All Practice Exams

100+ Free Module 15 Practice Questions

Pass your EASA Part-66 Module 15 - Gas Turbine Engine exam on the first try — instant access, no signup required.

✓ No registration✓ No credit card✓ No hidden fees✓ Start practicing immediately
100+ Questions
100% Free

Loading practice questions...

2026 Statistics

Key Facts: Module 15 Exam

92 questions / 115 min

B1.1/B1.3 Module 15 Exam

EASA Part-66 examination standard

75%

Pass Mark per Module

EASA Part-66

~75 seconds

Time per Question

115 min / 92 questions

12 June 2024

Regulation (EU) 2023/989 Applicable

Commission Implementing Regulation (EU) 2023/989

22 sub-modules

Module 15 Syllabus (15.1-15.22)

EASA Part-66 Appendix I

Level 3

15.21 Engine Monitoring (B1)

EASA Part-66 knowledge levels

-47 C

Jet A-1 Max Freezing Point

DEF STAN 91-091 / Jet A-1 spec

EASA Part-66 Module 15 is the gas-turbine engine module sat by aircraft maintenance licence candidates in the Category A1/A3 and B1.1/B1.3 streams (it is not taken by B2/B3). For B1.1/B1.3 it is 92 multiple-choice questions in 115 minutes (A1/A3: 60 questions/75 minutes), passed at 75% - about 75 seconds per question. The real EASA exam uses 3-option MCQ; this free practice bank uses 4 options. The 22 sub-modules run from fundamentals (Brayton cycle, thrust, SFC, bypass ratio) and engine performance (EPR, flat rating) through the gas path (inlet, compressors with stall/surge and variable stator vanes, combustion, turbine creep and cooling, exhaust and thrust reversers), bearings and seals, lubricants and fuels, lubrication and fuel systems (hydromechanical and FADEC), air systems, starting and ignition, indication, turboprop/turboshaft/APU, installation and fire protection, to level-3 engine monitoring and ground operation. Content follows Regulation (EU) 2023/989, applicable 12 June 2024.

Sample Module 15 Practice Questions

Try these sample questions to test your Module 15 exam readiness. Each question includes a detailed explanation. Start the interactive quiz above for the full 100+ question experience with AI tutoring.

1The gas turbine engine operates on a thermodynamic cycle in which air is continuously compressed, heated at constant pressure, and then expanded through a turbine and nozzle. Which cycle is this?
A.The Brayton (constant-pressure) cycle
B.The Otto cycle
C.The Carnot cycle
D.The Diesel (constant-volume) cycle
Explanation: The gas turbine works on the Brayton cycle, in which combustion (heat addition) occurs at essentially constant pressure as the gases flow continuously through the engine, unlike the intermittent combustion of a piston engine.
2In a gas turbine, the four phases of the working cycle occurring continuously in different parts of the engine are:
A.Induction, compression, expansion, exhaust
B.Induction, compression, combustion, exhaust
C.Intake, combustion, ignition, exhaust
D.Compression, ignition, power, scavenge
Explanation: The gas-turbine cycle phases are induction (intake), compression, combustion (heat addition), and exhaust (expansion through turbine and nozzle), occurring simultaneously and continuously rather than sequentially in one chamber.
3Gross thrust of a turbojet at a given operating point is calculated, ignoring fuel mass, as the mass flow multiplied by the jet velocity. Net thrust is obtained by:
A.Adding the ram drag (intake momentum drag) to the gross thrust
B.Multiplying gross thrust by the bypass ratio
C.Subtracting the ram drag (intake momentum drag) from the gross thrust
D.Dividing gross thrust by the engine pressure ratio
Explanation: Net thrust = gross thrust minus ram drag. Ram drag is the momentum of the incoming air (mass flow x aircraft forward speed); subtracting it accounts for the momentum the engine must first impart to entering air.
4Specific fuel consumption (SFC) of a turbojet/turbofan engine is most correctly defined as:
A.Thrust per unit of compressor speed
B.Thrust produced per litre of fuel
C.Fuel flow divided by airflow
D.Fuel flow per unit of thrust per unit time
Explanation: Thrust SFC is the fuel mass (or weight) consumed per unit of thrust per hour (e.g., kg/h per kN). A lower SFC means a more economical engine for the thrust produced.
5A high-bypass turbofan develops most of its thrust from:
A.The fan (bypass) airflow
B.The core (hot) exhaust gases
C.The afterburner
D.The exhaust nozzle convergence alone
Explanation: In a high-bypass turbofan the large fan moves a great mass of air around the core; this cold bypass stream produces the majority (typically around 80%) of the total thrust, giving high propulsive efficiency and low noise.
6Bypass ratio of a turbofan engine is defined as the ratio of:
A.Core airflow to bypass airflow
B.Bypass (fan) airflow to core (gas-generator) airflow
C.Fan speed to compressor speed
D.Total thrust to core thrust
Explanation: Bypass ratio = mass of air passing through the bypass duct divided by the mass passing through the core. A bypass ratio of 10:1 means ten times as much air bypasses the core as flows through it.
7A 'flat-rated' engine is one whose maximum rated thrust is held constant up to a particular ambient temperature. Above that 'kink-point' or 'corner' temperature, the rated thrust:
A.Continues to increase with temperature
B.Remains unchanged regardless of temperature
C.Is reduced as ambient temperature rises further
D.Increases only at high altitude
Explanation: A flat-rated engine maintains its rated thrust up to the flat-rating (corner) temperature by holding back available thrust on cold days. Above that temperature the engine can no longer hold the rating without exceeding limits, so thrust falls off with rising temperature.
8Engine Pressure Ratio (EPR), used as a thrust-setting parameter on many turbofans, is the ratio of:
A.Fan discharge pressure to core discharge pressure
B.Combustion chamber pressure to ambient pressure
C.Compressor delivery pressure to inlet pressure
D.Turbine exhaust (or exit) total pressure to engine inlet total pressure
Explanation: EPR is the ratio of turbine/exhaust total pressure (Pt7) to compressor inlet total pressure (Pt2). It gives the flight crew an indication of the thrust the engine is producing.
9As an aircraft climbs at constant Mach number, the thrust of a gas turbine generally decreases. The principal reason is:
A.Falling air density reduces the mass airflow through the engine
B.Rising ambient temperature increases drag
C.The fuel becomes less dense at altitude
D.The compressor speed automatically reduces
Explanation: Thrust is proportional to mass airflow. As altitude increases, air density falls, so for a given engine the mass of air ingested drops and thrust decreases, even though ram effect provides partial recovery.
10The primary purpose of the engine air intake (inlet) on a subsonic turbofan is to:
A.Accelerate the air to supersonic speed before the fan
B.Deliver air to the compressor face at the correct velocity with minimum loss and good distribution
C.Burn excess fuel before the compressor
D.Cool the bypass duct
Explanation: A subsonic intake is a divergent duct that diffuses (slows) the incoming air, recovering ram pressure and delivering a uniform, low-turbulence flow to the fan/compressor face with minimum pressure loss.

