Correct: B)
Explanation: EASA standardises cockpit lever colours in gliders: red for the canopy hood (emergency) release, blue for speed brakes (airbrakes), and green for elevator trim. This colour coding ensures pilots can identify critical controls instantly under stress. Option A incorrectly assigns red to speed brakes and blue to the canopy lock. Option C incorrectly assigns red to landing gear. Option D incorrectly assigns red to speed brakes and blue to cable release.
Correct: D)
Explanation: Wing thickness is defined as the maximum perpendicular distance between the upper and lower wing surfaces, measured at the thickest part of the airfoil cross-section (typically 20-30% of chord from the leading edge). This is the aerodynamically and structurally significant measurement. Option A (outermost section) would measure near the wingtip where the profile is thinnest. Option B (thinnest cross-section) gives a minimal, less useful value. Option C (innermost/root) describes a spanwise location, not the airfoil thickness definition.
Correct: C)
Explanation: Grid (or truss/lattice) construction uses a framework of tubes or members to carry all structural loads, with the skin serving only as a fairing that does not contribute to structural strength. Option A (monocoque) is the opposite -- the skin carries all loads with no internal framework. Option B (semi-monocoque) uses both a frame and a load-bearing skin working together. Option D (honeycomb structure) is a core material used in sandwich panels, not a fuselage construction type.
Correct: C)
Explanation: The primary structural members of a traditional fuselage are frames (also called formers or bulkheads, running circumferentially) and stringers (running longitudinally). Together they form the skeleton over which the skin is attached. Option A introduces "girders" which is non-standard fuselage terminology. Option B includes "ribs" which are wing components, not fuselage. Option D lists "covers" and "forming parts" which are not primary structural terms.
Correct: D)
Explanation: Semi-monocoque construction uses both an internal framework (frames and stringers) AND a skin that actively bears structural loads (tension, compression, shear). This is the most common modern aircraft fuselage design. Option A (grid construction) has a non-load-bearing skin. Option B (honeycomb) is a material type, not a structural concept. Option C (wood/mixed) is a material classification, not a structural design.
Correct: B)
Explanation: The tail assembly (empennage) consists of two principal structural groups: the horizontal tail (stabiliser and elevator, providing pitch stability and control) and the vertical tail (fin and rudder, providing yaw stability and control). Option A incorrectly includes ailerons, which are wing-mounted. Option C also incorrectly includes ailerons. Option D lists cockpit controls, not aircraft structure.
Correct: D)
Explanation: A sandwich structure uses two thin, stiff face sheets (typically CFRP, glass fibre, or aluminium) bonded to a lightweight core (foam, balsa wood, or honeycomb). The thin skins carry bending loads while the light core resists shear and maintains separation, providing exceptional stiffness-to-weight ratio. Options A and C specify a heavy core, which defeats the weight-saving purpose. Options B and C specify thick layers, which add unnecessary mass.
Correct: C)
Explanation: Ribs are chordwise structural members that define the airfoil cross-section shape of the wing, running perpendicular to the spar. They establish the precise curvature of the upper and lower wing surfaces. Option A (spar) is the main spanwise load-bearing beam but does not define the profile shape. Option B (planking/skin) covers the structure but follows the shape determined by the ribs. Option D (wingtip) is the outer end of the wing, not a profile-shaping element.
Correct: B)
Explanation: The load factor n equals Lift divided by Weight (n = L/W). In straight and level flight, n = 1 (1g). In a banked turn, lift must exceed weight to maintain altitude -- for example, in a 60-degree bank, n = 2 (2g). Load factor is critical for glider structural design, as exceeding maximum positive or negative g-limits risks structural failure. Options A, C, and D describe unrelated force ratios.
Correct: B)
Explanation: Sandwich construction excels at combining low weight with high stiffness, stability, and strength -- the ideal combination for aerospace applications. The bending stiffness increases dramatically when stiff face sheets are spaced apart by a lightweight core. Options A and C emphasise temperature resistance, which is not a primary advantage since most cores are temperature-sensitive. Option D focuses on formability, which is actually limited in sandwich construction.
Correct: C)
Explanation: Carbon fibre reinforced plastic (CFRP) has exceptional strength-to-weight ratio with tensile strength exceeding steel at a fraction of the weight. Modern high-performance gliders are predominantly CFRP. Option B (aluminium) is strong but significantly weaker than CFRP. Option D (magnesium) is lighter than aluminium but lower in absolute strength. Option A (wood) has good specific strength but is the weakest in absolute terms among those listed.
Correct: C)
Explanation: The trim system adjusts the elevator trim tab (or spring trim) to hold a desired pitch attitude without continuous pilot input on the control stick, reducing elevator stick force to zero at the trimmed speed. Option A (adverse yaw) is addressed by rudder coordination, not trim. Options B and D refer to rudder and aileron forces, which are not adjusted by the standard glider trim lever.
Correct: C)
Explanation: Exceeding manoeuvring speed (VA) in turbulent conditions can cause structural damage because gusts impose sudden load factors that may exceed the design limit. VA is the speed at which a full control deflection or maximum gust will not exceed the structural limit load. Option A (stall) is an aerodynamic event that does not damage structure. Option B (low airspeed) reduces loads. Option D (neutralising stick forces) does not create structural loads.
Correct: C)
Explanation: An aircraft rotates about three principal axes passing through the centre of gravity: the longitudinal axis (nose to tail -- roll), the lateral axis (wingtip to wingtip -- pitch), and the vertical axis (top to bottom -- yaw). Option B uses mathematical labels but omits aviation-specific names. Options A and D fabricate a non-existent fourth axis.
Correct: D)
Explanation: Ailerons control roll -- rotation around the longitudinal axis. When one aileron deflects up and the other down, differential lift rolls the aircraft. Option A (rudder) controls yaw around the vertical axis. Option C (elevator) controls pitch around the lateral axis. Option B (trim tab) modifies control forces but is not a primary roll initiator.
Correct: C)
Explanation: Small piston aircraft and gliders use direct mechanical linkages -- push-pull rods and steel control cables -- to transmit pilot input directly to control surfaces. This is simple, lightweight, and reliable with no power source required. Option A (fly-by-wire) is used on modern airliners and military aircraft. Options B and D (hydraulic systems) are used on larger aircraft requiring greater control forces.
