Correct: B)
Explanation: The correct answer is B because the aircraft flight manual (AFM) is the authoritative document that specifies the approved operating categories, including whether aerobatic flight is permitted, and under what conditions and limitations. A is wrong because the certificate of airworthiness confirms the aircraft meets its type certificate but does not detail specific operational approvals. C is wrong because aerobatic approval is a formal certification requirement, not simply a matter of having an accelerometer installed. D is wrong because the operating envelope is contained within the AFM, not a separate standalone document.
Correct: C)
Explanation: The correct answer is C because the aircraft flight manual (AFM) is the official regulatory document that contains all operating limitations, loading data (mass and balance), performance charts, and operational procedures for a specific aircraft type. A is wrong because the logbook records maintenance and flight history, not operational limitations. B is wrong because technical communications (service bulletins) address modifications or issues, not standard operating data. D is wrong because the certificate of airworthiness confirms legal airworthiness status but does not contain detailed operating information.
]
- A) Altimeter, airspeed indicator, and netto variometer.
- B) Altimeter, airspeed indicator, and diaphragm variometer.
- C) Airspeed indicator, altimeter, and vane variometer.
- D) Airspeed indicator, altimeter, and oxygen pressure gauge.
Correct: C)
Explanation: The correct answer is C because the diagram shows, from left to right, the airspeed indicator (ASI), altimeter, and a vane variometer — the standard "basic T" arrangement in a glider cockpit. A and B incorrectly identify the order of the ASI and altimeter and misidentify the variometer type. D is wrong because an oxygen pressure gauge is a separate ancillary instrument typically mounted elsewhere, not part of the standard flight instrument panel layout.
Correct: D)
Explanation: The correct answer is D because on a glider's ASI, the white arc indicates the speed range within which camber flaps (positive flap settings) may be deployed. Operating flaps outside this range risks structural damage or adverse handling characteristics. A is wrong because maneuvering speed is a single value (VA), not an arc. B is wrong because the smooth-air caution range is the yellow arc. C is wrong because the range permitting full control deflection corresponds to the green arc (up to VA/VNO).
Correct: C)
Explanation: The correct answer is C because the airspeed indicator is a mandatory minimum instrument required for flight. The glider may only return to service once the ASI has been repaired or replaced and is fully functional. A is wrong because there is no regulatory provision allowing flight with a defective mandatory instrument for even one circuit. B is wrong because the unavailability of a maintenance organisation does not waive airworthiness requirements. D is wrong because a GPS ground speed indication cannot substitute for an ASI, which measures indicated airspeed based on dynamic pressure.
Correct: D)
Explanation: The correct answer is D because when the minimum useful load (typically minimum cockpit load) is not met, the C.G. may be outside the aft limit and the wing loading may be below the certified minimum. Adding lead ballast at the prescribed location (usually forward) brings the total load up to the minimum required value and positions the C.G. within limits. A is wrong because trim adjusts control forces but does not change the aircraft's mass or C.G. B is wrong because the seat position is fixed. C is wrong because the stabiliser incidence is not adjustable in flight or on the ground by the pilot.
Correct: C)
Explanation: The correct answer is C because the maximum mass is a hard certification limit based on structural strength and stall speed. When it is exceeded, the aircraft is no longer within its certified flight envelope and flight is prohibited until the excess load is removed. A is wrong because reducing speed does not address the structural overload risk. B is misleading — redistribution changes C.G. position but does not reduce total mass. D is wrong because trim adjustment has no bearing on mass limitations.
Correct: C)
Explanation: The correct answer is C because in a single-seat glider, the only practical way to move the C.G. is by changing the mass in the cockpit — adding or removing lead ballast at forward or aft positions, or by a different pilot weight. A is wrong because trim adjusts elevator deflection and control forces, not the physical mass distribution. B is wrong because angle of attack is an aerodynamic flight parameter, not a loading parameter. D is wrong because the angle of incidence is a fixed design feature of the wing and cannot be modified by the pilot.
