I85PREP
⌘ K
NCAA CPL Flight Performance & Planning study materials
NCAA CPL Flight Performance & Planning study resources

NCAA CPL Flight Performance & Planning practice questions

One question at a time. Build your NCAA CPL Flight Performance & Planning understanding.

First 50 of 200 questions. Each one lists the choices, the correct answer, and an explanation. The checker at the top of this page saves progress in this browser when it is available.

Continue in the practice tool above to load more questions, 50 at a time.

Question 1Mass and Balance

In mass and balance terminology, what does the abbreviation MTOM represent?

  1. Maximum Take-Off Mass Correct answer.
  2. Mean Take-Off Mass
  3. Minimum Take-Off Moment
  4. Maximum Taxi Operating Mass

Explanation

MTOM is Maximum Take-Off Mass, the highest mass at which the aircraft is permitted to begin the take-off run. It is a structural and certification limit stated in the aircraft flight manual and is independent of the actual load carried on a given flight.

Question 2Mass and Balance

Which mass is defined as the mass of the aircraft with structure, powerplant, systems and equipment, including unusable fuel and undrainable oil, but excluding usable fuel and payload?

  1. Landing Mass
  2. Zero Fuel Mass
  3. Dry Operating Mass
  4. Basic Empty Mass Correct answer.

Explanation

Basic Empty Mass includes the airframe, powerplant, systems, fixed equipment, unusable fuel and undrainable oil. Usable fuel, crew, passengers and cargo are excluded and are added later to build up the operating and take-off masses.

Question 3Mass and Balance

An aircraft has a Dry Operating Mass of 3,200 kg, a traffic load of 800 kg and a fuel load of 400 kg. What is the take-off mass?

  1. 3,600 kg
  2. 4,000 kg
  3. 4,800 kg
  4. 4,400 kg Correct answer.

Explanation

Take-off mass is the sum of Dry Operating Mass, traffic load and take-off fuel: 3,200 + 800 + 400 = 4,400 kg. Each component must be included once, and the total is then checked against MTOM and the performance-limited mass.

Question 4Mass and Balance

What is the definition of the centre of gravity of an aircraft?

  1. The geometric midpoint of the fuselage between nose and tail
  2. The point through which the total weight of the aircraft is considered to act Correct answer.
  3. The point where the wing spar passes through the fuselage
  4. The point on the fuselage at which the main wheels are attached

Explanation

The centre of gravity is the point at which the resultant of all mass forces is considered to act, and it is the reference for the balance calculation. Its position is expressed as a distance from a defined datum and must remain within the certified CG limits.

Question 5Mass and Balance

What is the datum in a mass and balance calculation?

  1. The forwardmost point of the aircraft structure
  2. The point at which the aircraft mass is assumed to be concentrated
  3. An arbitrary fixed reference point from which all longitudinal arms are measured Correct answer.
  4. The aft limit of the permitted centre of gravity range

Explanation

The datum is an arbitrary but fixed reference plane or point chosen by the manufacturer, from which all longitudinal arms are measured. Because it is fixed, arms of items ahead of the datum are negative and those behind it are positive, and the sign convention must be applied consistently.

Question 6Mass and Balance

In the standard mass and balance convention, what is a moment?

  1. The ratio of mass to arm
  2. The sum of all arms on the aircraft
  3. The difference between MTOM and the actual mass
  4. The product of a mass and its arm from the datum Correct answer.

Explanation

A moment is the product of an item's mass and its arm measured from the datum, expressed in mass-length units such as kg·m. Moments are summed and divided by the total mass to find the CG arm.

Question 7Mass and Balance

Which condition must be satisfied for an aircraft to be legally dispatched in terms of balance?

  1. The centre of gravity must be behind the aft limit to reduce trim drag
  2. The centre of gravity must be exactly at the midpoint of the permitted range
  3. The centre of gravity must lie within the certified forward and aft limits for take-off and throughout the flight Correct answer.
  4. The centre of gravity must be forward of the forward limit to ensure nose-down authority

Explanation

The CG must remain within the certified forward and aft limits at take-off and for the whole flight, including fuel burn and any in-flight movement of load. Being inside the range ensures both adequate control authority and acceptable stability.