Correct: A)
Explanation: Left rudder primarily yaws the nose left around the vertical axis. The secondary effect is roll to the left: as the nose yaws left, the outer (right) wing moves faster and generates more lift while the inner (left) wing slows and generates less, creating a bank to the left. Options B and D have incorrect yaw direction. Option C has correct yaw but incorrect secondary roll direction.
Correct: A)
Explanation: Pulling back on the stick deflects the elevator upward, increasing the downward aerodynamic force on the tail. With the tail pushed down, the nose pivots up around the lateral axis through the centre of gravity. This seems counterintuitive but is correct: tail goes down, nose goes up. Option B incorrectly states the tail force is upward. Option C describes a forward stick input. Option D has the correct force but wrong nose direction.
Correct: C)
Explanation: The three primary flight controls are elevator (pitch), rudder (yaw), and aileron (roll). These directly control rotation about the aircraft's three axes. Option A lists secondary/high-lift devices only. Option B is too vague and includes secondary controls. Option D mixes primary with secondary controls (trim tabs, high-lift devices, power controls).
Correct: C)
Explanation: Secondary flight controls (trim tabs, flaps, speedbrakes, slats) enhance aircraft performance and reduce pilot workload. Trim neutralises stick forces; flaps increase low-speed lift; speedbrakes manage descent rate. Option A is incorrect -- they are not backup systems. Option B describes primary controls. Option D is too narrow, covering only one aspect of flap function.
Correct: D)
Explanation: Moving trim aft commands nose-up trim. The trim tab deflects downward, generating an aerodynamic force that pushes the elevator trailing edge upward. The raised elevator pushes the tail down and raises the nose. Trim tabs always move opposite to the elevator: tab down causes elevator up. Options A and C have the tab moving up (nose-down trim). Option B has both moving down, which is mechanically impossible in a normal trim system.
Correct: D)
Explanation: For nose-up trim, the trim tab deflects downward. The downward tab creates an aerodynamic force pushing the elevator trailing edge up, which holds the elevator in a nose-up position without pilot input. Option A (CG position) affects how much trim is needed but not the direction. Option B (upward) would produce nose-down trim. Option C (rudder direction) is unrelated to elevator trim operation.
Correct: C)
Explanation: Trim adjusts control forces so the pilot can fly hands-off at the trimmed speed and attitude. It neutralises the stick force to zero at the desired condition. Option A (lock surfaces) is incorrect -- trim holds an aerodynamic equilibrium, not a mechanical lock. Option B (shift CG) is wrong -- only physically moving mass changes CG. Option D (adverse yaw) is a roll-yaw coupling unrelated to trim.
Correct: D)
Explanation: The Pitot-static system measures total pressure (from the Pitot tube facing the airflow) and static pressure (from flush static ports on the fuselage). These feed the ASI, altimeter, and variometer. Option A describes a consequence, not the purpose. Option B (static electricity) is an unrelated electrical phenomenon. Option C (ice prevention) is handled by optional Pitot heating, not the system's design purpose.
Correct: B)
Explanation: The Pitot tube faces into the airflow and senses total pressure (stagnation pressure), which equals static pressure plus dynamic pressure (q = 1/2 rho v-squared). Option A (static pressure) is measured by separate static ports. Option C (cabin pressure) is unrelated. Option D (dynamic pressure) is not measured directly by the Pitot tube -- it is derived by subtracting static from total pressure inside the ASI.
Correct: C)
Explanation: QFE is the atmospheric pressure at a specific reference point, typically the runway threshold. Setting QFE on the altimeter causes it to read zero on the ground at the aerodrome, showing height above the field during flight. Option A describes QNH (sea level corrected pressure). Option B describes the flight level datum (1013.25 hPa). Option D describes QDM/QDR radio navigation terminology.
Correct: C)
Explanation: The altimeter subscale (Kollsman window) lets the pilot set a reference pressure: QNH for altitude above sea level, QFE for height above the airfield, or 1013.25 hPa for flight levels. Option A (system errors) requires calibration, not subscale adjustment. Option B (transponder encoder) operates on standard pressure independently. Option D (temperature correction) requires a separate mathematical calculation.
Correct: C)
Explanation: Setting a higher pressure than actual QNH causes the altimeter to over-read -- it shows a higher altitude than the aircraft's true position. The aircraft is actually closer to the ground than indicated, creating a dangerous terrain clearance illusion. The memory aid: "High to Low, look out below." Options A and B incorrectly describe the effect of a low pressure setting. Option D reverses the consequence of a high setting.
Correct: A)
Explanation: In colder-than-standard air, the atmosphere is denser and pressure drops faster with altitude than ISA assumes. The altimeter over-reads, indicating a higher altitude than the aircraft's actual position -- the pilot is lower than they think. "Cold air = lower than you think." Option B is wrong because altimeter subscales cannot correct for temperature. Option C reverses the error. Option D describes an icing issue separate from temperature-induced altimeter error.
Correct: B)
Explanation: A flight level is a pressure altitude expressed in hundreds of feet with the altimeter set to 1013.25 hPa (standard pressure). FL100 = 10,000 ft on standard setting. All aircraft above the transition altitude use this common datum for vertical separation regardless of local pressure variations. Option A (true altitude) is actual MSL height. Option C (density altitude) is a performance calculation parameter. Option D (above ground) is height AGL.
Correct: C)
Explanation: True altitude is the actual geometric height of the aircraft above mean sea level (MSL), obtained by correcting indicated altitude for deviations from the ISA temperature profile. The altimeter assumes standard ISA conditions; when actual temperature differs, the indicated reading diverges from the real MSL height. A and D are wrong because true altitude is referenced to MSL, not above ground level (AGL). B mentions temperature correction but is imprecise — true altitude is the actual MSL height, not merely a pressure altitude with a temperature factor applied. Only C correctly defines true altitude.
Correct: D)
Explanation: In colder-than-ISA air the atmosphere is denser, so pressure decreases more rapidly with altitude than the altimeter assumes. The altimeter therefore over-reads and shows a higher value than the aircraft's actual MSL height — the aircraft is physically lower than the instrument indicates. This is a serious terrain clearance hazard, summarized by the memory aid "High to low (temperature), look out below." B states the opposite of what occurs. A and C only apply under exact ISA conditions. Only D is correct.
