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100+ Free CAAS SAR-66 Module 14 Propulsion Practice Questions
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2026 Statistics
Key Facts: CAAS SAR-66 Module 14 Propulsion Exam
24 Qs
Multiple-choice questions per exam sitting.
CAAS AC 66-13 Category B2 Matrix
30 Mins
Time allowed per exam sitting.
CAAS AC 66-13 Category B2
75%
Minimum passing score per SAR-66 module.
CAAS SAR-66 Appendix 1
S$87.20
Exam fee per basic knowledge subject (ANO 12th Sched. 2026).
CAAS Air Navigation Order
5 Syllabus Modules
From 14.1 Principles to 14.5 Warning Systems.
CAAS SAR-66 Module 14 Syllabus
CAAS SAR-66 Module 14 Propulsion is a 30-minute exam featuring 24 multiple-choice questions, requiring a 75% pass mark for CAAS Aircraft Maintenance Engineer (Category B2 Avionics) licensing in Singapore.
Sample CAAS SAR-66 Module 14 Propulsion Practice Questions
Try these sample questions to test your CAAS SAR-66 Module 14 Propulsion exam readiness. Each question includes a detailed explanation. Start the interactive quiz above for the full 100+ question experience with AI tutoring.
1In a gas turbine engine operating on the ideal Brayton cycle, which thermodynamic process occurs inside the combustion chamber?
A.Isentropic compression
B.Constant pressure heat addition
C.Isothermal expansion
D.Constant volume combustion
Explanation: The ideal Brayton cycle consists of two isentropic processes (compression and expansion) and two constant pressure (isobaric) processes. Heat addition in the combustion chamber occurs at substantially constant pressure while the gas expands volume and increases in temperature.
2An engine exhaust nozzle has a total pressure (Pt7) of 45 psia and the engine inlet total pressure (Pt2) is 15 psia. What is the indicated Engine Pressure Ratio (EPR)?
A.0.33
B.3.00
C.30.0
D.60.0
Explanation: Engine Pressure Ratio (EPR) is defined as the ratio of turbine discharge total pressure (Pt7 or Pt5) to compressor inlet total pressure (Pt2). EPR = Pt7 / Pt2 = 45 / 15 = 3.00.
3A turbofan engine ingests air at a mass flow rate of 120 kg/s. The aircraft is flying at a true airspeed of 150 m/s, and the exhaust gas exit velocity is 400 m/s. Assuming a fully expanded convergent nozzle (Pj = Pa), calculate the net thrust (Fn).
A.18,000 N
B.30,000 N
C.48,000 N
D.66,000 N
Explanation: Net thrust Fn = mass flow rate * (Vj - Va). Given mass flow = 120 kg/s, Vj = 400 m/s, and Va = 150 m/s: Fn = 120 * (400 - 150) = 120 * 250 = 30,000 N (30 kN).
4What happens to the net thrust produced by a gas turbine engine as aircraft flight altitude increases at a constant true airspeed and engine RPM?
A.Net thrust increases due to lower ambient temperature.
B.Net thrust decreases due to the primary effect of reduced ambient air density.
C.Net thrust remains constant because ram pressure recovery compensates for altitude loss.
D.Net thrust increases continuously up to the tropopause.
Explanation: Although lower ambient temperature at higher altitudes tends to increase air density and thermal efficiency, the decrease in ambient atmospheric pressure reduces total air density significantly. Consequently, the mass flow rate entering the engine drops, leading to an overall reduction in net thrust.
5The propulsive efficiency (eta_p) of a jet engine is expressed by which of the following mathematical relations, where Va is aircraft speed and Vj is jet velocity?
A.eta_p = (Vj - Va) / (Vj + Va)
B.eta_p = 2 * Va / (Vj + Va)
C.eta_p = Va^2 / Vj^2
D.eta_p = (Vj + Va) / (2 * Va)
Explanation: Propulsive efficiency measures how effectively kinetic energy imparted to the jet exhaust is converted into useful propulsive work on the airframe. The formula is eta_p = (2 * Va) / (Vj + Va). High bypass turbofans achieve high propulsive efficiency by keeping Vj closer to Va.
6In a dual-spool high bypass turbofan engine, the bypass ratio is defined as the ratio of:
A.Mass flow rate through the fan bypass duct to mass flow rate passing through the engine core.
B.Fuel mass flow rate to total ingested air mass flow rate.
C.Turbine exhaust gas velocity to compressor inlet air velocity.
D.Low pressure turbine work output to high pressure compressor power absorption.
Explanation: Bypass ratio (BPR) is the mass flow rate of air passing around the core engine through the bypass duct divided by the mass flow rate of air passing through the core engine (compressors, combustor, and turbines).
7Which change occurs to total air pressure and static air pressure as subsonic airflow passes through a divergent duct (diffuser) in an engine intake?
A.Static pressure increases, dynamic pressure decreases, and total pressure remains constant (ignoring friction).
B.Static pressure decreases, dynamic pressure increases, and total pressure increases.
C.Static pressure increases, dynamic pressure increases, and total pressure decreases.
D.Static pressure remains constant, while dynamic pressure and total pressure decrease.
Explanation: According to Bernoulli's principle and energy conservation, as subsonic airflow passes through a divergent duct, velocity decreases, causing dynamic pressure to drop while static pressure rises (diffuser action). Total pressure remains constant assuming frictionless flow.
8What is the primary operational advantage of a high-bypass turbofan over a turbojet engine producing equal total thrust?
A.Lower overall weight per unit of engine length
B.Lower Specific Fuel Consumption (SFC) and reduced noise emissions
C.Higher maximum exhaust gas velocity at supersonic flight speeds
D.Elimination of the low-pressure compressor and turbine spools
Explanation: High-bypass turbofans accelerate a larger mass of air to a lower velocity, which produces thrust more efficiently (higher propulsive efficiency). This results in significantly lower Specific Fuel Consumption (SFC) and substantially lower jet noise.
9If a gas turbine exhaust nozzle becomes choked under high pressure ratio conditions, what is the Mach number of the gas flow at the nozzle throat area?
A.Mach 0.5
B.Mach 0.85
C.Mach 1.0
D.Mach 2.0
Explanation: When an exhaust nozzle is choked, the pressure ratio across the nozzle exceeds the critical pressure ratio (~1.85 to 2.0 for hot exhaust gases), accelerating gas flow to local sonic speed (Mach 1.0) at the throat (minimum area).
10How does an increase in ram air pressure ratio (due to increasing forward aircraft speed) affect the overall performance of a gas turbine engine?
A.It decreases compressor air inlet density, reducing net thrust.
B.It increases compressor inlet total pressure (Pt2), increasing mass air flow and gross thrust.
C.It reduces turbine entry temperature, causing an immediate engine flameout.
D.It eliminates the necessity for compressor variable stator vanes.
Explanation: Forward velocity compresses incoming air at the intake (ram effect), raising Pt2 and air density. This increases the mass flow through the engine and generates higher gross thrust at high airspeed.
About the CAAS SAR-66 Module 14 Propulsion Practice Questions
Verified exam format metadata for CAAS SAR-66 Module 14 Propulsion (Category B2 Avionics) is pending. The practice questions above remain available while official exam length, timing, passing score, fee, and administrator details are reviewed.