Question 8Mass and Balance

What is the principal effect of loading an aircraft so that its centre of gravity moves toward the forward limit?

  1. The stick force and rotation effort increase and take-off performance may be reduced Correct answer.
  2. Take-off distance decreases because the tailplane load is reduced
  3. The stall speed decreases because the wing loading is lower
  4. The aircraft becomes less stable in pitch and easier to rotate

Explanation

A forward CG increases the nose-down moment, so more tail-down force and elevator deflection are needed to rotate and trim. This raises the required stick force and can increase take-off distance and reduce climb performance.

Question 9Mass and Balance

An aircraft has a total mass of 4,000 kg and a total moment of 20,000 kg·m about the datum. What is the CG arm?

  1. 5.0 m Correct answer.
  2. 4.0 m
  3. 80,000 m
  4. 0.2 m

Explanation

The CG arm is total moment divided by total mass: 20,000 ÷ 4,000 = 5.0 m. Dividing rather than multiplying is essential because the moment already contains the mass factor.

Question 10Mass and Balance

An item of 150 kg is loaded at an arm of −2.0 m relative to the datum. What moment does it contribute?

  1. −300 kg·m Correct answer.
  2. +75 kg·m
  3. +300 kg·m
  4. −75 kg·m

Explanation

Moment equals mass times arm, so 150 kg × (−2.0 m) = −300 kg·m. A negative sign indicates the item lies ahead of the datum, and this negative moment correctly reduces the total moment.

Question 11Mass and Balance

During a flight, fuel is burned from tanks located ahead of the centre of gravity. What is the effect on the CG position?

  1. The CG moves aft Correct answer.
  2. The CG moves forward only if the tanks are in the wings
  3. The CG remains unchanged because mass is lost symmetrically
  4. The CG moves forward

Explanation

Burning fuel removes mass from a point ahead of the CG, which removes a nose-down moment. The remaining mass therefore has a relatively larger aft contribution, so the CG moves aft, and this must be checked against the aft limit at landing.

Question 12Mass and Balance

What is the significance of the maximum zero fuel mass (MZFM)?

  1. It limits the total mass at the moment of touchdown
  2. It limits the combined mass of the aircraft and traffic load before usable fuel is added Correct answer.
  3. It is the mass of the aircraft with unusable fuel only
  4. It defines the maximum fuel that may be carried in the tanks

Explanation

MZFM is the maximum permissible mass of the aircraft with payload but without usable fuel. It protects the wing bending and structural limits, and it can be more restrictive than MTOM on short sectors where a large payload is carried with little fuel.

Question 13Mass and Balance

An aircraft has a maximum landing mass of 5,000 kg and will land with 600 kg of fuel. What is the maximum traffic load permitted at landing if the Dry Operating Mass is 3,500 kg?

  1. 2,100 kg
  2. 1,500 kg
  3. 900 kg Correct answer.
  4. 300 kg

Explanation

Landing mass equals DOM plus traffic load plus fuel remaining, so traffic load = 5,000 − 3,500 − 600 = 900 kg. The result must then be compared with the take-off and zero fuel mass limits, and the lowest governs.

Question 14Mass and Balance

Why does an operator often compute a load sheet using index units instead of raw moments?

  1. Indices are required by ICAO for all aircraft above 5,700 kg
  2. Indices are scaled moments that keep numbers small and allow simple addition with tabulated values Correct answer.
  3. Indices eliminate the need to check the CG against the envelope
  4. Indices convert mass into volume for cargo loading

Explanation

An index is a moment divided by a constant and shifted by a reference value, producing small convenient numbers. Loading tables then give the index change for each item so the total can be found by simple addition, and the result is converted back to a CG arm or read directly against the envelope.

Question 15Mass and Balance

A load is moved aft by 1.5 m on an aircraft of total mass 6,000 kg. The item moved has a mass of 200 kg. By how much does the CG shift?

