Results
Q1. *If the CG is aft of the neutral point, it results in:
Correct answer is – Longitudinal instability
Q2. *An aeroplane is loaded with its centre of gravity towards the rear limit. This will result in:
Correct answer is – an increased risk of stalling due to a decrease in tailplane moment
Q3. * The stalling speed of an aeroplane will be highest when it is loaded with a:
Correct answer is – high gross mass and forward centre of gravity
Q4. *Which of the following statements is correct?
Correct answer is – A tail-heavy aeroplane is less stable and stalls at a lower speed than a nose heavy aeroplane.
Q5. *In cruise flight, an aft centre of gravity location will:
Correct answer is – decrease longitudinal static stability.
Q6. *Which of the following would not affect the CG?
Correct answer is – Stabiliser trim setting.
Q7. *If the maximum structural landing mass is exceeded:
Correct answer is – the undercarriage could collapse on landing.
Q8. * The handling and performance problems encountered with a CG too far aft include:
Correct answer is – Difficulty or inability in recovering from a spin.
Q9. *An aeroplane is said to be ‘neutrally stable’. This is likely to:
Correct answer is – be caused by a centre of gravity which is towards the rearward limit.
Q10. *Loads must be adequately secured in order to:
Correct answer is – avoid unplanned centre of gravity (cg) movement and aircraft damage.
Q11. *The effect of operating an aeroplane with a CG too far forward is to experience:
Correct answer is – Inability or difficulty in flaring on touchdown, resulting in nosewheel landing first.
Q12. * If the centre of gravity is near the forward limit the aeroplane will:
Correct answer is – require elevator trim which will result in an increase in fuel consumption.
Q13. *With the centre of gravity on the forward limit which of the following is to be expected?
Correct answer is – A decrease in range
Q14. *The mass displacement caused by landing gear extension:
Correct answer is – creates a longitudinal moment in the direction (pitch-up or pitch-down) determined by the type of landing gear.
Q15. *The handling and performance problems encountered with a CG too far aft include:
Correct answer is – Degrade or loss of nose wheel steering.
Q16. *If an aeroplane is at a higher mass than anticipated, for a given airspeed the angle of attack will:
Correct answer is – be greater, drag will increase and endurance will decrease.
Q17. *Fuel loaded onto an aeroplane is 15400 kg but is erroneously entered into the load and trim sheet as 14500 kg. This error is not detected by the flight crew, but they will notice that:
Correct answer is – speed at un-stick will be higher than expected.
Q18. *Due to a mistake in the load sheet the aeroplane is 100 kg heavier than you believe it to be. As a consequence:
Correct answer is – VMU will be higher.
Q19. *During take-off you notice that, for a given elevator input, the aeroplane rotates much more rapidly than expected. This is an indication that:
Correct answer is – the centre of gravity may be towards the aft limit.
Q20. *Which of the following statements is correct?
Correct answer is – A tail-heavy aeroplane is less stable and stalls at a lower speed than a nose heavy aeroplane
Q21. *An additional baggage container is loaded into the aft cargo compartment but is not entered into the load and trim sheet. The aeroplane will be heavier than expected and calculated take-off safety speeds:
Correct answer is – will give reduced safety margins.
Q22. *For a large aircraft where the main and nose landing gears retract forward, the effect on the CG on lowering the gear is:
Correct answer is – to move aft
Q23. *If nose wheel moves aft during gear retraction, how will this movement affect the location of the centre of gravity (cg) on the aeroplane?
Correct answer is – It will cause the cg to move aft.
Q24. A large passenger aircraft takes off but has to make an immediate landing following an engine failure. This may cause:
Correct answer is – Higher than normal threshold speed and risk of undercarriage damage. – Threshold speed increases due higher landing mass increasing stall speed and approach speed, increasing landing impact energy
Q25. Which of the following would occur if an aircraft were flown with its C of G aft of the neutral point?