About the Module 15 Exam

EASA Part-66 Module 15 (Gas Turbine Engine) is the dedicated turbine-engine examination for candidates pursuing a Category A1/A3 or B1.1/B1.3 aircraft maintenance licence. It covers the theory and construction of gas-turbine engines from the Brayton cycle and engine performance through the inlet, compressors, combustion, turbine and exhaust, plus bearings, seals, fuel and oil systems, starting, ignition, indication, engine types, powerplant installation, fire protection and engine monitoring. For B1.1/B1.3 the exam is 92 multiple-choice questions in 115 minutes with a 75% pass mark. Content here follows the syllabus as amended by Commission Implementing Regulation (EU) 2023/989, applicable from 12 June 2024.

Questions

92 scored questions

Time Limit

115 minutes (B1.1/B1.3); 75 minutes for A1/A3 (60 questions)

Passing Score

75% per module

Exam Fee

Varies by NAA/Part-147 organisation (approx. EUR 50-230 per module sitting) (EASA framework; exams sat at National Aviation Authorities or approved Part-147 maintenance training organisations)

Module 15 Exam Content Outline

18%

Fundamentals & Engine Performance

Brayton (constant-pressure) cycle and the four cycle phases, Newton's third-law thrust, gross/net thrust and ram drag, specific fuel consumption (SFC), bypass ratio, overall pressure ratio, engine pressure ratio (EPR), flat rating and thrust ratings, propulsive efficiency, and the thrust lapse with altitude (sub-modules 15.1-15.2)

30%

Inlet, Compressors, Combustion, Turbine & Exhaust

Subsonic intake diffusion and bleed-air anti-ice, centrifugal vs axial compressors, stall and surge, variable stator vanes and handling-bleed valves, annular and multi-can combustors with duplex nozzles and swirl/dilution air, nozzle guide vanes, turbine fir-tree roots, creep, internal blade cooling, nickel superalloys, convergent and convergent-divergent nozzles, thrust reversers and noise suppression (15.3-15.7)

10%

Bearings, Seals & Air Systems

Ball (thrust/locating) and roller bearings, labyrinth seals, the internal air system using P3 compressor delivery air for turbine cooling, bearing-chamber sealing and pressurisation, the centrifugal breather, and engine anti-ice air with overheat/leak monitoring (15.8, 15.12)

