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100+ Free Module 11A Aeroplane Turbine Practice Questions
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Sample Module 11A Aeroplane Turbine Practice Questions
Try these sample questions to test your Module 11A Aeroplane Turbine exam readiness. Each question includes a detailed explanation. Start the interactive quiz above for the full 100+ question experience with AI tutoring.
1What happens to the local airflow speed over the upper surface of a swept wing as an aeroplane approaches its Critical Mach Number (M_crit)?
A.Local airflow speed reaches Mach 1.0 at the point of maximum camber before the aircraft reaches Mach 1.0
B.Local airflow speed remains strictly subsonic until the free-stream Mach number reaches Mach 1.0
C.Local airflow speed decreases due to the boundary layer energisation over swept wings
D.Local airflow speed becomes supersonic across the entire wing surface simultaneously
Explanation: Critical Mach Number (M_crit) is defined as the free-stream Mach number at which airflow over any part of the aircraft surface (typically the point of maximum camber on the upper wing surface) first reaches Mach 1.0.
2What is the primary function of wing sweepback on high-speed turbine aeroplanes?
A.To increase the Critical Mach Number by reducing the effective thickness-to-chord ratio normal to the leading edge
B.To eliminate wave drag completely at supersonic speeds
C.To move the centre of pressure forward during high-speed cruise
D.To increase low-speed lift production during take-off and landing
Explanation: Sweepback resolves the airflow vector into components parallel and perpendicular to the leading edge. The perpendicular velocity component is smaller than total airspeed, effectively delaying shockwave formation and increasing M_crit.
3Which aerodynamic phenomenon causes 'tuck under' in high-speed jet transport aeroplanes?
A.Aft movement of the wing centre of pressure combined with loss of tailplane downforce due to shockwave formation
B.Forward shift of the aerodynamic centre as airspeed exceeds M_crit
C.Flow separation at the wing root causing an abrupt pitch-up moment
D.Excessive yaw damper inputs at high Mach numbers leading to Dutch roll
Explanation: As speed increases beyond M_crit, shockwaves form on the wing causing the centre of pressure to move aft. Simultaneously, the downwash reaching the tailplane decreases, leading to a nose-down pitching moment called 'tuck under'.
4What is the purpose of a Mach trim system in a turbine transport aircraft?
A.Automatically adjust the elevator or horizontal stabiliser position to counter tuck-under tendencies at high Mach numbers
B.Trim the rudder automatically during single-engine operation at high altitude
C.Vary the engine thrust automatically to prevent exceeding V_MO/M_MO
D.Adjust the roll trim to compensate for asymmetrical shockwave formation on swept wings
Explanation: Mach trim monitors Mach number via air data computers and automatically repositions the horizontal stabiliser or elevator to maintain neutral pitch stability and prevent tuck-under as speed increases.
5Why are vortex generators fitted to the upper surface of swept wings on turbine aeroplanes?
A.To re-energise the boundary layer with high-energy air from above, delaying shock-induced boundary layer separation
B.To increase laminar airflow across the entire wing root area
C.To reduce wingtip vortices and decrease induced drag during cruise
D.To generate aerodynamic lift directly at low angles of attack
Explanation: Vortex generators create small high-energy vortices that mix high-energy free-stream air into the slow boundary layer, keeping it attached longer and preventing shock-induced stall/separation.
6How does a stall warning stick shaker/pusher system determine when to activate on a turbine aeroplane?
A.Inputs from angle of attack (AoA) sensors, wing flap position sensors, and air data computers
B.Direct measurement of hydraulic pressure in the elevator PCU return line
C.Cockpit airspeed indicator pitot-static pressure differential threshold only
D.Engine N1 shaft speed and altitude sensors
Explanation: Stall warning computers process alpha (AoA) vane positions, flap/slat configuration signals, and Mach/airspeed data to compute critical angle of attack thresholds and trigger the shaker/pusher.
7What aerodynamic effect occurs when a normal shockwave forms on an aerofoil in transonic flight?
A.Air pressure and density increase behind the shockwave, while airflow velocity drops from supersonic to subsonic
B.Air pressure and density decrease behind the shockwave, while velocity accelerates to hypersonic speeds
C.Airflow velocity remains constant while temperature drops to freezing levels
D.Airflow direction reverses completely across the entire upper wing surface
Explanation: Across a normal shockwave in transonic flight, static pressure, temperature, and density increase abruptly, while airflow speed drops from supersonic to subsonic.
8Why are outboard ailerons typically locked out (inhibited) during high-speed cruise flight on jet transport aircraft?
A.To prevent severe wing twisting (control reversal) and structural overstressing caused by high dynamic pressure
B.To reduce electrical load on the primary flight control computers
C.To allow the outboard spoilers to operate as ground lift dumpers
D.To maintain artificial feel system pressure within normal limits
Explanation: At high speeds, deploying outboard ailerons creates large torsional moments on flexible swept wings, potentially flexing the wing in reverse and causing control reversal. Outboard ailerons are locked out, leaving inboard ailerons (or roll spoilers) for lateral control.
9Which boundary layer control device is deployed along the leading edge of a swept wing during low-speed landing configuration?
A.Krueger flaps or slats, which delay stall by extending the nose profile and re-energising upper surface airflow
B.Trim tabs, which balance control surface hinge moments
C.Mach trim vanes, which counter high-speed tuck under
D.Vortex generators, which retract into the upper wing skin during high speed
Explanation: Leading-edge slats and Krueger flaps extend forward and down at low speeds to increase camber, create a slot for boundary layer energisation, and allow high angles of attack without stalling.
10What is the function of speedbrakes/spoilers when symmetrical extension is selected in flight?
A.Increase parasite drag and destroy wing lift to permit steep descents without increasing airspeed
B.Increase wing lift while maintaining constant pitch attitude during holding patterns
C.Provide asymmetric roll control assistance at low airspeed only
D.Automatically trim the rudder to maintain directional stability during turbulence
Explanation: Symmetrical speedbrake/spoiler deployment disrupts upper surface laminar/attached flow, dumping lift and increasing parasite drag, allowing steep descents or rapid deceleration.
About the Module 11A Aeroplane Turbine Exam
UK CAA Part-66 Module 11A tests turbine aeroplane airframe structures and complex mechanical/electrical systems for Category B1.1 AME candidates. Exam includes 140 MCQs with a 75% pass mark.
Questions
140 scored questions
Time Limit
175 minutes
Passing Score
75%
Exam Fee
£75 (UK Civil Aviation Authority (CAA))
Module 11A Aeroplane Turbine 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 11A Aeroplane Turbine Exam
What You Need to Know
- Passing score: 75%
- Exam length: 140 questions
- Time limit: 175 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 11A Aeroplane Turbine 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 11A Aeroplane Turbine?
The pass mark required by the UK CAA is 75%.