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100+ Free CAAS SAR-66 Module 17 (Propeller) Practice Questions
CAAS SAR-66 Basic Knowledge Examination - Module 17 Propeller practice questions are available now; exam metadata is being verified.
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2026 Statistics
Key Facts: CAAS SAR-66 Module 17 (Propeller) Exam
32 Qs
Total MCQs on the official CAAS examination.
CAAS SAR-66 Appendix 1
40 Mins
Duration allowed for the examination.
CAAS Airworthiness Notice 10 / AC 66-13
75%
Minimum passing score per module.
CAAS SAR-66 Requirements
S$87.20
Examination fee per basic subject from 1 Jan 2026.
Air Navigation Order Twelfth Schedule
B1.1 / B1.2
Licence categories requiring Module 17.
CAAS SAR-66 Syllabus
CAAS SAR-66 Module 17 Propeller tests B1.1/B1.2 AME candidates across 32 MCQs in 40 minutes with a 75% passing mark on propeller theory, control, and maintenance.
Sample CAAS SAR-66 Module 17 (Propeller) Practice Questions
Try these sample questions to test your CAAS SAR-66 Module 17 (Propeller) exam readiness. Each question includes a detailed explanation. Start the interactive quiz above for the full 100+ question experience with AI tutoring.
1What is defined as the distance an aircraft propeller would advance in one revolution through a solid, non-yielding medium?
A.Geometric pitch
B.Effective pitch
C.Slip distance
D.Angle of attack
Explanation: Geometric pitch is the theoretical distance a propeller blade element would advance forward in one complete 360-degree revolution if it were turning through a solid medium without slipping. It depends purely on the blade angle relative to the plane of rotation. Effective pitch is the actual distance the propeller advances through air during flight.
2An aircraft propeller has a geometric pitch of 72 inches. During steady cruising flight, the propeller actually advances 54 inches per revolution. What is the propeller slip and percent slip?
A.Slip is 18 inches, Percent slip is 25%
B.Slip is 18 inches, Percent slip is 33.3%
C.Slip is 12 inches, Percent slip is 16.7%
D.Slip is 24 inches, Percent slip is 30%
Explanation: Propeller slip is calculated as Geometric Pitch minus Effective Pitch (72 in - 54 in = 18 in). Percent slip is calculated as (Slip / Geometric Pitch) * 100 = (18 / 72) * 100 = 25%. This slip represents the aerodynamic efficiency loss inherent in pulling air rearward to generate thrust.
3Which aerodynamic turning moment acts on a rotating propeller blade to rotate the blade toward a higher blade pitch angle (coarse pitch)?
A.Aerodynamic Turning Moment (ATM)
B.Centrifugal Turning Moment (CTM)
C.Thrust Bending Moment
D.Torque Bending Moment
Explanation: The Aerodynamic Turning Moment (ATM) is caused by the center of pressure on the blade aerofoil being located forward of the blade pitch-change axis. The aerodynamic lift generated by the blade tries to rotate the blade to a higher pitch angle (coarse pitch). In contrast, Centrifugal Turning Moment (CTM) opposes ATM by attempting to rotate the blade toward fine pitch.
4Why is Centrifugal Turning Moment (CTM) generally greater than Aerodynamic Turning Moment (ATM) under normal operating engine speeds?
A.Centrifugal forces acting on blade mass elements create a high rotational moment seeking alignment with the plane of rotation, overcoming aerodynamic forces
B.Aerodynamic forces decay to zero whenever the propeller blade is operating at cruise speed
C.CTM and ATM act in the exact same direction, so CTM adds directly to ATM strength
D.ATM only occurs when the engine is operating at negative pitch angles during ground reversing
Explanation: Centrifugal Turning Moment (CTM) results from centrifugal force acting on every particle of mass along the blade thickness. Because mass elements attempt to align themselves in the plane of rotation, CTM exerts a powerful twisting force toward fine pitch that significantly exceeds the coarse-pitch twisting force of ATM under high operational RPM.