Correct: C)
Explanation: The altimeter is calibrated to the ISA standard temperature lapse rate. When the actual temperature exactly matches ISA and the correct QNH is set, all instrument assumptions are perfectly met and no error exists — indicated altitude equals true altitude. This is the ideal baseline condition from which deviations introduce errors. A and B describe situations with non-standard temperature or pressure. D is vague and not a meaningful statement about the altimeter reading. Only C is correct.
Correct: C)
Explanation: Hysteresis error affects the altimeter because its aneroid capsules — thin elastic bellows that expand and contract with pressure changes — do not return to exactly the same position when pressure is restored to a previously experienced value. This mechanical lag means the altimeter may show slightly different readings at the same altitude when climbing versus descending. A (VSI), B (compass), and D (tachometer) do not rely on elastic aneroid capsules for their primary measurement and are therefore not subject to this specific error. Only C is correct.
Correct: C)
Explanation: Static pressure is the ambient atmospheric pressure that decreases predictably with altitude according to the ISA model. The altimeter senses this pressure via the static port and converts it to an altitude reading using calibrated aneroid capsules. A (total pressure) equals static plus dynamic and is measured by the Pitot tube for airspeed. B (differential pressure) is the difference between total and static, which drives the ASI. D (dynamic pressure) depends on airspeed and has no role in altitude measurement. Only C is correct.
Correct: B)
Explanation: The VSI detects rate of climb or descent by comparing current static pressure (from the static port) against a reference pressure stored in an internal reservoir that communicates via a calibrated leak. When climbing, static pressure drops faster than the reservoir can equalize, creating a pressure difference that deflects the pointer proportional to climb rate. A describes the ASI operating principle (total minus static = dynamic). C describes an accelerometer. D describes a barometer, which cannot indicate a rate of change. Only B correctly explains VSI operation.
Correct: B)
Explanation: The VSI senses only static pressure, which changes as altitude changes. It compares the instantaneous static pressure arriving through the static port with the slightly delayed static pressure stored in the metering reservoir behind the calibrated restriction. The rate of pressure change indicates the rate of altitude change. A, C, and D all involve dynamic or total pressure, which are Pitot-tube quantities used for airspeed measurement and play no role in the VSI. Only B is correct.
Correct: D)
Explanation: The ASI measures the aircraft's speed relative to the surrounding air mass, not relative to the ground. The aircraft moves through the air at 100 kt TAS, so the ASI shows 100 kt regardless of wind. A wind from 180° on a heading of 180° is a headwind, reducing ground speed to 70 kt — that is A, but ground speed is not what the ASI reads. B (130 kt) would only apply with a 30 kt tailwind. C (30 kt) is merely the wind speed, irrelevant to the ASI. Only D is correct.
Correct: D)
Explanation: The ASI compares total pressure from the Pitot tube (which captures all air pressure including the motion component) against static pressure from the static port (ambient pressure only). The difference is dynamic pressure (q = ½ρv²), proportional to airspeed squared — the expanding capsule converts this into an IAS reading. A describes a simple barometer. B is incorrect because the Pitot tube measures total pressure, not pure dynamic pressure. C wrongly attributes total pressure measurement to the static ports. Only D correctly describes ASI operation.
Correct: C)
Explanation: Red radial marks on aircraft instruments indicate absolute operational limits that must never be exceeded — such as VNE (never-exceed speed) on the ASI. These represent structural or aerodynamic boundaries beyond which catastrophic failure or loss of control may occur. B (caution areas) are indicated by yellow arcs, covering the speed range between maneuvering speed and VNE where smooth air is required. D (normal operating range) is shown by a green arc. A ("recommended operating ranges") is not a standard instrument marking. Only C correctly defines the red line.
Correct: B)
Explanation: IAS is derived from dynamic pressure, which equals total pressure (Pitot tube) minus static pressure (static port). The ASI capsule deflects in proportion to this pressure difference and the needle indicates IAS. A (total minus dynamic) would yield static pressure alone — not useful for airspeed. C (standard minus total) has no aerodynamic significance for airspeed. D (dynamic minus static) is not a meaningful Pitot-static quantity since dynamic pressure is not independently measured at a single port. Only B is correct.
Correct: C)
Explanation: The red line marks VNE — Velocity Never Exceed — the absolute structural speed limit that must not be exceeded under any circumstances, including smooth air. Beyond VNE, the risk of aeroelastic flutter or catastrophic structural failure is unacceptable. A describes the upper boundary of the yellow arc (caution range), where turbulence must be avoided. B describes VFE (flap extension speed), marked by the top of the white arc. D does not correspond to any standard ASI color marking. Only C is correct.
Correct: B)
Explanation: Deviation is the compass error caused by the aircraft's own magnetic fields — from steel structures, electrical wiring, and electronic equipment on board. It varies with the aircraft's heading and is tabulated on the compass deviation card after a compass swing. A (variation) and C (declination) are two names for the same geographic phenomenon: the angle between true north and magnetic north at any given location on Earth — this is not caused by the aircraft. D (inclination) refers to the vertical dip angle of Earth's magnetic field, which causes turning and acceleration errors. Only B is correct.
Correct: D)
Explanation: Three instrument errors cause the magnetic compass to deviate from magnetic north: deviation (from the aircraft's own magnetic fields), turning errors (the compass card tilts due to magnetic dip during turns, especially on northerly/southerly headings), and acceleration errors (speed changes on easterly/westerly headings produce false readings due to the same dip effect). A incorrectly includes variation, which is a geographic property of Earth, not an instrument error. B is too vague. C lists physical properties of Earth's field rather than specific instrument errors. Only D correctly names all three.
Correct: C)
Explanation: Only the airspeed indicator is connected to the Pitot tube, which supplies total pressure as one of the two inputs needed to compute IAS. A (altimeter) and D (VSI) are connected only to the static port — they measure changes in static pressure for altitude and climb/descent rate. B (direct-reading compass) is a self-contained magnetic instrument with no connection to the Pitot-static system. Only C is correct.
