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Sample PPL(H) Performance Helicopter Practice Questions
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1What primary mechanism causes Hover In Ground Effect (HIGE) to require less engine power than Hover Out of Ground Effect (HOGE)?
A.The proximity of the ground reduces induced flow velocity and rotor tip vortices, increasing the effective angle of attack.
B.The ground surface increases parasitical drag on the fuselage, forcing lower engine RPM.
C.HIGE increases downwash velocity through the rotor disc, generating greater lift coefficient.
D.The ground friction reduces tail rotor power requirement by 50%.
Explanation: In Ground Effect (HIGE), the physical boundary of the ground restricts the expansion of rotor downwash. This reduces induced flow (inflow velocity) through the main rotor disc and curtails the formation of rotor tip vortices. With less induced flow, the relative wind is pitched more horizontally, increasing the effective angle of attack for a given pitch setting and reducing induced drag, thereby requiring less power.
2At approximately what altitude above the surface is ground effect generally considered to cease for a main rotor system?
A.At a height equal to one main rotor diameter above the surface.
B.At a height equal to ten main rotor diameters above the surface.
C.At a height equal to one rotor blade chord width above the surface.
D.At 50 feet AGL regardless of rotor size.
Explanation: Ground effect is maximum right near the surface and gradually diminishes as height increases. It virtually ceases when the rotor height above the surface exceeds approximately one rotor disc diameter (1.0 D).
3Which component of total power required by a helicopter decreases most significantly as airspeed increases from a hover to Effective Translational Lift (ETL)?
A.Induced power.
B.Parasite power.
C.Profile power.
D.Tail rotor anti-torque power.
Explanation: Total power required consists of induced power, profile power, parasite power, and accessory/tail rotor power. At zero airspeed (hover), induced power (power needed to accelerate air downward) is at its maximum. As forward airspeed increases into ETL (16-24 knots), the rotor moves into clean, undisturbed air, significantly reducing induced power.
4Effective Translational Lift (ETL) typically occurs within which speed range during forward acceleration?
A.16 to 24 knots.
B.5 to 10 knots.
C.40 to 50 knots.
D.60 to 70 knots.
Explanation: Effective Translational Lift (ETL) occurs when the main rotor completely outruns its own re-circulated downwash vortices and receives a clean mass flow of air, typically between 16 and 24 knots.
5If a helicopter requires 85% torque to hover out of ground effect (HOGE) and maximum available take-off power is 80% torque under ambient conditions, what is the operational limitation?
A.The helicopter cannot perform a HOGE; it must perform a HIGE take-off or reduce gross mass.
B.The helicopter can perform a HOGE by increasing rotor RPM past maximum limit.
C.The helicopter can perform HOGE if a tailwind is present.
D.The helicopter can perform HOGE by lowering the collective during hover.
Explanation: Because HOGE requires 85% torque and maximum available power is only 80%, attempting HOGE will lead to drooping rotor RPM and a descent. The pilot must either lower gross mass or ensure a HIGE departure path over clear terrain.
6How does slope terrain affect Hover In Ground Effect (HIGE) efficiency compared to flat terrain?
A.Ground effect efficiency is reduced because rotor downwash flows down the slope, preventing full cushion build-up.
B.Ground effect efficiency is increased because slope angle directs air straight back into the intake.
C.Ground effect efficiency is completely unaffected by ground slope.
D.Slope terrain eliminates tail rotor drift entirely.
Explanation: Sloping ground allows rotor downwash to escape downhill rather than creating a stagnant high-pressure air cushion directly beneath the rotor disc. Consequently, ground effect benefit is partially lost.
7What change in rotor performance occurs when transitioning from hover in calm air to hovering with a 15-knot headwind?
A.The helicopter enters Effective Translational Lift (ETL) while stationary relative to the ground, requiring less power to hover.
B.The helicopter requires higher engine power due to wind turbulence.
C.Rotor induced flow increases, requiring collective to be raised significantly.
D.Tail rotor becomes redundant and requires zero power.
Explanation: Airflow over the rotor disc is relative wind. A 15-knot headwind supplies 15 knots of relative wind across the main rotor disc, placing the rotor into Effective Translational Lift (ETL) even though ground speed is zero.
8On a power-required versus airspeed curve for a helicopter, what does the minimum point on the total power curve represent?
A.Maximum endurance airspeed (V_min_power).
B.Maximum range airspeed.
C.Never exceed speed (V_NE).
D.Hover out of ground effect power.
Explanation: The lowest point of the total power required curve represents the minimum power required speed (Vy). Flying at this airspeed consumes fuel at the lowest hourly rate, yielding maximum endurance.
9How is Maximum Range Airspeed determined from a power-required curve?
A.By drawing a straight tangent line from the origin (0 speed, 0 power) to the total power curve.
B.By selecting the exact lowest point of the total power curve.
C.By selecting the point where parasite power equals zero.
D.By adding 20 knots to V_NE.
Explanation: Maximum range airspeed represents maximum distance per unit of fuel (power/speed ratio). Graphically, this is the point of tangency on the total power curve for a line drawn from the origin (0,0).
10What happens to induced power required as a helicopter's forward airspeed increases beyond 80 knots?
A.Induced power decreases to a very low value and remains low, while parasite power dominates.
B.Induced power increases exponentially to become the dominant power consumer.
C.Induced power equals profile power at all airspeeds above 50 knots.
D.Induced power becomes negative, driving the engine.
Explanation: Induced power varies inversely with forward airspeed (P_induced proportional to 1/V). At high forward speeds (e.g., 80+ kt), induced power is minimal, while parasite power (P_parasite proportional to V^3) becomes the dominant component.
About the PPL(H) Performance Helicopter Exam
UK CAA PPL(H) Performance covers hover power requirements, weight and balance CG calculations, height-velocity avoid zones, and environmental performance for private helicopter pilots. Exam includes 20 MCQs with a 75% pass mark.
Exam sponsor: UK Civil Aviation Authority (CAA). The requirements and fees below concern the certification or admission exam, separate from our free practice resources.
Questions
20 questions
Time Limit
45 minutes
Passing Score
75%
Fees, eligibility, and exam policies can change. Confirm them with the exam sponsor before applying or paying.
Official sources
Our practice resources: topics covered
We aim to reflect publicly available exam outlines and topic information in our study resources. Coverage, format, and difficulty may differ from the actual exam, and we cannot guarantee that every detail is accurate or current. Confirm exam requirements, fees, and policies with the official exam sponsor.
50%
Core Knowledge & Regulations
Fundamental principles, laws, and operating requirements.
50%
Applied Systems & Calculations
Practical application, calculations, and maintenance procedures.
Preparing for the PPL(H) Performance Helicopter Exam
What You Need to Know
- Passing score: 75%
- Exam length: 20 questions
- Time limit: 45 minutes
- Exam / certification fees: £50 Official sources
Using Our Practice Resources
- Work through all 100 available questions
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PPL(H) Performance Helicopter: Suggested Study Strategy
1Review official CAA syllabus and learning objectives.
2Practise worked calculations and formula applications.
Frequently Asked Questions
What is the pass mark for PPL(H) Performance Helicopter?
The pass mark required by the UK CAA is 75%.