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100+ Free Part-66 Module 11 Practice Questions

Pass your EASA Part-66 Module 11 - Aeroplane Aerodynamics, Structures and Systems exam on the first try — instant access, no signup required.

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2026 Statistics

Key Facts: Part-66 Module 11 Exam

140 questions

B1.1 Exam Length

EASA Part-66 (B1.1 turbine aeroplane)

175 minutes

B1.1 Time Limit

EASA Part-66 (about 75 seconds/question)

75%

Pass Mark per Module

EASA Part-66

400 Hz

Standard AC Frequency

ATA 24 Electrical Power

3,000 psi

Typical Hydraulic Pressure

ATA 29 Hydraulic Power

12 June 2024

2023/989 Applicable (11A/11B/11C merged)

Commission Implementing Regulation (EU) 2023/989

EASA Part-66 Module 11 is taken by aircraft maintenance engineers training for a category B1.1 (turbine aeroplane) or A1 licence. It is one of the largest Part-66 modules: the B1.1 exam is 140 three-option multiple-choice questions in 175 minutes (about 75 seconds each) with a 75% pass mark, sat at a National Aviation Authority or approved Part-147 organisation. Content spans theory of flight and high-speed aerodynamics (Mach number, shock waves, high-lift devices), airframe structures and CS-25 airworthiness (fail-safe and damage tolerance, station/zonal numbering, pressurisation), and aeroplane systems by ATA chapter: air conditioning/pressurisation (21), electrical power (24), fire protection (26), flight controls (27) including fly-by-wire, fuel (28), hydraulics (29), ice and rain protection (30), landing gear (32), oxygen (35), pneumatics (36) and integrated modular avionics. Under Regulation (EU) 2023/989 (applicable 12 June 2024) former sub-modules 11A/11B/11C were merged; pre-2024 courses must finish under the old standard by 12 June 2026.

Sample Part-66 Module 11 Practice Questions

Try these sample questions to test your Part-66 Module 11 exam readiness. Each question includes a detailed explanation. Start the interactive quiz above for the full 100+ question experience with AI tutoring.