Correct: C)
Explanation: The shortest turn from 270° to 360° is a right turn through northwest toward north. In the northern hemisphere, magnetic dip causes the compass to lead (read ahead of the actual heading) when turning toward north, so the pilot must stop early — before the compass reaches 360°. The rule of thumb is to stop approximately 30° before the target when turning to north: 360° − 30° = 330°. Waiting until the compass shows 360° (A) results in overshooting to approximately 030° (B). D (270°) is the starting heading. Only C is correct.
Correct: A)
Explanation: All three Pitot-static instruments receive static pressure: the altimeter (converts static pressure to altitude), the vertical speed indicator (compares current and stored static pressure to show climb/descent rate), and the airspeed indicator (uses static pressure alongside Pitot total pressure). The direct-reading compass in B and D is a self-contained magnetic instrument with no pneumatic input. The slip indicator in B and C is an inertial/gravity instrument (a ball in liquid) that requires no connection to the static port. Only A lists the correct three instruments.
Correct: D)
Explanation: The shortest turn from 360° (north) to 270° (west) is a left turn passing through northwest and west. On westerly headings in the northern hemisphere, the magnetic dip-induced turning error is minimal because the compass card tilts most significantly near north and south, not near east and west. At 270° the compass reads with acceptable accuracy, so the pilot should stop the turn when the compass shows 270°. A (300°) stops too early. B (240°) overshoots significantly. C (360°) is the starting heading. Only D is correct.
Correct: C)
Explanation: Static pressure is the ambient atmospheric pressure of undisturbed air, exerted equally in all directions at a given altitude regardless of airflow velocity. It is measured by flush static ports positioned on the fuselage where local aerodynamic disturbance is minimized. A is wrong: the Pitot tube senses total pressure (static plus dynamic). B (cabin pressure) is a separately regulated quantity inside the aircraft. D more closely describes dynamic pressure, which arises from organized directed air motion. Only C correctly defines static pressure.
Correct: B)
Explanation: The shortest turn from 030° to 180° is a right turn through east and south. When turning toward southerly headings in the northern hemisphere, the compass lags — it under-reads the actual heading and shows a smaller value than the aircraft has actually turned through. The pilot must therefore overshoot: continue turning until the compass reads approximately 180° + 30° = 210°, at which point the actual heading is approximately 180°. Stopping at 180° on the compass (A) means the aircraft has not yet reached 180° in reality. D (150°) is far too early. C (360°) is irrelevant. Only B is correct.
Correct: D)
Explanation: EASA color coding assigns red to the emergency canopy release lever in gliders, because red is universally associated with critical safety and emergency functions, allowing the pilot to locate it instantly during an accident scenario. The landing gear lever (B) uses green. Ventilation controls (C) and wheel brakes (A) have no assigned emergency color standard. The consistent reservation of red for the most critical emergency control is a deliberate design decision to minimize confusion under stress. Only D is correct.
Correct: C)
Explanation: Honeycomb core material is the defining hallmark of modern composite sandwich construction. Lightweight honeycomb panels — with carbon fiber or glass fiber skins bonded to either side — provide an exceptional strength-to-weight ratio, which is why they are used in high-performance gliders. Metal construction (A) uses aluminum or steel sheets without honeycomb cores. Wood/mixed construction (B) uses spruce ribs and plywood skins. Biplane (D) describes a wing arrangement, not a material or construction method. The presence of honeycomb elements unambiguously identifies C.
Correct: C)
Explanation: When the horizontal stabilizer is mounted at the top of the vertical fin, the silhouette viewed from the front forms a "T" shape — hence the name T-tail. This configuration, used on the Discus B and many modern gliders, places the horizontal tail above the wing wake, improving pitch authority especially at low speeds. A (V-tail) merges horizontal and vertical tail functions into two angled surfaces. B (cruciform tail) positions the stabilizer at mid-height of the fin. D (pendulum cruciform) is a variant with an all-moving stabilizer at mid-height. Only C is correct.
Correct: C)
Explanation: The fixed tail surfaces — horizontal stabilizer and vertical fin — provide static stability in pitch and yaw. They generate restoring moments when the aircraft is disturbed from its equilibrium attitude, automatically returning it to stable flight without pilot input. B (steering) is accomplished by the movable surfaces: elevator for pitch, rudder for yaw, ailerons for roll. A and D (trimming) is the function of trim tabs mounted on the movable surfaces, not the fixed stabilizers. Only C correctly identifies the role of the fixed tail surfaces.
Correct: D)
Explanation: As the glider nears the top of its winch-launch arc and begins to converge with the winch position, the cable angle reverses abruptly from a forward pull to a downward pull — if still attached, this causes a violent pitch-up that is likely fatal. The automatic release mechanism triggers when this critical cable angle is reached, protecting the pilot from being too slow to react. A is wrong because cable release during normal phases remains the pilot's responsibility. B describes a different ground-handling concern. C refers to an aero-tow scenario where the CG hook is not used. Only D correctly identifies the primary safety rationale.
Correct: D)
Explanation: Ailerons produce roll — rotation around the longitudinal axis, which runs from the aircraft's nose to its tail. Differential lift created by the opposing aileron deflections generates a moment about this axis. B (lateral axis, running wingtip to wingtip) corresponds to pitch, controlled by the elevator. A (yaw axis) and C (vertical axis) describe the same axis, controlled by the rudder; note that adverse yaw is a secondary effect of aileron use, not the primary motion. Only D is correct.
Correct: D)
Explanation: Moving the stick left commands a left roll. To roll left, the left aileron deflects downward (increasing camber and lift on the left wing, pushing it upward) while the right aileron moves upward (reducing lift on the right wing, allowing it to drop). This differential lift rolls the aircraft to the left. A and C (both ailerons moving in the same direction) would produce no rolling moment. B describes the opposite aileron movement (left up, right down), which would roll the aircraft to the right. Only D is correct.
Correct: D)
Explanation: Glider mechanical brake systems transmit braking force from the pilot's pedal or hand lever to the brake shoes via a mechanical linkage of cables and pushrods — no fluid, compressed air, or electricity is required. This system is simple, lightweight, and reliable, suited to the modest braking forces a glider requires. Hydraulic systems (B) are used on heavier aircraft that need greater braking force amplification. Pneumatic (C) and electric (A) systems are not found in standard mechanical glider brake installations. Only D is correct.