5In a constant-speed governor, flyweight centrifugal force is governed by the formula F = m * omega^2 * r. If engine rotational speed (omega) increases by 20%, by what percentage does the flyweight centrifugal force increase?
A.44%
B.20%
C.40%
D.80%
Explanation: Centrifugal force is proportional to the square of angular velocity (F ~ omega^2). If speed increases to 1.20 times original, force becomes (1.20)^2 = 1.44 times original force, representing a 44% increase. This non-linear relationship makes constant-speed governors highly sensitive to minor RPM deviations.
6What is the primary function of twisting a propeller blade along its span from shank to tip (blade wash-out)?
A.To maintain a relatively uniform angle of attack along the entire length of the blade despite varying rotational speeds
B.To increase structural strength at the tip where centrifugal force is highest
C.To eliminate Centrifugal Turning Moment (CTM) during high speed dives
D.To allow the blade shank to generate more thrust than the blade tip
Explanation: Because the tip travels through a much larger circumference than the shank during each revolution, rotational velocity increases from hub to tip. Twisting the blade to decrease the blade angle progressively toward the tip maintains a near-constant effective angle of attack and uniform thrust generation across the span.
7How is propeller efficiency (eta) defined in aircraft propulsion performance calculations?
A.Ratio of Thrust Horsepower (THP) to Brake Horsepower (BHP)
B.Ratio of Geometric Pitch to Effective Pitch
C.Ratio of Aerodynamic Turning Moment (ATM) to Centrifugal Turning Moment (CTM)
D.Ratio of forward velocity to rotational velocity
Explanation: Propeller efficiency is defined as Thrust Horsepower divided by Brake Horsepower (eta = THP / BHP). It measures how effectively engine shaft output power (BHP) is converted into useful propulsive power (THP) in the air.
8Which side of a propeller blade aerofoil corresponds to the cambered upper surface of a standard aircraft wing?
A.Blade back (curved surface facing forward in direction of flight)
B.Blade face (flat surface facing rearward toward pilot)
C.Blade shank
D.Blade leading edge
Explanation: The blade back is the curved (cambered) surface of the aerofoil that faces forward in the direction of flight. Low pressure is created over the blade back in accordance with Bernoulli's principle, pulling the aircraft forward to produce thrust.
9If an aircraft accelerates in level flight while engine RPM remains constant, what happens to the propeller blade angle of attack?
A.Angle of attack decreases because forward velocity vector increases relative to rotational velocity
B.Angle of attack increases because forward velocity adds directly to rotational speed
C.Angle of attack remains unchanged regardless of airspeed
D.Angle of attack shifts immediately to 90 degrees
Explanation: Relative airflow vector is the vector sum of forward aircraft speed and blade rotational speed. As forward speed increases with constant rotational speed, the relative airflow vector moves closer to the blade chord line, reducing the blade angle of attack. On constant speed propellers, the governor increases blade pitch to restore optimum angle of attack.
10What is the primary purpose of brass or copper tipping fitted to the leading edge and tip of a wooden propeller blade?
A.To protect the wood from erosion and impact damage caused by rain, gravel, and debris
B.To shift the center of gravity rearward to increase Aerodynamic Turning Moment
C.To act as a grounding conductor for de-icing electrical boots
D.To prevent the propeller from overspeeding during high pitch maneuvers
Explanation: Metal tipping (sheet brass, copper, or stainless steel) is countersunk and screwed/riveted to the leading edge and tip of wooden blades to protect the soft timber from erosion and impact damage by rain, stones, and runway gravel. Small drain holes are drilled in the extreme tip to release accumulated moisture.
About the CAAS SAR-66 Module 17 (Propeller) Practice Questions
Verified exam format metadata for CAAS SAR-66 Basic Knowledge Examination - Module 17 Propeller is pending. The practice questions above remain available while official exam length, timing, passing score, fee, and administrator details are reviewed.