Correct answer is – It would be statically unstable. – Aft of neutral point results in loss of static stability
Q26. On an aircraft in which the main gear retracts inwards and the nose gear retracts rearwards?
Correct answer is – Gear extension will move the C of G forward. – Nose gear extension forward shifts C of G forward while main gear effects cancel
Q27. Which of the following factors is the most important is determining the allowable limits of forward movement of the C of G of an aeroplane?
Correct answer is – Available elevator and horizontal stabilizer range of movement. – Forward CG limit governed by control authority and stability requirements
Q28. Which of the following are true of an overloaded aircraft? (i) Take-off safety speeds VR VMU and VLOF are increased. (ii) Climb gradient is increased because TAS is slower. (iii) Engine-out performance is decreased. (iv) TODR is increased. (v) Rate of climb is decreased because more power is required. (vi) Range is increased because power required is reduced. (vii) Endurance is decreased because drag is increased. (viii) VMCA is increased. (ix) LDR is decreased.
Correct answer is – (i) (iii) (iv) (v) (vii). – Increased mass increases speeds, drag, TODR, reduces climb and endurance while VMCA unaffected
Q29. What would be the effect of flying with the C of G close to the forward limit?
Correct answer is – Degraded climb performance. – Forward C of G increases tail downforce, increases lift and drag, reducing climb performance, range and endurance
Q30. Which of the following factors is the most important is determining the allowable limits of rearward movement of the C of G of an aeroplane?
Correct answer is – Stability requirements. – Rear C of G limit is governed by maintaining adequate stability
Q31. Which of the following statements are true of an loaded such that its C of G lies close to its rear limit, compared to one with its C of G close to its forward limit? (i) Reduced range. (ii) Increased range. (iii) Reduced stalling speed. (iv) Increased stalling speed. (v) Reduced stick forces at rotation. (vi) Increased induced drag. (vii) Reduced induced drag.
Correct answer is – (ii) (iii) (v) (vii). – Rearward C of G reduces tail load, reducing drag and stall speed, increasing range and reducing stick force
Q32. If an aircraft were flown with its C of G on the neutral point?
Correct answer is – It would be neutrally statically stable. – At neutral point aircraft has zero static stability
Q33. How will landing gear retraction affect the C of G position of a large aircraft?
Correct answer is – There will be no significant change in C of G position. – Gear movement produces negligible CG shift in large aircraft
Q34. What would be the effect of flying with the C of G close to the forward limit?
Correct answer is – Increased induced drag. – Forward C of G increases tail load requiring more lift, increasing induced drag and reducing performance
Q35. If fuel consumption moves the C of G forwards in flight, the effects will include?
Correct answer is – Increased stability and more trim drag. – Forward shift increases stability but requires more tail force increasing trim drag
Q36. If the design of the landing gear is such that main gear retracts outwards and the nose gear retracts rearwards?
Correct answer is – Gear extension will move the C of G forward. – Nose gear extends forward shifting C of G forward while main gear effects cancel
Q37. If a large passenger aircraft is required to make an emergency landing immediately after take-off this will cause?
Correct answer is – Increased threshold speed and risk of undercarriage damage. – High landing mass increases approach speed and landing loads
Q38. If an aircraft is overloaded? (i) TODR is increased. (ii) Rate of climb is decreased because more power is required. (iii) Climb gradient is increased because TAS is slower. (iv) Endurance is decreased because drag is increased. (v) Take-off safety speeds VR VMU and VLOF are increased. (vi) Engine-out performance is decreased. (vii) VMCA is increased. (viii) LDR is decreased. (ix) Range is increased because power required is reduced.
Correct answer is – (i) (ii) (iv) (v) (vi). – Increased mass increases TODR, speeds and drag, reduces climb and endurance; VMCA unaffected and LDR increases
Q39. What would be the effect of flying with the C of G close to the forward limit?
Correct answer is – Reduced rate of climb. – Forward C of G increases drag and power required reducing climb performance