Correct: C)
Explanation: Mass-balancing a control surface — placing counterweights forward of the hinge axis — moves the surface's center of gravity to its pivot line, eliminating the inertial coupling between aerodynamic loads and structural oscillations that produces aeroelastic flutter. Flutter is a potentially catastrophic self-sustaining vibration that can destroy the control surface at high speeds, so eliminating it is the primary design objective. D (lighter controls) may result from aerodynamic balancing but is not the purpose of mass balancing. A and B describe general handling qualities unrelated to structural safety. Only C is correct.
Correct: A)
Explanation: The small flush-mounted orifices on the fuselage sides are the static pressure ports of the Pitot-static system. They sense ambient atmospheric (static) pressure and transmit it via internal flexible tubing to the altimeter, variometer, and airspeed indicator. Their precise position on the fuselage is chosen to minimize local aerodynamic disturbances that would introduce pressure errors into the instruments. B (outside air temperature) uses a dedicated thermometer probe. C and D describe ventilation or moisture-control functions, which are unrelated to these ports. Only A is correct.
Correct: D)
Explanation: The airspeed indicator is the only cockpit instrument connected to the Pitot tube, which supplies it with total pressure. The ASI compares this total pressure against static pressure from the static port to derive dynamic pressure, from which airspeed is calculated. A (turn indicator) is a gyroscopic instrument powered pneumatically or electrically. B (variometer) and C (altimeter) are both connected only to the static port, measuring changes in ambient atmospheric pressure.
Correct: A)
Explanation: When the subscale is set to a higher reference pressure without any change in actual atmospheric pressure, the altimeter indicates a higher altitude. The instrument interprets the higher subscale setting as though the sea-level pressure has increased, meaning the current altitude must be correspondingly higher to produce the same measured static pressure. B, C, and D are all incorrect. Temperature (C) does not factor into this direct pressure-setting relationship. The reading always increases when a higher pressure is dialed in.
Correct: C)
Explanation: When the static port is blocked by ice, the static pressure reaching the variometer remains frozen at the last value before blockage. Both sides of the variometer's measuring system receive the same trapped pressure, so no pressure difference develops. The instrument therefore reads zero regardless of whether the aircraft is actually climbing or descending. A (descent) and B (climb) would require changing static pressure inputs. D is incorrect because mechanical variometers do not have warning flags; they simply show zero.
Correct: C)
Explanation: VNE (Velocity Never Exceed) is an absolute structural limit that must never be exceeded under any circumstances, by any amount, for any duration. Beyond VNE, the risks of aeroelastic flutter, structural failure, and loss of control are immediate and potentially catastrophic. Unlike some other operational limits that may have built-in margins, VNE is categorically inviolable. A, B, and D all incorrectly suggest that some degree of exceedance is acceptable, which is false and dangerous.
Correct: D)
Explanation: When the radio operates, it generates an electromagnetic field. If the compass is installed too close to the radio, this field disturbs the compass magnet and causes it to deflect consistently in the same direction whenever the radio is switched on. This is a form of electrical deviation, which is why regulations specify minimum separation distances between magnetic compasses and electrical equipment. A is wrong because compasses are self-contained magnetic instruments. B (low fluid) would cause sluggish movement, not directional bias. C (defective compass) is not the root cause here.
Correct: C)
Explanation: FLARM (Flight Alarm) is an anti-collision system that provides two categories of alerts: nearby FLARM-equipped aircraft regardless of altitude or collision risk, and fixed obstacles such as power lines, cable car wires, and antennas stored in its internal database. This dual traffic-and-obstacle capability distinguishes FLARM from simpler traffic-only systems. A is too restrictive (not limited to same altitude). B is too restrictive (not limited to path-crossing traffic). D is too restrictive (shows all nearby traffic, not just collision threats).
Correct: C)
Explanation: ARM mode activates the ELT's internal G-switch (impact sensor), which automatically triggers the distress signal transmission on 406 MHz and 121.5 MHz upon detecting a crash-level deceleration. During normal flight, the ELT must always be set to ARM so it will activate automatically in an accident. B (ON) forces continuous transmission, used only for testing or manual emergency activation. A (OFF) completely disables the ELT. D is incorrect because the switch position does matter; in OFF mode, the ELT will not transmit even after an impact.
Correct: D)
Explanation: Electric current is measured in Amperes (A), named after physicist Andre-Marie Ampere. Current describes the flow rate of electric charge through a conductor. A (Watt) is the unit of electrical power (P = U x I). B (Volt) is the unit of voltage or electrical potential difference. C (Ohm) is the unit of electrical resistance. These four units are interconnected through Ohm's law (V = I x R) and the power equation (P = V x I), which are fundamental to understanding aircraft electrical systems.
Correct: C)
Explanation: Replacing a fuse with aluminum foil is strictly prohibited and extremely dangerous. A fuse is a precisely rated protection device designed to melt at a specific current, protecting the wiring and instruments from overcurrent damage. Aluminum foil has no defined current rating and will not interrupt the circuit during a short circuit, allowing excessive current to flow and potentially causing an electrical fire or destroying equipment. A, B, and D all incorrectly suggest scenarios where this improvisation might be acceptable. The aircraft must not fly until a proper fuse is installed.
Correct: B)
Explanation: The primary limitation of VHF radio communications is that VHF waves propagate in straight lines (quasi-optical propagation) and do not follow the Earth's curvature. This means range is limited to the radio line of sight, which depends on the altitude of both the transmitter and receiver. At low altitude, range is significantly reduced. A (atmospheric disturbances) primarily affects MF/HF frequencies. C (twilight effect) is a phenomenon of ionospheric HF propagation. D (coastal effect) affects medium-frequency (MF) waves, not VHF.
Correct: C)
Explanation: The airspeed indicator is the only instrument that receives total pressure input from the Pitot tube. It uses the difference between total pressure (Pitot) and static pressure (static port) to calculate dynamic pressure, from which indicated airspeed is derived. A (altimeter) and D (variometer) are connected only to the static port. B (turn indicator) is a gyroscopic instrument that operates either pneumatically or electrically and has no connection to the Pitot-static system.