1On a swept-wing turbine aeroplane, the speed at which airflow over the upper wing surface first reaches Mach 1.0 (M=1.0) locally while the aircraft itself is still subsonic is known as the:
A.Critical Mach number (Mcrit)
B.Mach number
C.Coffin corner speed
D.Drag divergence Mach number
Explanation: The critical Mach number (Mcrit) is the free-stream Mach number at which the local airflow over the wing first reaches the speed of sound (M=1.0), marking the onset of transonic effects and shock-wave formation.
2As airflow passes through a normal shock wave on the upper surface of a wing in transonic flight, the static pressure of the air:
A.Decreases and velocity increases
B.Increases and velocity decreases to subsonic
C.Remains constant while temperature falls
D.Decreases while density falls
Explanation: Across a normal shock wave the flow decelerates from supersonic to subsonic, so static pressure, density and temperature all increase abruptly while velocity drops below M=1.0.
3A leading-edge slat improves the low-speed lift of a wing primarily by:
A.Increasing the wing camber only
B.Reducing the wing area to lower stall speed
C.Energising the boundary layer and delaying the stall to a higher angle of attack
D.Increasing the chord line incidence relative to the fuselage
Explanation: A slat opens a slot that ducts high-energy air from below to the upper surface, re-energising the boundary layer so the flow stays attached and the stall is delayed to a higher angle of attack and higher CLmax.
4On a large transport aeroplane, roll control at high speed is often provided by spoilers in addition to ailerons mainly because:
A.Spoilers create more lift than ailerons
B.Ailerons cannot be powered hydraulically
C.Spoilers reduce the aircraft's stall speed
D.Outboard ailerons can cause wing twist (aileron reversal) at high dynamic pressure
Explanation: At high dynamic pressure, deflecting an outboard aileron can twist a flexible wing and reverse the rolling moment (aileron reversal); roll spoilers and/or locked-out inboard ailerons avoid this by dumping lift on one wing.
5In a 'fail-safe' airframe structural design philosophy, structural integrity after a single failure is assured because:
A.Multiple load paths exist so remaining structure carries the load until the failure is detected
B.Every component is replaced at a fixed flight-hour life regardless of condition
C.The component is designed never to crack within the aircraft's life
D.Inspections are eliminated because the part cannot fail
Explanation: Fail-safe design provides redundant (multiple) load paths so that if one member fails, the load is carried by the remaining structure long enough for the damage to be found and repaired at the next inspection.
6The 'zonal' identification system used to locate components on a large transport aeroplane divides the aircraft into major zones numbered:
A.By ATA chapter only
B.By major area (e.g. 100 lower fuselage, 200 upper fuselage, 300 empennage, 400 powerplants, 500/600 wings)
C.Alphabetically from nose to tail
D.By electrical bus number
Explanation: The aircraft zoning system splits the airframe into major zones (e.g. 100 lower fuselage, 200 upper fuselage, 300 empennage, 400 nacelles/pylons, 500 left wing, 600 right wing), then sub-zones and zones, to locate components for maintenance.
7On a pressurised fuselage, fuselage station (STA or FS) numbers normally represent the distance:
A.Vertically above the cabin floor
B.From the wing root in degrees
C.Measured in inches aft of a fixed datum (station zero) near or ahead of the nose
D.Outboard from the aircraft centreline
Explanation: Fuselage station numbers give the longitudinal distance (usually in inches) measured aft of a reference datum plane at or ahead of the nose, allowing any frame or component to be located precisely.
8A semi-monocoque fuselage carries flight loads primarily through:
A.The skin alone, with no internal structure
B.Pressurisation air pressure acting on the skin
C.Solid internal trusses with non-structural skin
D.A combination of skin (stressed), frames, formers, longerons and stringers
Explanation: In semi-monocoque construction the stressed skin carries a large part of the load but is supported by frames/formers (shape) and longerons/stringers (longitudinal bending), distributing stresses and resisting buckling.
9The cabin pressurisation outflow valve principally controls cabin pressure by:
A.Modulating the rate at which air is allowed to leave the fuselage
B.Regulating the volume of bleed air entering the cabin
C.Opening only as an emergency dump valve
D.Sensing engine N1 and adjusting bleed pressure
Explanation: Inflow from the packs is roughly constant, so cabin pressure is governed by controlling the rate of outflow; the outflow valve modulates how much air escapes the cabin, setting cabin altitude and rate of change.
10In an air-cycle air-conditioning pack, the cold air leaving the system is produced mainly by:
A.A refrigerant compressor and evaporator
B.Expansion of the air across the cold-air unit (ACM) turbine, which extracts energy
C.Mixing with liquid nitrogen
D.Passing the air over the battery heat exchanger
Explanation: In an air-cycle machine, hot bleed air is partially cooled in heat exchangers, then expanded across the expansion turbine; the work the air does driving the turbine removes energy, dropping its temperature sharply.

About the Part-66 Module 11 Exam

EASA Part-66 Module 11 is the large aeroplane aerodynamics, structures and systems module that aircraft maintenance engineers must pass for a category B1.1 (turbine aeroplane) or A1 licence. It covers theory of flight including high-speed (transonic) aerodynamics, airframe structures and airworthiness, and the full range of aeroplane systems by ATA chapter - air conditioning and pressurisation, electrical power, fire protection, flight controls, fuel, hydraulics, ice and rain protection, landing gear, oxygen, pneumatics and modern avionics architectures. Under Commission Implementing Regulation (EU) 2023/989 (applicable 12 June 2024) the former sub-modules 11A, 11B and 11C were merged into a single Module 11. The B1.1 examination is 140 multiple-choice questions in 175 minutes with a 75% pass mark.

Questions

140 scored questions

Time Limit

175 minutes (category B1.1 turbine aeroplane)

Passing Score

75% per module

Exam Fee

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

Part-66 Module 11 Exam Content Outline

16%

Theory of Flight & High-Speed Flight

Roll, pitch and yaw control surfaces; high-lift devices (slats, slots, Krueger and Fowler flaps); spoilers and lift dumpers; Mach number, critical Mach and drag divergence; shock waves and compressibility; wing sweep, vortex generators and supercritical aerofoils

20%

Airframe Structures & Airworthiness

CS-25 airworthiness requirements; fail-safe, safe-life and damage-tolerance philosophies; semi-monocoque fuselage with stringers and frames; fuselage station and zonal numbering; wing torsion box and integral tanks; stabilisers; plug doors and pressurised windows; tear straps and pressurisation structure

15%

Air Conditioning & Pressurisation (ATA 21)

Bleed-air, APU and ground-cart supply; air-cycle (ACM) and vapour-cycle packs; heat exchangers and water separators; ozone converters; mixing chambers and zone temperature control; outflow valves, cabin-altitude and rate control; differential-pressure and safety relief valves

