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EASA Part66 Module 15 Cats A1 · A3 · B1.1 · B1.3

Gas Turbine Engine EASA Part66 — Module 15 Practice Questions

Module 15 covers the gas turbine engine end-to-end — Brayton cycle theory, intake and compressor behaviour, combustion, the hot section, fuel and oil systems, indications, and ground operation. Below: what's examinable, exam format, and seven sample questions in the same style you'll meet on exam day.

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1 377
Questions in bank
5
Syllabus sections
115 min
Exam time (B1/B2)
75 %
EASA pass mark

Syllabus at a glance

Full Module 15 syllabus
Section 15.1 / 15.2
Fundamentals & Performance
  • Brayton cycle, Newton's laws & energy conversion
  • Turbojet, turbofan, turboprop & turboshaft layouts
  • Gross/net thrust, EPR, bypass ratio & SFC (B1 only)
  • Flat rating, altitude & hot-day limitations (B1 only)
Section 15.3 / 15.4
Intake & Compressor
  • Inlet duct configurations & ice protection
  • Axial vs centrifugal compressors
  • Stall & surge — causes, indications, recovery
  • Bleed valves, VIGVs & variable stator vanes
Section 15.5
Combustion Section
  • Annular, can & cannular chamber layouts
  • Primary, secondary & dilution airflow split
  • Swirl vanes, flame-tube cooling & hot-spots
Section 15.6 / 15.7
Turbine & Exhaust
  • Impulse, reaction & impulse-reaction blading
  • Nozzle guide vanes, blade root attachment
  • Creep, stress & shrouded rotor tips
  • Convergent & convergent-divergent nozzles, thrust reversers
Section 15.14 / 15.21
Indications, Monitoring & FOD
  • EGT/ITT, EPR, N1/N2, oil & fuel parameters
  • Trend monitoring, oil analysis & vibration
  • Borescope inspection & FOD assessment (level 3 for B1)
  • Compressor wash & ground run-up procedures

Three classic exam-day traps

Brayton: constant-pressure, not constant-volume

The Otto cycle (piston engines) is constant-volume; the Brayton cycle (gas turbines) is constant-pressure. Many candidates swap them under exam pressure and lose easy fundamentals marks.

Subsonic vs supersonic nozzle behaviour

Subsonic air speeds up in a convergent duct and slows in a divergent one. Supersonic flow does the opposite. Mix the regimes and every exhaust-section question becomes a coin-flip.

N1 indicates LP — but the LP turbine drives it

In a twin-spool engine, the front fan and LP compressor share the N1 shaft, but that shaft is turned by the rear LP turbine — not the HP turbine. Twin-spool spool-up questions hinge on this.

What Module 15 covers — in plain English

Module 15 is the dedicated gas-turbine paper sat by Category A1, A3, B1.1 and B1.3 candidates — the aeroplane-turbine and helicopter-turbine licence streams. Candidates working towards a piston licence (A2, A4, B1.2, B1.4) sit Module 16 instead, and B2 avionics candidates skip both. The syllabus walks the engine from intake to tailpipe: Brayton-cycle fundamentals, inlet aerodynamics, axial and centrifugal compressors, combustion, the hot section, bearings and seals, fuel and oil systems, air and anti-ice systems, ignition and starting, indications, alternate constructions, turboprop and turboshaft variants, APUs, the powerplant installation, fire protection, ground operation and storage. B1 candidates also cover engine performance — gross and net thrust, EPR, SFC, bypass ratio, flat rating — and the newer 15.15 section on geared turbofans, open-rotor and hybrid-electric concepts introduced by EU 2023/989 in June 2024.

The exam is one of the larger Part66 papers — 92 questions in 115 minutes for B1.1/B1.3, or 60 questions in 75 minutes for A1/A3. Time per question is roughly 75 seconds, so the paper rewards candidates who can recognise a stem (e.g. "the working fluid of a gas turbine is …") and lock the answer in without re-deriving it. The hot-section topics — combustion airflow split, NGV function, turbine creep, EGT limits — and the FADEC/fuel-control questions are where most marks are lost. The performance section also catches B1 candidates who memorise formulas but mix up which efficiency applies (thermal, propulsive, or overall) for a given stem, or who confuse N1 and N2 spool attribution on twin-spool engines.

