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100+ Free CAAS SAR-66 Module 11A - Aeroplane Aerodynamics, Structures and Systems (Turbine) Practice Questions
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2026 Statistics
Key Facts: CAAS SAR-66 Module 11A - Aeroplane Aerodynamics, Structures and Systems (Turbine) Exam
140 Qs
Total multiple-choice questions on the Category B1.1 examination.
CAAS AC 66-13 Appendix A
175 Mins
Time duration allotted for Module 11A.
CAAS AC 66-13 Appendix A
75%
Minimum passing score required by CAAS.
CAAS SAR-66 Section 1
S$87.20
Examination fee per basic knowledge subject (ANO 12th Sched, 1 Jan 2026).
CAAS Air Navigation Order
Category B1.1
Licence subcategory for turbine-powered aeroplanes.
CAAS SAR-66 Appendix 1
CAAS SAR-66 Module 11A (Turbine Aeroplane Aerodynamics, Structures and Systems) is a 140-question, 175-minute examination with a 75% pass mark required for Category B1.1 AML certification in Singapore.
Sample CAAS SAR-66 Module 11A - Aeroplane Aerodynamics, Structures and Systems (Turbine) Practice Questions
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1What aerodynamic phenomenon occurs when an aircraft accelerates past its critical Mach number (Mcr)?
A.Airflow over the upper wing surface accelerates to supersonic speed, forming local shock waves.
B.The entire airframe instantly experiences supersonic flow from nose to tail.
C.Induced drag drops to zero as boundary layer separation is entirely suppressed.
D.The center of pressure moves rapidly forward toward the leading edge.
Explanation: Critical Mach number is the free-stream Mach number at which local airflow over the upper wing surface first reaches Mach 1.0. As speed increases beyond Mcr, local supersonic pockets develop, creating shock waves and wave drag. This also causes the center of pressure to shift aft.
2What is the primary function of wing sweepback on high-speed turbine aeroplanes?
A.It delays the onset of critical Mach number by reducing the effective spanwise curvature vector.
B.It increases low-speed maximum lift coefficient (CLmax) during takeoff and landing.
C.It eliminates the formation of wingtip vortices completely during cruise flight.
D.It reduces structural wing weight by increasing spar root depth.
Explanation: Wing sweepback reduces the component of airflow velocity perpendicular to the wing leading edge. By responding only to the normal velocity component, the wing behaves as if it is traveling at a lower Mach number, effectively delaying wave drag and shock wave formation.
3Which aerodynamic device is designed specifically to re-energize the boundary layer and delay airflow separation at high angles of attack?
A.Vortex generators
B.Trailing-edge trim tabs
C.Mach trim actuators
D.Ground spoilers
Explanation: Vortex generators are small vanes positioned perpendicular to the wing surface that draw high-energy air from outside the boundary layer down into the slow boundary layer. This delays airflow separation, preventing stall and improving control surface authority.
4What is 'Mach Tuck' and what causes it during high-subsonic flight?
A.A nose-down pitching tendency caused by the aft movement of the center of pressure as shock waves form on the wing.
B.A nose-up pitching moment resulting from loss of downwash over the tailplane at high angles of attack.
C.A rapid uncommanded yaw angle caused by asymmetric shock wave detachment on swept wingtips.
D.A high-frequency structural vibration caused by flutter in trailing-edge control surfaces.
Explanation: As an aircraft accelerates above Mcr, local shock waves cause the center of pressure to shift aft from its normal subsonic position. This aft movement increases the nose-down pitching moment (Mach Tuck), which is automatically compensated for by a Mach trim system.
5How do Krueger flaps differ from leading-edge slats in their deployment mechanism and aerodynamic operation?
A.Krueger flaps hinge forward and down from the lower leading edge, whereas slats extend forward and down creating a slotted duct for upper surface air.
B.Krueger flaps open slots for high-pressure air to flow over the lower wing surface, whereas slats deploy backward over the trailing edge.
C.Krueger flaps are used exclusively at high Mach numbers for wave drag reduction, whereas slats function only during emergency extension.
D.Krueger flaps are variable-camber trailing-edge devices, while slats are rigid leading-edge spoilers.
Explanation: Krueger flaps fold out from under the wing leading edge to increase nose camber and radius. Leading-edge slats extend forward to open a slot that directs high-pressure air over the upper wing surface to energize the boundary layer.
6In a swept-wing jet transport, why is spanwise boundary layer flow problematic at high angles of attack, and how is it mitigated?
A.Spanwise flow thickens the boundary layer at the wingtips leading to premature tip stall; wing fences or stall strips are used to block the lateral flow.
B.Spanwise flow concentrates boundary layer air at the wing root causing premature root stall; vortex generators are placed at the wing root.
C.Spanwise flow creates reverse flow over the elevator; anti-servo tabs are installed on the tailplane to counteract the turbulence.
D.Spanwise flow forces air outward into the engine intakes; intake bypass doors are used to bleed off boundary air.
Explanation: Sweepback causes boundary layer air to flow outward toward the wingtips. This accumulates low-energy air at the tips, inducing tip stall first (which causes pitch-up due to CP moving forward). Wing fences, chordwise slots, or stall strips physically impede this spanwise flow.
7Which type of structural classification applies to airframe components whose failure would result in catastrophic loss of the aeroplane?
A.Primary structure
B.Secondary structure
C.Tertiary structure
D.Non-load-bearing structure
Explanation: Primary structures carry critical flight, ground, or pressurisation loads; their failure would compromise structural integrity and result in catastrophic aircraft loss (e.g., wing spars, main wing-to-body fittings, primary pressure bulkheads).
8What defines a 'fail-safe' structural design philosophy in transport category aircraft?
A.Incorporating redundant load paths so that if one member fails, adjacent members safely support the redistributed load until detected during routine inspection.
B.Designing components with infinite fatigue life so they never crack or experience fatigue degradation throughout the airframe lifetime.
C.Replacing all metallic structural elements with composite honeycomb panels that resist all environmental corrosion.
D.Allowing primary structural components to deform plastically under normal limit loads without permanent yield.
Explanation: Fail-safe design ensures that structural failure of a single member or partial crack propagation will not cause immediate catastrophic structural collapse, because remaining redundant members absorb the redistributed load until detected.
9Which form of corrosion occurs in composite-to-metal joints when carbon fiber reinforced plastic (CFRP) comes into direct contact with aluminum alloys?
A.Galvanic corrosion
B.Intergranular corrosion
C.Stress corrosion cracking
D.Fretting corrosion
Explanation: Carbon fiber is noble (cathodic) relative to aluminum (anodic). Direct contact between CFRP and aluminum in the presence of an electrolyte causes severe galvanic corrosion of the aluminum. Isolation barriers such as fiberglass scrim cloth or sealant must be used.
10What is the key characteristic of 'damage tolerant' structural design mandated for modern turbine aircraft under SAR-25 / CS-25?
A.The structure is evaluated to show that fatigue cracks, manufacturing defects, or corrosion damage will be detected by planned NDT inspections before propagating to critical size.
B.The structure relies on mandatory replacement of components at strict life limits regardless of structural condition or inspection findings.
C.The airframe is designed to absorb ground bird strikes without experiencing any elastic deflection of outer skin panels.
D.All fuselage skin panels must be manufactured without lap joints or fastener holes to prevent stress concentrations.
Explanation: Damage tolerance relies on fracture mechanics and NDT inspection programs to ensure that any crack or damage remains stable and detectable during routine maintenance intervals before it reaches critical failure length.
About the CAAS SAR-66 Module 11A - Aeroplane Aerodynamics, Structures and Systems (Turbine) Practice Questions
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