EASA Module 17 Practice Questions - EASA Part-66 Module 17 - Propeller Exam - EASA Module 17 Practice Questions - EASA Part-66 Module 17

Question 1

In propeller blade element theory, the blade is analysed as a series of small aerofoil sections along its length. Why is the geometric pitch (blade angle) progressively reduced from the root to the tip?

Because the tip moves through a greater rotational distance per revolution than the root, so a smaller angle keeps the angle of attack and advance roughly constant along the blade Because the root sees a higher relative airflow velocity than the tip and must be unloaded Because centrifugal force is greatest at the tip and a small angle reduces blade stress Because the tip operates in compressible flow and a small angle prevents shock formation at all speeds

Correct Answer:

Because the tip moves through a greater rotational distance per revolution than the root, so a smaller angle keeps the angle of attack and advance roughly constant along the blade

Question 2

Propeller geometric pitch is defined as the distance the propeller would advance in one revolution if it moved through the air like a screw through a solid. The actual distance the propeller advances is the effective pitch. The difference between geometric and effective pitch is known as:

Slip Blade angle Helix angle Angle of attack

Correct Answer:

Slip

Question 3

For a fixed-pitch propeller, what happens to the angle of attack of the blade sections as the aircraft's forward (true) airspeed increases at a constant engine RPM?

The angle of attack increases because the relative airflow becomes more axial The angle of attack remains constant because RPM is unchanged The angle of attack decreases because the forward velocity vector increases the helix angle of the relative airflow The angle of attack reverses, producing negative thrust

Correct Answer:

The angle of attack decreases because the forward velocity vector increases the helix angle of the relative airflow

Question 4

Which force acting on a rotating propeller blade is by far the greatest in magnitude and acts to throw the blade outward along its longitudinal axis?

Thrust bending force Centrifugal twisting moment Centrifugal force Aerodynamic twisting moment

Correct Answer:

Centrifugal force

Question 5

The centrifugal twisting moment (CTM) acting on a rotating propeller blade tends to rotate the blade toward which pitch position, and how is this exploited in many propeller designs?

Toward low (fine) pitch; used to drive the blades to fine pitch on oil-pressure loss Toward high (coarse) pitch; used to assist feathering Toward feather; used as an overspeed stop Toward reverse; used to assist ground braking

Correct Answer:

Toward low (fine) pitch; used to drive the blades to fine pitch on oil-pressure loss

Question 1

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Prepare with the EASA Module 17 Practice Questions - EASA Part-66 Module 17 - Propeller Exam practice quiz. This question bank includes 100 questions covering propeller, blade, constant-speed, engine, and blades. Use it to review important concepts, identify knowledge gaps, and build confidence for the related exam, course, or assessment.

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EASA Module 17 Practice Questions - EASA Part-66 Module 17 - Propeller Exam

This practice set contains 100 questions from the matching question bank and focuses on propeller, blade, constant-speed, engine, and blades. Work through each question carefully, review the provided solutions, and revisit topics that need more study before your next attempt.

This is an independent study resource intended for practice and review; it is not an official examination or an endorsement by any organization named in the title.

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EASA Module 17 Practice Questions - EASA Part-66 Module 17 - Propeller Exam

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