Correct: D)
Explanation: The correct answer is D because an aft C.G. beyond the rear limit reduces the longitudinal static stability of the glider. As the C.G. moves closer to or behind the neutral point, the aircraft becomes neutrally stable or unstable in pitch, making it progressively harder to control until recovery from any pitch disturbance becomes impossible. A is less dangerous — a forward C.G. increases stability but may limit elevator authority for flaring. B and C are not standard concerns in glider mass-and-balance considerations.
Correct: D)
Explanation: The correct answer is D because the yellow arc on a glider's ASI marks the caution range between VNO (maximum structural cruising speed) and VNE (never-exceed speed). Flight within this speed range is permitted only in smooth, non-turbulent air because turbulence-induced loads at these speeds could exceed the structural design limits. A is wrong because full control deflection is permitted only up to VA (within the green arc). B is wrong because maneuvering speed is a single value, not a range. C is wrong because the flap operating range is shown by the white arc.
Correct: B)
Explanation: The correct answer is B because the Earth's magnetic field lines are not horizontal — they dip downward toward the magnetic poles at an angle that increases with latitude. This inclination causes the compass magnet assembly to tilt, introducing errors during turns (northerly turning error) and during accelerations/decelerations. A is wrong because temperature variations affect compass fluid viscosity but not the fundamental dip error. C is wrong because deviation is a separate error caused by ferromagnetic materials in the cockpit. D is wrong because acceleration errors are a consequence of dip, not the root cause.
Correct: C)
Explanation: The correct answer is C because yellow marks the caution range on an airspeed indicator, spanning from VNO to VNE. This range is reserved for smooth-air flight only. A (green) marks the normal operating range from VS1 to VNO. B (white) marks the flap operating range. D (red) is used only for the VNE radial line, not an arc. The colour coding is standardised across aviation to ensure immediate recognition.
Correct: C)
Explanation: The correct answer is C because in the International Standard Atmosphere, 1 hPa corresponds to approximately 8 metres of altitude near sea level (the "30 ft per hPa" rule). Increasing the subscale setting by 10 hPa (from 1000 to 1010) raises the displayed altitude by approximately 10 x 8 = 80 metres. B is wrong because the reading does change. D is wrong because increasing the QNH setting increases, not decreases, the displayed altitude. A is wrong because the conversion factor is fixed by the ISA model and does not depend on the actual QNH.
Correct: C)
Explanation: The correct answer is C because QFE is the atmospheric pressure measured at the aerodrome reference point. When this value is set on the altimeter subscale, the instrument reads zero on the ground at that aerodrome and indicates height above the aerodrome during flight. A is wrong because pressure altitude requires setting 1013.25 hPa. B is wrong because altitude above mean sea level requires setting QNH. D is wrong because the altimeter displays a dynamic reading during flight, not the fixed elevation of the airfield.
Correct: C)
Explanation: The correct answer is C because if the compensating (equalising) tank is oversized, it stores more pressure than intended, creating a larger pressure differential across the variometer restriction when altitude changes. This amplifies the indicated vertical speed, producing a reading that is too high (over-indication). A is wrong because the instrument will still function, just inaccurately. B is wrong because an oversized tank causes over-reading, not under-reading. D is wrong because the oversized tank does not create mechanical stress on the instrument.
Correct: B)
Explanation: The correct answer is B because a variometer (vertical speed indicator) compares the current atmospheric static pressure with the pressure retained in a reference chamber connected through a calibrated leak. As altitude changes, the instantaneous static pressure diverges from the stored (previous) pressure, and this differential drives the indication. A is wrong because the difference between total and static pressure is dynamic pressure, which is what the airspeed indicator measures. C and D are wrong because total pressure and dynamic pressure are not used in variometer operation.