  1. 0.30 m aft
  2. 0.50 m aft
  3. 0.05 m aft Correct answer.
  4. 0.75 m aft

Explanation

The CG shift equals the mass moved times the distance moved, divided by the total mass: (200 × 1.5) ÷ 6,000 = 0.05 m aft. The shift is in the same direction as the movement but much smaller because the item is a small fraction of total mass.

Question 16Mass and Balance

Which loading practice would most effectively correct a CG that is slightly aft of the aft limit?

  1. Adding ballast at the tail cone
  2. Moving load from a forward compartment to a rear compartment
  3. Moving load from a rear compartment to a forward compartment Correct answer.
  4. Reducing fuel in tanks located behind the CG

Explanation

Moving mass forward shifts the total CG forward because the moment about the datum is reduced by the item's mass times the distance moved. This is the standard correction when the CG is aft of the limit and the mass limits still allow the load to be carried.

Question 17Mass and Balance

What does the floor loading limit of a cargo compartment protect against?

  1. Excessive fuel pressure in the wing tanks
  2. Excessive local load per unit area that could damage the structure Correct answer.
  3. Excessive total mass of the aircraft at take-off
  4. Excessive cumulative moment about the datum

Explanation

The floor loading limit is a local structural limit expressed as mass per unit area, such as kg/m². It prevents concentrated loads from overstressing floor panels and frames even when the total mass and the CG are within limits.

Question 18Mass and Balance

An aircraft is loaded with a take-off mass of 4,900 kg against an MTOM of 5,000 kg, but its CG is 0.1 m ahead of the forward limit. What is the correct operational conclusion?

  1. The aircraft may depart if the fuel load is reduced by 100 kg
  2. The aircraft may depart because the mass is below MTOM
  3. The aircraft may not depart until the CG is brought within the forward limit Correct answer.
  4. The aircraft may depart provided the aft limit is respected

Explanation

Both mass and balance limits must be satisfied; being under MTOM does not excuse a CG outside the envelope. The load must be redistributed, for example by moving items aft, until the CG is inside the forward limit before departure.

Question 19Mass and Balance

Which statement correctly describes the relationship between the centre of gravity and the centre of pressure in steady level flight?

  1. The centre of pressure is a fixed structural point independent of angle of attack
  2. The tailplane provides a balancing force so that the resultant lift acts through the CG Correct answer.
  3. The CG moves aft as the centre of pressure moves forward
  4. The centre of pressure always coincides with the CG at all angles of attack

Explanation

In steady flight the moments about the CG must sum to zero, so the wing and tail lift resultants together pass through the CG. Because the wing centre of pressure moves with angle of attack, the tailplane load changes to maintain trim.

Question 20Mass and Balance

An aircraft of total mass 5,000 kg has its CG at 4.0 m from the datum. A 250 kg item at 10.0 m from the datum is offloaded. What is the new CG arm?

  1. 4.32 m
  2. 3.50 m
  3. 3.90 m
  4. 3.68 m Correct answer.

Explanation

Original moment is 5,000 × 4.0 = 20,000 kg·m; the removed item contributes 250 × 10.0 = 2,500 kg·m. New moment is 17,500 kg·m over 4,750 kg, giving 3.684 m, which rounds to 3.68 m. Removing mass behind the CG moves the CG forward.

Question 21Mass and Balance

Why can a forward CG limit be more restrictive than the aft limit on some aircraft during take-off?

  1. The elevator may reach its deflection limit before generating enough tail-down force to rotate at the required speed Correct answer.
  2. The nosewheel steering becomes ineffective with a forward CG
  3. The wing lift is reduced when the CG is forward, lowering the stall margin
  4. The aft limit is set only by the landing gear strength

Explanation

With a very forward CG, the tailplane must produce a large download to rotate the aircraft. If the elevator reaches full deflection before that download is achieved, rotation cannot occur at the scheduled speed, so a forward limit is imposed to preserve rotation capability.

Question 22Mass and Balance

An operator uses an index formula where index = (moment ÷ 1,000) + 50. A load sheet shows a total index of 62 with a total mass of 4,200 kg. What is the CG arm?