Knowledge levels run mostly at level 2 for B1 across the syllabus, with level 3 on 15.21 — Engine Monitoring and Ground Operation, reflecting that B1 engineers actually carry out ground runs, borescope inspections and trend interpretation on the line. Cat A1/A3 candidates sit a smaller subset, mostly at level 1, and skip 15.2 Performance, 15.8 Bearings and Seals, 15.15 Alternate Constructions and 15.22 Storage entirely. Section 15.6 Turbine and 15.3 Inlet are level 2 even at A-licence, because line maintenance on those sections is part of an A-engineer's scope. The full per-section breakdown — including which paragraphs you can safely skim and which need full level-2 recall — is on our Module 15 syllabus page.

These samples are drawn from our live Module 15 question bank of 1 377 questions. The full timed practice quiz draws 92 questions per attempt (or 60 for Cat A), scored against the official EASA 75 % pass mark, with weak-area tracking across attempts.

7 free sample questions

Click "Reveal answer + explanation" after you've picked.

Take the timed practice quiz
Q1 Fundamentals · Thermodynamic cycle

The Brayton cycle is known as the constant

  1. A temperature cycle.
  2. B mass cycle.
  3. C pressure cycle.
Reveal answer + explanation Hide answer
Correct answer: Cpressure cycle.
The Brayton (gas-turbine) cycle is the constant-pressure cycle: combustion adds heat at essentially constant chamber pressure while the gas accelerates through the engine. Piston engines run the constant-volume Otto cycle — a common swap in exam stems.
Q2 Performance · Bypass ratio

A high bypass engine results in

  1. A overall slower airflow and greater propulsive efficiency.
  2. B overall faster airflow.
  3. C greater propulsive efficiency.
Reveal answer + explanation Hide answer
Correct answer: Aoverall slower airflow and greater propulsive efficiency.
A high bypass ratio moves a larger mass of air at a lower velocity, which raises propulsive efficiency (smaller jet/aircraft velocity gap) and cuts SFC and noise. The "faster airflow" distractor describes a low-bypass turbojet, not a modern high-bypass turbofan.
Q3 Compressor · Gas-path pressures

At what point in an axial flow turbojet engine will the highest gas pressures occur?

  1. A At the compressor outlet.
  2. B At the turbine entrance.
  3. C Within the burner section.
Reveal answer + explanation Hide answer
Correct answer: AAt the compressor outlet.
Pressure peaks at the compressor outlet (P3/CDP), just before combustion. The Brayton cycle is constant-pressure, but small losses through the diffuser and flame tube mean turbine entry pressure is fractionally lower than compressor discharge.
Q4 Combustion · Flame stabilisation

What component creates a vortex in a gas turbine flame tube?

  1. A Tertiary hole.
  2. B Swirl vanes.
  3. C Cascade vanes.
Reveal answer + explanation Hide answer
Correct answer: BSwirl vanes.
Swirl vanes sit around the fuel nozzle and impart rotation to the primary airflow, creating the low-velocity recirculation zone that anchors the flame. Without that vortex the flame would be blown downstream and the chamber would weak-extinguish.
Q5 Exhaust · Subsonic flow

As subsonic air flows through a convergent nozzle the velocity

  1. A decreases.
  2. B increases.
  3. C remains constant.
Reveal answer + explanation Hide answer
Correct answer: Bincreases.
For subsonic flow, a converging duct accelerates the gas (and pressure falls) — continuity plus Bernoulli. Most exhaust nozzles on civil turbofans are simple convergent designs because they only need to reach Mach 1 at the throat for choked operation.
Q6 Indications · EGT limits

A factor that limits EGT is the

  1. A jet pipe.
  2. B compressors.
  3. C turbine.
Reveal answer + explanation Hide answer
Correct answer: Cturbine.
EGT redlines are set by the turbine — specifically the NGV and HP turbine blade material limits. Beyond the limit, creep accelerates dramatically. EGT is measured downstream of the turbine precisely because the upstream turbine-inlet temperature is too hot to instrument directly.
Q7 Monitoring · Borescope inspection

When carrying out a borescope the damage on turbine blades that would indicate a failure is

  1. A speckling.
  2. B tip curl.
  3. C colour changes.
Reveal answer + explanation Hide answer
Correct answer: Btip curl.
Tip curl indicates the blade has crept under combined centrifugal and thermal stress beyond its plastic limit — a reject finding. Speckling and discolouration are normal hot-section signatures and only become reject conditions when they coincide with cracking or material loss.
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