15%

Electrical Power (ATA 24)

AC generation at 400 Hz; constant speed drive and integrated drive generator; generator control units and paralleling; transformer rectifier units; static inverters; busbars and bus-tie breakers; Ni-Cd thermal runaway; ram air turbine emergency power; distribution, bonding and differential protection

16%

Flight Controls, Fire & Ice Protection (ATA 26, 27, 30)

Primary and secondary controls; fly-by-wire, control laws and envelope protection; trim, yaw damper, Mach trim and artificial feel; continuous-loop and dual-loop fire/overheat detection; halon extinguishing; Class C cargo and lavatory protection; thermal anti-ice, de-icer boots and probe heat

18%

Fuel, Hydraulic, Pneumatic & Landing Gear (ATA 28, 29, 32, 36)

Boost pumps, cross-feed, jettison, CG transfer and capacitance fuel quantity; hydraulic pumps (EDP/EMDP), reservoirs, accumulators, PTU and priority valves; bleed-air pre-coolers and leak detection; oleo struts, anti-skid, autobrake, nose-wheel steering, air-ground sensing and carbon brakes

How to Pass the Part-66 Module 11 Exam

What You Need to Know

  • Passing score: 75% per module
  • Exam length: 140 questions
  • Time limit: 175 minutes (category B1.1 turbine aeroplane)
  • Exam fee: Approx. EUR 50-230 per module sitting (varies by NAA/Part-147 organisation)

Keys to Passing

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

Part-66 Module 11 Study Tips from Top Performers

1Memorise the B1.1 exam logistics: 140 multiple-choice questions in 175 minutes (about 75 seconds each) with a 75% pass mark - pace yourself and do not dwell too long on any one question
2Learn each system by ATA chapter (21 air conditioning, 24 electrical, 26 fire, 27 flight controls, 28 fuel, 29 hydraulics, 30 ice/rain, 32 landing gear, 36 pneumatics) so you can place any question quickly
3Know key numbers cold: 400 Hz AC generation, ~3,000 psi hydraulic pressure, ~8,000 ft maximum cabin altitude, and 28 V DC distribution
4Distinguish closely related concepts: anti-icing (prevents ice) versus de-icing (removes ice), fail-safe versus safe-life versus damage tolerance, and air-cycle versus vapour-cycle packs
5Understand fly-by-wire fundamentals - electrical signalling to computers, control laws and envelope protection - and how artificial feel, yaw damper and Mach trim support handling on swept-wing jets
6Study the 2023/989 merge: 11A, 11B and 11C are now one Module 11, so expect both turbine-aeroplane (dominant) and some piston-aeroplane items in the syllabus

Frequently Asked Questions

What is EASA Part-66 Module 11?

Module 11 is the aeroplane aerodynamics, structures and systems module of the EASA Part-66 aircraft maintenance licence syllabus. It is required for a category B1.1 (turbine aeroplane) or A1 licence and covers theory of flight, airframe structures and the full range of aeroplane systems organised by ATA chapter.

How many questions is the Module 11 exam and what is the time limit?

For category B1.1 (turbine aeroplane) the Module 11 examination is 140 multiple-choice questions in 175 minutes - about 75 seconds per question. The B1.2 piston version is 100 questions in 125 minutes and category A1 is 108 questions in 135 minutes.

What is the pass mark?

All EASA Part-66 module examinations require 75% to pass. The questions are three-option multiple choice with no marks deducted for wrong answers. Candidates are allowed a maximum of three consecutive attempts, then a 90-day waiting period before retrying.

What changed when 11A, 11B and 11C were merged?

Under Commission Implementing Regulation (EU) 2023/989, applicable from 12 June 2024, the former sub-modules 11A (turbine), 11B and 11C (piston) were merged into a single Module 11. Pre-2024 courses had to complete under the old standard by 12 June 2026.

Which systems (ATA chapters) does Module 11 cover?

Module 11 covers air conditioning/pressurisation (ATA 21), electrical power (24), fire protection (26), flight controls (27), fuel (28), hydraulics (29), ice and rain protection (30), landing gear (32), oxygen (35), pneumatics (36) plus avionics integration, on-board maintenance and integrated modular avionics.

Is this practice test free?

Yes. All 100 OpenExamPrep Module 11 practice questions and the AI tutor are free with no signup required. The bank uses four options for deeper learning, while the real EASA exam uses three-option multiple choice.