  1. 2.38 m
  2. 2.86 m Correct answer.
  3. 12.00 m
  4. 3.40 m

Explanation

Rearranging gives moment ÷ 1,000 = 62 − 50 = 12, so moment = 12,000 kg·m. Dividing by the total mass gives 12,000 ÷ 4,200 = 2.857 m, which rounds to 2.86 m.

Question 23Mass and Balance

An aircraft with MTOM 5,700 kg, MZFM 5,000 kg and MLM 5,400 kg has DOM 3,600 kg and a take-off fuel load of 1,000 kg. What is the limiting traffic load?

  1. 1,100 kg Correct answer.
  2. 800 kg
  3. 1,800 kg
  4. 1,400 kg

Explanation

MTOM limits traffic load to 5,700 − 3,600 − 1,000 = 1,100 kg; MZFM limits it to 5,000 − 3,600 = 1,400 kg; MLM with, say, 200 kg fuel remaining limits it to 5,400 − 3,600 − 200 = 1,600 kg. The lowest value, 1,100 kg, governs.

Question 24Mass and Balance

What is the purpose of a longitudinal CG envelope diagram in the aircraft flight manual?

  1. To show the permitted combinations of mass and CG arm for each phase such as take-off and landing Correct answer.
  2. To give the take-off distance for each flap setting
  3. To list the structural repair limits for the fuselage
  4. To show the fuel consumption rate against altitude

Explanation

The CG envelope plots mass against CG arm and encloses the combinations permitted for a given configuration and phase. Take-off and landing envelopes may differ, and the loaded aircraft must be checked against the relevant one.

Question 25Mass and Balance

A pilot adds 300 kg of baggage at an arm of 6.0 m to an aircraft whose current mass is 3,700 kg with a CG at 4.5 m. Which statement is correct?

  1. The new CG is about 4.50 m because baggage has little effect
  2. The new CG is about 4.61 m and the mass is 4,000 kg, so both must be checked against the limits Correct answer.
  3. The new CG is about 4.39 m because the baggage is forward of the datum
  4. The new CG is about 5.25 m because arms are averaged directly

Explanation

New moment = 3,700 × 4.5 + 300 × 6.0 = 16,650 + 1,800 = 18,450 kg·m over 4,000 kg, giving 4.6125 m. The CG moves aft because the baggage arm is behind the existing CG, and the new mass must also be checked against MTOM.

Question 26Mass and Balance

In mass and balance calculations, what does the term 'datum' refer to?

  1. The maximum allowable aft position of the centre of gravity
  2. The point at which the centre of gravity must always be located
  3. An arbitrary reference point from which all arms are measured Correct answer.
  4. The point about which the aircraft would balance if suspended

Explanation

The datum is an arbitrarily chosen reference point, often at or near the nose, from which all longitudinal arms are measured. It is not necessarily the CG or a balance point; it simply provides a consistent origin for moment calculations. The CG is then found by dividing total moment by total mass.

Question 27Mass and Balance

An aircraft has a basic empty mass of 3,200 kg with a CG arm of 4.0 m. What is the basic empty moment about the datum?

  1. 800 kg·m
  2. 12,800 kg·m Correct answer.
  3. 12,800 kg/m
  4. 3,204 kg·m

Explanation

Moment is mass multiplied by arm: 3,200 kg × 4.0 m = 12,800 kg·m. The moment is expressed in kilogram-metres, not kilograms per metre. This basic empty moment is the starting value to which all subsequent load moments are added.

Question 28Mass and Balance

Which statement best describes the operational significance of the maximum take-off mass (MTOM)?

  1. It is the maximum mass of traffic load that may be carried in the cabin
  2. It is the maximum mass at which the aircraft may land, regardless of take-off mass
  3. It is the maximum mass at which the aircraft may be dispatched, limited by structural and performance considerations Correct answer.
  4. It is the maximum mass of fuel that may be carried in the tanks

Explanation

MTOM is the maximum certificated mass for the start of the take-off run, and it accounts for structural strength, climb performance, and brake energy. It is not the landing limit or a fuel or payload limit in isolation. Exceeding MTOM invalidates the assumed performance and structural margins.