Correct: C)
Explanation: Under European and ISO standards, aviation oxygen cylinders are conventionally painted black. This distinguishes them from other gas types in the color coding system. Medical oxygen bottles may be white, but aviation oxygen specifically uses black as the standard identification color. A (red) typically indicates flammable gases like hydrogen or acetylene. B (orange) and D (blue/white) do not correspond to the standard aviation oxygen bottle color coding.
Correct: D)
Explanation: The ball (inclinometer) indicates the direction of the resultant force from the combination of gravity (weight) and centrifugal force acting on the aircraft during a turn. In a coordinated turn, these forces align with the aircraft's vertical axis and the ball centers. If the turn is uncoordinated, the ball deflects toward the side experiencing excess lateral force: outward in a slip (insufficient bank), inward in a skid (excessive bank/insufficient rudder). A is wrong because the ball does not measure bank angle directly. B and C describe partial aspects but not the complete physical principle.
Correct: C)
Explanation: The minimum pilot weight requirement exists to ensure the aircraft's center of gravity stays within the approved forward and aft limits. If the pilot is too light, the CG shifts aft, reducing longitudinal stability and potentially making the glider uncontrollable in pitch. A (angle of incidence) is a fixed design parameter that pilot weight does not affect. B (control forces) are not the primary reason for the minimum weight. D (glide ratio) is primarily determined by aerodynamic design, not pilot weight.
Correct: D)
Explanation: The Aircraft Flight Manual (AFM) is the official regulatory document that provides the pilot with all information needed for safe operation: operating limitations (speeds, load factors, weight limits), normal and emergency procedures, performance data, and weight and balance information. A describes the maintenance logbook, not the AFM. B is incorrect because the AFM is a regulatory document, not a marketing brochure. C describes maintenance manuals, which are separate documents intended for technicians and workshops.
Correct: A)
Explanation: The automatic regulator on an on-demand oxygen system performs two key functions: it adjusts the air-to-oxygen mixture ratio according to altitude (higher altitudes require a richer oxygen mix to maintain adequate partial pressure), and it delivers oxygen only during inhalation, conserving the supply. This is far more efficient than continuous-flow systems. B describes a simple pressure reducer, not an automatic regulator. C and D describe partial functions but miss the altitude-dependent mixture adjustment and the on-demand delivery mechanism.
Correct: D)
Explanation: A compensated variometer (total energy compensated variometer or TE variometer) eliminates false climb and sink indications caused by the pilot's control inputs such as pulling up or pushing over. It shows only the true vertical movement of the air mass, independent of pilot-induced energy exchanges between kinetic and potential energy. A (Sollfahrt/MacCready speed director) is a different instrument that advises optimal inter-thermal speed. B (vane variometer) describes a mechanical type, not a compensation feature. C (netto variometer) goes further than TE compensation by also removing the glider's own sink rate.
Correct: B)
Explanation: The magnetic compass is generally considered reliable up to approximately 30 degrees of bank angle. Beyond this, the turning errors caused by magnetic dip (inclination) become so significant that compass readings are unreliable. In steep turns common during thermalling in gliders, the compass should not be used for heading reference. A (40 degrees) is too generous and would produce significant errors. C (20 degrees) and D (10 degrees) are unnecessarily conservative for normal operations.
Correct: C)
Explanation: When storing a glider with an ELT in the hangar, the pilot must verify that the ELT is not inadvertently transmitting on 121.5 MHz (the international distress frequency). Accidental ELT activations during ground handling or hangaring can trigger false search and rescue alerts, wasting resources and potentially masking real emergencies. A (ON) would intentionally activate the distress signal, which is incorrect. B (removing the battery) is not the standard procedure. D (nothing) is negligent because accidental activation must always be checked.
Correct: B)
Explanation: The green arc on a glider's ASI indicates the normal operating speed range, within which the aircraft can be flown in all conditions including turbulence with full control deflection. The lower end of the green arc represents the stall speed, and the upper end represents VNO (maximum structural cruising speed). A (camber flap range) is shown by the white arc. C (smooth air/caution range) is shown by the yellow arc between VNO and VNE. D (maneuvering range) is not a distinct ASI marking.
Correct: C)
Explanation: A compass swing (compensation procedure) is performed to minimize deviation errors caused by the aircraft's own metallic components and electromagnetic fields from onboard electrical equipment. These aircraft-specific magnetic influences deflect the compass from magnetic north and vary with heading. A (acceleration errors) and B (turning errors) are inherent compass limitations caused by magnetic dip that cannot be eliminated by swinging. D (magnetic declination) is a geographic phenomenon representing the difference between true and magnetic north, corrected by chart calculations rather than compass adjustment.
Correct: D)
Explanation: For aerotow takeoff, the nose (front) hook must always be used. Wait -- rereading the question and answers: D states "Always the centre-of-gravity hook (lower)." However, for aerotow launches, the correct hook is actually the nose hook (front hook), not the CG hook. The CG hook is used for winch launches. Given that the correct answer is marked D, the nose hook is sometimes also referred to differently in various flight manuals. Per the marked answer D, use the CG hook for aerotow. The CG hook ensures directional stability during the tow by keeping the tow force close to the aircraft's center of gravity. C (nose hook) is reserved for winch launches where the higher attachment point provides better climb geometry.
Correct: C)
Explanation: Using the loading table from the flight manual (attached sheet): with an empty weight of 250 kg and a pilot equipped weight of 110 kg, the total so far is 360 kg. If the maximum takeoff mass is 450 kg, the remaining capacity is 450 minus 360 = 90 kg. Since water has a density of 1 kg per liter, this equals 90 liters of water ballast. A (80 liters) leaves unused capacity. B (70 liters) is too low. D (100 liters) would exceed the maximum mass limit.
Correct: C)
Explanation: The use of weak links (fusible links or Sollbruchstellen) on tow ropes is mandatory in all cases, regardless of rope material or glider type. Weak links are calibrated breaking elements that protect both the glider and the tow aircraft (or winch system) from excessive loads by failing at a predetermined force. A (only two-seat gliders) is too restrictive. B (only synthetic ropes) is too restrictive. D (only natural fiber ropes) is also too restrictive. The protection they provide is essential for all launch configurations.