Correct: C)
Explanation: The correct answer is C because Touring Motor Gliders (TMGs) are typically powered by four-cylinder, four-stroke piston engines such as the Rotax 912 or Limbach series, which offer a good balance of reliability, power-to-weight ratio, and fuel economy for sustained powered flight. A is wrong because two-stroke engines are less common in TMGs due to higher fuel consumption and lower reliability. B is wrong because Wankel rotary engines are not standard in certified TMG types. D is wrong because two-cylinder diesels lack the power output typically required for TMG operations.
Correct: D)
Explanation: The correct answer is D because the yellow arc on the ASI indicates the caution speed range (VNO to VNE), within which flight is only permitted in smooth air without gusts. At these higher speeds, turbulence-induced load factors could exceed structural design limits. A is wrong because flap/brake operating ranges are shown by the white arc. B is wrong because aerotow speeds are typically within the green arc. C is wrong because the best glide speed is a single point, not associated with the yellow arc.
Correct: C)
Explanation: The correct answer is C because a total-energy compensated variometer eliminates the effect of speed changes (kinetic energy exchanges) on the vertical speed indication. In a steady glide with constant airspeed, the TE variometer indicates the vertical movement of the surrounding air mass — showing zero in still air, or the actual thermal/sink value in moving air. A is wrong because that describes an uncompensated variometer. B and D are wrong because the TE variometer does not add or subtract airmass movement from the glider's vertical speed — it isolates the airmass movement itself.
Correct: D)
Explanation: The correct answer is D because during a right turn, a yaw string deflecting to the left indicates the nose is sliding outward (skidding turn) — there is insufficient rudder coordination and possibly too much bank for the rate of turn. To correct this, apply more right rudder (in the direction of the turn) to bring the nose around, and reduce bank slightly to decrease the tendency to skid. A and C are wrong because they call for less rudder, which would worsen the skid. B is wrong because adding more bank would increase the centripetal force demand and worsen the coordination problem.
Correct: C)
Explanation: Airworthiness of an aircraft is fundamentally determined by the structural integrity of load-bearing components (main spar, wing attachment, fuselage frames, control system attachment points). Damage to these parts compromises the aircraft's ability to sustain flight loads and constitutes a loss of airworthiness. A dirty leading edge (A) reduces performance but is not an airworthiness defect. A cracked canopy (B) and a scratch on paint (C) are cosmetic or minor defects that do not affect structural integrity.
Correct: C)
Explanation: The load sheet (weight and balance document) specifies a minimum pilot weight to ensure the centre of gravity remains within approved limits. If the actual pilot weight is below the minimum, ballast must be added (typically in the ballast area specified by the POH) to bring the total loaded mass up to the minimum required value. Adjusting trim (A, C) does not address the underlying CG/mass problem, and changing seat position (B) is not a standard corrective action for under-weight loading.
Correct: A)
Explanation: Minimum speed (stall speed) is proportional to the square root of wing loading: Vs ∝ √(W/S). If wing loading increases by 40% (factor 1.4), stall speed increases by √1.4 ≈ 1.183, i.e., approximately 18.3%. A 40% speed increase (B) would require a 96% increase in wing loading, 100% (A) would require a quadrupling of wing loading, and 200% (C) is far too large. Only the square-root relationship gives approximately 18%.
Correct: C)
Explanation: If the actual loaded mass exceeds the maximum allowed mass from the load sheet, the only correct action is to reduce the load (remove ballast, water ballast, baggage, or have a lighter pilot). Exceeding maximum mass means structural load limits may be reached at lower G-loads or airspeeds. Increasing speed (A) or adjusting trim (C, D) does not address the structural overload problem.
Correct: A)
Explanation: A torsion-stiffened leading edge is a structural design feature in which the leading edge of the wing (from the leading edge to the main spar) is planked (covered) on both upper and lower surfaces, creating a closed-section D-box that resists torsional (twisting) loads. This is not a spar component (A), not merely a shape descriptor (B), and not a reference to a torsion moment distribution point (C).