20%

Lubricants, Fuels, Lubrication & Fuel Systems

Synthetic ester oils to MIL-PRF-23699/7808, Jet A-1 (freezing point about -47 C) and FSII anti-ice additive, pressure and scavenge pumps with greater scavenge capacity, hot- and cold-tank systems, magnetic chip detectors and filter impending-bypass indicators, hydromechanical and FADEC fuel control, gear-type fuel pumps, fuel-cooled oil coolers and the pressurising/shut-off valve (15.9-15.11)

10%

Starting, Ignition & Indication

Start sequence and motoring, air-turbine and starter-generator starters, capacitor-discharge high-energy ignition, continuous ignition, hung and hot starts, EGT thermocouples and EGT margin, N1/N2 percentage rpm, EPR, torque on turboprop/turboshaft, fuel flow and vibration monitoring (15.13-15.14)

12%

Engine Types, Installation, Fire & Ground Operation

Geared turbofan, open-rotor and hybrid-electric awareness, turboprop reduction gears with constant-speed governing and feathering, free-turbine turboshaft, APUs, power augmentation, QEC build-up and engine mounts, firewalls, fire detection and two-bottle extinguishing, and level-3 engine monitoring: boroscope, EHM/trend monitoring, ground run and storage/preservation (15.15-15.22)

How to Pass the Module 15 Exam

What You Need to Know

  • Passing score: 75% per module
  • Exam length: 92 questions
  • Time limit: 115 minutes (B1.1/B1.3); 75 minutes for A1/A3 (60 questions)
  • Exam fee: Varies by NAA/Part-147 organisation (approx. EUR 50-230 per module sitting)

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 15 Study Tips from Top Performers

1Lock in the exam logistics: 92 questions in 115 minutes for B1.1/B1.3 (about 75 seconds each) at a 75% pass mark - practise pacing so you do not run out of time
2Understand the Brayton cycle and the four phases (induction, compression, combustion, exhaust) and be able to derive net thrust = gross thrust minus ram drag
3Know the surge story cold: stall/surge from excessive blade angle of attack, and how variable stator vanes and handling-bleed valves restore surge margin at low speed and during acceleration
4Memorise turbine hot-section facts: fir-tree blade roots, creep as time/temperature/stress elongation, internal air cooling from compressor (P3) air, and nickel superalloy single-crystal blades
5Distinguish the fuel-system building blocks: gear-type HP pump, hydromechanical vs FADEC control, fuel-cooled oil cooler, and Jet A-1 (freezing point about -47 C) with FSII anti-ice additive
6Treat sub-module 15.21 (Engine Monitoring) as level 3: be fluent in boroscope inspection, EHM/trend monitoring, a falling EGT margin as deterioration, and safe ground-run intake/exhaust danger zones

Frequently Asked Questions

Who takes EASA Part-66 Module 15?

Module 15 (Gas Turbine Engine) is taken by candidates for the Category A1, A3, B1.1 and B1.3 aircraft maintenance licences - the aeroplane-turbine and helicopter-turbine streams. It is not taken by B2 (avionics) or B3 (piston-aeroplane) candidates, and the piston-engine module (16) is separate.

How many questions are on Module 15 and how long is the exam?

For Category B1.1/B1.3 the Module 15 exam is 92 multiple-choice questions to be answered in 115 minutes (about 75 seconds per question). For Category A1/A3 it is a smaller subset of 60 questions in 75 minutes. The pass mark is 75%.

What is the pass mark and how is the exam scored?

Every EASA Part-66 module is passed at 75%. Module 15 is multiple-choice only - there is no essay (essays remain only in Module 7). The real EASA exam uses 3-option questions; this free practice bank uses 4 options to add challenge.

Does Module 15 follow the 2023/989 syllabus?

Yes. This practice content is built to the syllabus as amended by Commission Implementing Regulation (EU) 2023/989, applicable from 12 June 2024, which merged some former sub-module splits and added awareness of geared-turbofan, open-rotor and hybrid-electric concepts. Note that the UK CAA has diverged post-Brexit, so this content is EASA-specific.

What topics carry the most weight on Module 15?

The largest block is the engine gas path - inlet, compressors (with stall and surge), combustion, turbine (creep and cooling) and exhaust. Fundamentals and performance, and the fuel/oil/lubrication systems, are also heavily examined, with engine monitoring (15.21) uniquely taught at knowledge level 3 for B1.

How long should I study for Module 15?

Most candidates spend roughly 80-120 hours on the gas-turbine module, typically over 8-12 weeks alongside a Part-147 course. Strong grounding in the Brayton cycle, compressor airflow, and the fuel and oil system schematics pays off because many questions test cause-and-effect understanding rather than rote facts.