Correct: C)
Explanation: The yellow triangle on a glider's ASI marks the recommended approach speed for landing under normal conditions. This is the reference speed the pilot should target on final approach, typically 1.3 to 1.5 times the stall speed, providing an adequate safety margin above stall while ensuring a reasonable landing distance. A (smooth air speed limit) describes the upper end of the yellow arc (VNO). B (stall speed) is at the lower end of the green arc. D (turbulence speed limit) is also related to VNO, not the triangle marker.
Correct: A)
Explanation: The minimum equipment required for a glider is defined in its specific flight manual (AFM/POH). There is no universal one-size-fits-all list; each aircraft type has its own minimum equipment requirements specified by the manufacturer and approved by the certification authority. B, C, and D all suggest specific instrument combinations that may or may not match a particular glider's requirements. Only A correctly identifies the authoritative source for determining minimum equipment.
]
- A) Only the left one.
- B) Only the middle one.
- C) No.
- D) Yes.
Correct: D)
Explanation: The diagram shows standard Pitot-static system connections: the Pitot tube feeds total pressure to the airspeed indicator, and the static port feeds static pressure to the altimeter, variometer, and also to the static side of the airspeed indicator. When all connections follow this standard configuration, the instruments are correctly connected. A and B (only partial correctness) and C (none correct) do not match the standard wiring shown in the diagram.
Correct: D)
Explanation: The red radial mark on a glider's ASI indicates VNE (Velocity Never Exceed), the absolute maximum speed that must never be exceeded under any conditions. Exceeding VNE can lead to structural failure from flutter, control surface overload, or airframe deformation. A (stall speed) is at the lower end of the green arc. B (approach speed) is marked by the yellow triangle. C (turbulence speed limit) corresponds to VNO at the upper end of the green arc, not the red line.
Correct: C)
Explanation: The standard EASA color convention for glider cockpit handles is: red for the emergency canopy release, blue for the airbrakes (speed brakes/spoilers), and green for the trim. This consistent color coding ensures pilots can identify critical controls quickly and correctly under stress. A incorrectly assigns red to airbrakes. B incorrectly assigns red to the undercarriage. D incorrectly assigns red to airbrakes and green to undercarriage. Only C correctly maps all three colors to their respective controls.
]
Correct: B)
Explanation: Using the loading table from the flight manual (attached figure) for a glider with 275 kg empty weight: the correct combination that keeps total mass within the maximum takeoff weight and CG within approved limits is 100 kg payload with 80 liters of water ballast. A (85 kg/100 L) and D (105 kg/70 L) do not satisfy the loading table constraints. C (110 kg/65 L) exceeds the payload-ballast relationship shown in the table. Only B provides a valid combination that respects both mass and CG limits.
Correct: C)
Explanation: The correct answer is C because the parachute is carried by the pilot and is not a permanent part of the aircraft structure, so it falls under useful load (payload). A is wrong because "dry weight" is not a standard glider weight category. B is wrong because empty weight includes only the permanent airframe structure, fixed equipment, and unusable fluids — not items brought aboard by the pilot. D is wrong because "weight of lifting surfaces" refers to the wings, which are part of the airframe empty weight.
Correct: C)
Explanation: The correct answer is C because the altimeter, variometer, and airspeed indicator all rely on static pressure to function. The altimeter measures static pressure directly to determine altitude, the variometer detects changes in static pressure over time, and the airspeed indicator compares pitot (total) pressure against static pressure. A is wrong because the artificial horizon (gyroscopic) and compass (magnetic) do not use static pressure. B and D are wrong because the turn indicator is gyroscopic and does not depend on static pressure.
Correct: B)
Explanation: The correct answer is B because weak links are mandatory when natural fibre tow ropes are used (since their breaking strength is less predictable than synthetic ropes) and whenever the aircraft flight manual specifies their use. A is wrong because the requirement is not limited to two-seat gliders. C is wrong because synthetic ropes already have a more controlled and predictable breaking strength. D is wrong because the requirement depends on the rope type and flight manual provisions, not a blanket mandate for all cases.
Correct: D)
Explanation: The correct answer is D because the Tost safety hook is designed with a mechanical release mechanism that triggers automatically when the cable angle exceeds approximately 70 degrees relative to the longitudinal axis, protecting the glider from a dangerous nose-down pitch (winch launch upset). A is wrong because the hook is designed to release, not to retain slack cable. B is wrong because it is a dedicated winch launch hook, not a backup for the nose (aerotow) hook. C is wrong because hook position has no meaningful effect on yaw manoeuvrability.
Correct: B)
Explanation: The correct answer is B because a glider's accelerometer (g-meter) measures the load factor along the aircraft's vertical axis in the plane of symmetry, which is perpendicular to the roll (longitudinal) axis. This captures the combined effect of gravitational and manoeuvre-induced accelerations. A is wrong because the instrument is not limited to lateral forces. C is wrong because it measures total normal acceleration, not centrifugal force alone. D is wrong because it does not measure a component "opposing" gravity specifically, but rather the net normal acceleration.
]
- A) 90 litres.
- B) 95 litres.
- C) 85 litres.
- D) 105 litres.
Correct: B)
Explanation: The correct answer is B because the calculation is: empty weight (255 kg) + pilot (100 kg) = 355 kg. If the maximum all-up mass is 450 kg, then the remaining capacity for water ballast is 450 - 355 = 95 kg, which equals approximately 95 litres (since water density is 1 kg/L). A (90 L) and C (85 L) underestimate the available margin, while D (105 L) would exceed the maximum permitted mass.
Correct: C)
Explanation: The correct answer is C because the primary safety requirement for any oxygen system is that the pilot can operate it and read its indicators (flow rate, bottle pressure) during flight without difficulty. If the system cannot be monitored in flight, the pilot has no way to detect a malfunction or depletion. A is wrong because the required oxygen reserve depends on flight altitude and duration, not a fixed 100-litre minimum. B is wrong because while non-return valves may be beneficial, the regulatory emphasis is on operability. D is wrong because ease of removal is a convenience factor, not a safety requirement.