Question 29Mass and Balance

Which of the following is the standard unit for expressing the arm of an item in mass and balance calculations?

  1. Kilograms
  2. Kilogram-metres
  3. Metres Correct answer.
  4. Newton-metres

Explanation

Arm is a distance from the datum, so it is expressed in metres (or sometimes inches). Kilograms measure mass, and kilogram-metres measure moment. Newton-metres would be a moment in SI force units, not an arm.

Question 30Mass and Balance

An aircraft has a total mass of 4,200 kg and a total moment of 16,800 kg·m about the datum. What is the CG arm?

  1. 8.0 m
  2. 4.0 m Correct answer.
  3. 16,800 m
  4. 0.25 m

Explanation

The CG arm is total moment divided by total mass: 16,800 kg·m ÷ 4,200 kg = 4.0 m. This is the standard method for locating the CG after summing all mass and moment contributions. The result must then be checked against the CG envelope.

Question 31Mass and Balance

An aircraft is loaded such that its CG is at the forward limit. What is a likely consequence for take-off performance?

  1. Shorter take-off distance and improved climb gradient
  2. Reduced structural loading on the nose gear only
  3. No change in take-off distance but higher fuel consumption
  4. Longer take-off distance and reduced climb gradient Correct answer.

Explanation

A forward CG increases the load on the tailplane, requiring more elevator deflection and increasing trim drag and rotation effort. This typically lengthens the take-off distance and reduces the climb gradient. Performance charts often include a forward CG correction.

Question 32Mass and Balance

What is the effect on the CG of burning fuel from a tank located aft of the CG?

  1. The CG moves forward Correct answer.
  2. The CG moves to the datum
  3. The CG moves aft
  4. The CG remains unchanged

Explanation

Burning fuel removes mass from an aft location, which reduces the total moment and shifts the CG forward. The opposite occurs when fuel from a forward tank is burned. This shift must be considered for both take-off and landing CG checks.

Question 33Mass and Balance

An aircraft has a maximum zero fuel mass (MZFM) of 4,800 kg and a dry operating mass (DOM) of 3,500 kg. What is the maximum traffic load that can be carried?

  1. 8,300 kg
  2. 1,300 kg Correct answer.
  3. 3,500 kg
  4. 4,800 kg

Explanation

Traffic load = MZFM − DOM = 4,800 kg − 3,500 kg = 1,300 kg. MZFM limits the mass of aircraft, crew, payload, and unusable fuel, but excludes usable fuel. The result must also be checked against volume and floor loading limits.

Question 34Mass and Balance

Why is the CG envelope often narrower for take-off than for landing on some aircraft?

  1. Because take-off requires a specific CG range for rotation and climb performance Correct answer.
  2. Because landing is always conducted with a forward CG
  3. Because the landing gear configuration changes the datum
  4. Because fuel burn always moves the CG forward

Explanation

Take-off performance, particularly rotation and climb gradient, can be sensitive to CG position, so the AFM may impose a more restrictive take-off CG range. The landing CG range may be wider because landing performance is less sensitive. Pilots must check the CG against the appropriate envelope for each phase.

Question 35Mass and Balance

An operator uses an index formula where index = (moment ÷ 1,000) + 50. A load sheet shows a total index of 64 with a total mass of 5,000 kg. What is the CG arm?

  1. 3.2 m
  2. 2.8 m Correct answer.
  3. 5.0 m
  4. 6.4 m

Explanation

First find the moment: index 64 = (moment ÷ 1,000) + 50, so moment ÷ 1,000 = 14, and moment = 14,000 kg·m. Then CG arm = moment ÷ mass = 14,000 ÷ 5,000 = 2.8 m. This shows how index values must be converted back to moments before finding the CG.

Question 36Mass and Balance

A 200 kg item is moved from an arm of 3.0 m to an arm of 7.0 m. What is the change in total moment?

