for in modern aircraft propulsion systems?
A.Flight Automated Engine Control
B.Full Authority Digital Engine Control
C.Fuel Actuated Digital Engine Computer
D.Fixed Amplitude Digital Electronic Controller
Explanation: FADEC stands for Full Authority Digital Engine Control, an integrated electronic system that has complete control over engine operation and engine actuators.
8In a FADEC system, what provides dedicated AC electrical power to the Electronic Engine Control (EEC) during normal engine operation above idling speed?
A.The aircraft main DC battery bus
B.The engine-driven Permanent Magnet Alternator (PMA/PMG)
C.The flight control static inverter
D.The auxiliary power unit (APU) generator bus
Explanation: Once the engine accelerates past starter cutout/idle speed, a dedicated engine-driven Permanent Magnet Alternator (PMA or PMG) supplies self-contained electrical power to both EEC channels independent of aircraft bus power.
9How many independent electronic channels are typically contained within a standard dual-channel EEC / FADEC computer?
A.One channel with analog backup circuits
B.Two identical channels (Channel A and Channel B)
C.Three triple-redundant channels (A, B, and C)
D.Four quad-redundant channels
Explanation: Standard engine FADEC architecture features a dual-redundant configuration consisting of two complete, isolated electronic channels (Channel A and Channel B).
10What is the primary function of the Hydro-Mechanical Unit (HMU) or Fuel Metering Unit (FMU) in a FADEC-controlled engine?
A.To generate digital control algorithms for engine acceleration
B.To execute electrical commands from the EEC by physically metering fuel flow to the combustor nozzles
C.To measure exhaust gas temperature directly using thermocouple junctions
D.To supply high-voltage ignition sparks during engine start
Explanation: The HMU/FMU is the hydromechanical slave component that contains fuel pumps, metering valves, bypass valves, and torque motors to physically control fuel flow based on electrical signals from the EEC.
About the Module 14 Propulsion Exam
UK CAA Part-66 Module 14 covers turbine engine indicating parameters, electronic engine control (FADEC), and powerplant fire protection for Category B2 AME candidates. Exam includes 24 MCQs with a 75% pass mark.
Questions
24 scored questions
Time Limit
30 minutes
Passing Score
75%
Exam Fee
£75 (UK Civil Aviation Authority (CAA))
Module 14 Propulsion Exam Content Outline
50%
Core Knowledge & Regulations
Fundamental principles, laws, and operating requirements.
50%
Applied Systems & Calculations
Practical application, calculations, and maintenance procedures.
How to Pass the Module 14 Propulsion Exam
What You Need to Know
- Passing score: 75%
- Exam length: 24 questions
- Time limit: 30 minutes
- Exam fee: £75
Keys to Passing
- Complete 500+ practice questions
- Score 80%+ consistently before scheduling
- Focus on highest-weighted sections
- Use our AI tutor for tough concepts
Module 14 Propulsion Study Tips from Top Performers
1Review official CAA syllabus and learning objectives.
2Practise worked calculations and formula applications.
Frequently Asked Questions
What is the pass mark for Module 14 Propulsion?
The pass mark required by the UK CAA is 75%.