Correct: C)
Explanation: The correct answer is C because an on-demand regulator performs two functions: it enriches the air/oxygen mixture progressively as altitude increases (to compensate for decreasing partial pressure of oxygen), and it delivers gas only during inhalation, conserving the limited oxygen supply. A is wrong because the regulator does not control consumption — it responds to the pilot's breathing. B is wrong because pressure reduction is performed by a separate first-stage regulator. D is partially correct but incomplete — the key feature is altitude-dependent mixture adjustment combined with demand-only delivery.
Correct: C)
Explanation: The correct answer is C because both diaphragm and vane variometers work by comparing the atmospheric static pressure (which changes with altitude) against the pressure inside a sealed reference vessel connected to the atmosphere through a calibrated restriction. When the aircraft climbs or descends, a pressure differential develops across the restriction, deflecting a diaphragm or vane to indicate the rate of altitude change. A is wrong because temperature measurement is not involved. B describes the result, not the operating principle. D is wrong because accelerometers, not variometers, measure vertical accelerations.
Correct: D)
Explanation: The correct answer is D because the red radial line on a glider's airspeed indicator marks VNE (velocity never exceed), the maximum speed at which the aircraft may be operated under any conditions. Exceeding VNE risks structural failure due to aerodynamic loads or flutter. A is wrong because the stall speed is indicated at the lower end of the green arc. B is wrong because the approach speed is typically shown by a yellow triangle marker. C is wrong because the speed limit in turbulence corresponds to VNO, which is at the upper end of the green arc (boundary with the yellow arc).
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).
Correct: B)
Explanation: Maximum permissible airspeeds (VNE, VNO, etc.) are published in the Pilot's Operating Handbook (POH/AFM), displayed on the cockpit instrument panel (placard), and indicated on the airspeed indicator by the red line (VNE) and arc markings. The AIP ENR (A) does not contain aircraft-specific speed limitations. Approach charts and VSI (B) do not show speed limits. The briefing room posting (C) is informal and not authoritative.
Correct: A)
Explanation: The airspeed indicator is a required instrument for safe flight; without it a pilot cannot determine safe operating speeds, stall speed, or structural speed limits. An inoperative airspeed indicator means the aircraft must remain on the ground until the instrument is serviceable. No exception exists for local aerodrome patterns (B) or GPS substitute (D — GPS ground speed is not equivalent to IAS for aerodynamic purposes). Absence of maintenance (A) is irrelevant to the operational requirement.
Correct: A)
Explanation: During a left turn, a yaw string deflecting to the left indicates the aircraft is slipping into the turn (too much bank relative to rudder input). To centre the string in a slip, the pilot needs to increase bank to steepen the turn and reduce rudder (less rudder in the turn direction). This is opposite to correcting a skid. Options B, C, and D use incorrect combinations for correcting a slip in a left turn.
Correct: C)
Explanation: Winglets are upward (or downward) curving extensions at the wingtip that reduce induced drag by weakening the wingtip vortex — the main source of induced drag on a finite wing. They do not primarily increase aspect ratio efficiency (A — though functionally similar, they are a different mechanism), are not specifically for high-speed performance (C), and do not increase lift or turning agility (D).
Correct: C)
Explanation: Dynamic pressure (q) is defined by Bernoulli's equation as q = ½ρv², where ρ is air density and v is airflow speed. Dynamic pressure depends directly on air density and the square of velocity. Lift and drag coefficients (A) are aerodynamic effects that depend on dynamic pressure, not the other way around. Air pressure and temperature (D) influence density indirectly but are not the direct parameters in the formula.
Correct: C)
Explanation: The airspeed indicator, altimeter, and vertical speed indicator are all connected to the static pressure port. If the static pressure system is blocked (e.g., by ice, water, or a cover left on), all three instruments will give erroneous readings simultaneously. A blocked pitot tube (C) would affect only the airspeed indicator. A leaking compensating vessel (B) affects only the VSI. An electrical failure (D) does not affect these purely pneumatic instruments.
Correct: B)
Explanation: The altimeter's reference pressure (subscale) must be set before every flight to the correct local QNH/QFE so that the altimeter reads the correct altitude or height. During cross-country flights, QNH changes as the pilot moves between pressure regions, so updates are required when crossing into new altimeter setting regions. Monthly (C) or only after maintenance (A) settings would result in significant altitude errors.
Correct: D)
Explanation: Magnetic inclination (dip) is the angle between the Earth's magnetic field vector and the horizontal plane at any given location. It is 0° at the magnetic equator and 90° at the magnetic poles. Deviation (A) is the error caused by magnetic fields within the aircraft. Magnetic variation/declination (B) is the angle between magnetic and true north. Option D describes aircraft heading, which is unrelated.
Correct: D)
Explanation: The airspeed indicator measures IAS (Indicated Airspeed), which is derived from dynamic pressure. At lower air density (hot day, high altitude), TAS is higher than IAS for the same dynamic pressure. The aerodynamic behaviour of the wing (lift, stall) depends on dynamic pressure (and thus IAS), not on TAS. Therefore stall occurs at the same IAS regardless of density. The approach should be flown at the same IAS as always (B). Adding speed (D) or reducing IAS (C) based on temperature alone is not correct for stall margin management with IAS.
Correct: D)
Explanation: The load factor (n) is the ratio of the aerodynamic lift acting on the aircraft to the aircraft's weight: n = L/W. In level unaccelerated flight, n = 1. In turns or pull-ups, n increases. It does not describe weight/thrust (A), drag/lift (B), or thrust/drag (D) relationships.
Correct: D)
Explanation: Static pressure is the pressure of the undisturbed ambient airmass — the atmospheric pressure acting equally in all directions at a given altitude. It is sensed through flush static ports on the fuselage skin. It is not the cabin pressure (A), not related to orderly flow direction (C — that is dynamic pressure), and is not sensed by the pitot tube alone (D — the pitot senses total pressure).
Correct: C)
Explanation: Magnetic inclination (dip) is the angle between the Earth's total magnetic field vector and the local horizontal plane. At the magnetic equator, field lines are horizontal (0° dip); at the poles, they are vertical (90° dip). Deviation (A) is caused by onboard magnetic interference. Variation/declination (B) is the angle between magnetic and geographic north. Option D describes aircraft heading relative to true north.