  1. 800 kg·m aft Correct answer.
  2. 800 kg·m forward
  3. 400 kg·m aft
  4. 200 kg·m aft

Explanation

The change in moment is mass × change in arm = 200 kg × (7.0 − 3.0) m = 200 × 4.0 = 800 kg·m. Because the item moves aft, the moment increases in the aft direction. This moment change will shift the CG aft by 800 kg·m divided by the total mass.

Question 37Mass and Balance

Which of the following best explains why the CG must be checked at both take-off and landing?

  1. Because fuel burn and configuration changes can move the CG outside the limits during flight Correct answer.
  2. Because the datum changes when the aircraft is in flight
  3. Because the maximum landing mass is always lower than the maximum take-off mass
  4. Because the CG envelope is identical for all phases of flight

Explanation

Fuel burn, gear and flap retraction, and payload movement can shift the CG during flight. Therefore, the CG must be within the appropriate envelope at take-off and again at landing. Checking only one phase could allow an in-flight CG excursion beyond limits.

Question 38Mass and Balance

An aircraft has a maximum landing mass of 5,400 kg and will land with 500 kg of fuel. What is the maximum traffic load at landing if the dry operating mass is 3,600 kg?

  1. 1,800 kg
  2. 2,300 kg
  3. 5,400 kg
  4. 1,300 kg Correct answer.

Explanation

Landing mass = DOM + traffic load + landing fuel. Rearranging: traffic load = MLM − DOM − landing fuel = 5,400 − 3,600 − 500 = 1,300 kg. This must also be checked against MZFM and MTOM limits.

Question 39Mass and Balance

An aircraft has a total mass of 5,000 kg and a CG at 4.0 m. A 500 kg item is loaded at an arm of 10.0 m. What is the new CG arm?

  1. 6.0 m
  2. 5.5 m
  3. 4.5 m Correct answer.
  4. 5.0 m

Explanation

Original moment = 5,000 × 4.0 = 20,000 kg·m. Added moment = 500 × 10.0 = 5,000 kg·m. New total moment = 25,000 kg·m; new total mass = 5,500 kg. New CG = 25,000 ÷ 5,500 ≈ 4.545 m, which rounds to 4.5 m.

Question 40Mass and Balance

An aircraft has MTOM 5,700 kg, MZFM 5,000 kg, MLM 5,400 kg, DOM 3,600 kg, and take-off fuel 1,000 kg. What is the maximum traffic load?

  1. 1,100 kg Correct answer.
  2. 1,800 kg
  3. 1,400 kg
  4. 2,100 kg

Explanation

Check all limits: MTOM limit gives traffic load = 5,700 − 3,600 − 1,000 = 1,100 kg. MZFM limit gives 5,000 − 3,600 = 1,400 kg. MLM limit depends on landing fuel, but with 1,000 kg take-off fuel, landing fuel is less, so MLM is not limiting here. The lowest value, 1,100 kg, governs.

Question 41Performance - Aeroplanes

In aeroplane performance planning, which speed is defined as the speed at which the critical engine is assumed to fail during take-off, so that the remaining engine or engines allow the take-off to be continued or rejected within the available runway?

  1. V1 (decision speed) Correct answer.
  2. VMC (minimum control speed)
  3. V2 (take-off safety speed)
  4. VR (rotation speed)

Explanation

V1 is the take-off decision speed: at or above it the take-off must be continued after an engine failure, below it the take-off must be rejected. It is derived from the accelerate-stop and accelerate-go distances and is central to balanced field length planning.

Question 42Performance - Aeroplanes

The take-off distance available (TODA) differs from the take-off run available (TORA) because TODA includes which additional element?

  1. The stopway usable for an aborted take-off
  2. The clearway beyond the end of the runway Correct answer.
  3. The runway strip graded for emergency landing
  4. The displaced threshold at the far end

Explanation

TODA is TORA plus any clearway, because the aeroplane may be allowed to climb over the clearway before reaching 35 ft. The stopway is added to TORA to give ASDA, not TODA.

Question 43Performance - Aeroplanes

The accelerate-stop distance available (ASDA) is defined as the take-off run available plus which element?

  1. The length of any stopway Correct answer.
  2. The runway end safety area
  3. The length of any clearway
  4. The landing distance available

Explanation

ASDA is TORA plus stopway, since the stopway is a prepared area able to support the aeroplane during a rejected take-off. Clearway is an obstacle-free air area and cannot be used for stopping.

Question 44Performance - Aeroplanes

For a given pressure altitude, what is the general effect of increasing outside air temperature on the take-off ground roll?

  1. The ground roll is unchanged because thrust is constant
  2. The ground roll decreases because the air is thinner
  3. The ground roll increases because density altitude increases Correct answer.
  4. The ground roll decreases because lift increases

Explanation

Higher temperature at constant pressure altitude reduces air density, which raises density altitude. Thrust and lift both fall, so more runway is needed for the same take-off. This is why hot-and-high operations demand longer distances.

Question 45Performance - Aeroplanes

What does the term 'density altitude' represent in aeroplane performance planning?

  1. The pressure altitude corrected for non-standard temperature Correct answer.
  2. The true altitude above the surface
  3. The altitude at which the standard lapse rate stops
  4. The altitude indicated with the altimeter set to 1013 hPa

Explanation

Density altitude is the altitude in the standard atmosphere at which the observed air density would occur. It equals pressure altitude adjusted for temperature deviation and is the value used in performance charts.

Question 46Performance - Aeroplanes

Which of the following is a correct statement of the effect of wind on take-off performance?

  1. A tailwind shortens the ground roll because of reduced drag
  2. A tailwind has no effect on the take-off distance
  3. A headwind lengthens the ground roll because of increased lift
  4. A headwind shortens the ground roll and improves the climb gradient Correct answer.

Explanation

A headwind reduces the ground speed needed to reach the same airspeed, shortening the ground roll, and it improves the climb gradient over the ground. The benefit is normally assumed to disappear at the critical engine failure point in net take-off planning.

Question 47Performance - Aeroplanes

In landing performance planning, the landing distance required (LDR) is normally compared against which declared distance?

  1. The accelerate-stop distance available (ASDA)
  2. The take-off run available (TORA)
  3. The landing distance available (LDA) Correct answer.
  4. The take-off distance available (TODA)

Explanation

The LDR must not exceed the LDA, which is the runway length available for a landing from the threshold to the runway end. The take-off declared distances are not used to certify a landing.

Question 48Performance - Aeroplanes

Which of the following best describes the net take-off flight path used in obstacle clearance planning?

  1. The flight path at V2 with maximum continuous thrust
  2. The flight path after landing gear retraction at VREF
  3. The gross flight path reduced by a specified gradient margin Correct answer.
  4. The flight path flown with all engines operating

Explanation

The net take-off flight path is the gross climb path reduced by a defined gradient decrement to account for pilot technique and turbulence. Obstacles must be cleared by the net path, not by the gross path.

Question 49Performance - Aeroplanes

An aeroplane is planned to take off from a runway at a pressure altitude of 4 000 ft with an outside air temperature of ISA+15 °C. Compared with ISA conditions at the same pressure altitude, the take-off distance required will be:

  1. Shorter, because the air is more dense
  2. Shorter, because engine power increases
  3. The same, because pressure altitude is unchanged
  4. Longer, because the density altitude is higher Correct answer.

Explanation

At ISA+15 °C the air is warmer than standard, so density is lower than standard at that pressure altitude. The higher density altitude reduces thrust and lift, so the take-off distance required increases.

Question 50Performance - Aeroplanes

An aeroplane has a TORA of 1 800 m, a clearway of 150 m and a stopway of 60 m. What are TODA and ASDA respectively?

  1. 1 950 m and 1 950 m
  2. 1 800 m and 1 800 m
  3. 1 860 m and 1 950 m
  4. 1 950 m and 1 860 m Correct answer.

Explanation

TODA = TORA + clearway = 1 800 + 150 = 1 950 m. ASDA = TORA + stopway = 1 800 + 60 = 1 860 m. Clearway and stopway are separate elements and are not interchangeable.