Question Bank

1. Max structural T/O mass 55000 Kg, Max structural landing mass 52000 Kg, Max zero fuel mass 38000 Kg, DOM 29000 Kg, Fuel cons 1600 Kg/hr, Distance 1500nm, Reserve fuel 2750 Kg, TAS 260 Kts. Winds - headwind, 20K till halfway, thereafter changes to 60K tail wing. (i) Find Max traffic load in still air. (ii) Find Max traffic load with winds.

2. The stalling speed of an aero plane will be highest when it is loaded with a

3. When considering the effects of increased mass on an aero plane, which of the following is true?

4. With the center of gravity on the forward limit which of the following is to be expected?

5. From P to Q (where fuel is not available )& return to P. Maximum traffic load is to be off loaded at Q & maximum traffic load is to be uplifted from Q. the data given is: Distance P to Q 610 nm, Mass no fuel & no traffic load 36500 kg, Max landing mass 52400 kg. Max take off mass 63000 kg, Reserve fuel unused 400 kg. Additional fuel for each flight (T/O circuit landing etc.) 500 kg. Mean fuel consumption 1350 kg. /hr. Mean ground speed P to Q 240 K, Mean ground speed Q to P 280 K,Find: (i) fuel to be lifted at P, (ii) Maximum traffic load P to Q (iii) Maximum traffic load Q to P.

6. The empty mass of an aero plane is given as 44800kg. Operational items (including crew standard mass of 1060kg) are 2300kg. If the maximum zero fuel mass is given as 65500kg, the maximum traffic load which could be carried is

7. The center of gravity is the

8. When the center of gravity is the forward limit, an aero plane will be

9. The mass of an aero plane weighing more than 2000 Kgs must be determined prior to initial entry into service and thereafter

10. The Zero Fuel Mass and the Dry Operating Mass

11. The center of gravity of a body is that point

12. When an aero plane is stationary on the ground, its total weight will act vertically

13. At the flight preparation stage, the following parameters in particular are available for determining the mass of the aircraft: 1. Dry operating mass, 2. Operating mass Which statement is correct

14. Dry operating mass = 38 000 kg, Maximum structural take-off mass = 72 000 kg, Maximum landing mass = 65 000 kg, Maximum zero fuel mass = 61 000 kg, Fuel burn = 8 000 kg, Take-off Fuel = 10 300 kg, The maximum allowed take-off mass and payload are respectively

15.

MZFM is given as 47,000 kg, the MTOM IS 62,800 kg and the MLM is 54,900 kg. let us assume that there are no performance Limits so that the Regulated Take-off and Landing messes are equal to the Structural Limited Take-off Mass and the Structural Limited Land Mass respectively. Let us also assume that the DOM is 34,000kg that the actual traffic load is 12,400kg, the take off fuel load is 16,000 and 8,000 kg of fuel was used in flight. Can extra load be carried? If yes, how much?

16. The Dry Operating Mass of an aircraft is 2 000 kg. The maximum take-off mass, landing and zero fuel mass are identical at 3500 kg. The block fuel mass is 550kg, and the taxi fuel mass is 50 kg. The available mass of payload is

17.

APS weight = 40.oo t RLW = 49.55 t RTOW = 65.00 t MZFW = 48.00 t Burn-off = 12.89 t Reserve = 1.65 t Calculate the maximum permissible TOM and payload.

18. As aircraft basic empty mass is 3000 kg. The maximum take-off, landing, and zero-fuel mass are identical, at 5200 kg. Ramp fuel is 650 kg, the taxi fuel is 50 kg. The payload available is

19. Determine the Landing Mass for the following single engine aero plane. Standard Empty Mass : 1764 lbs, Optional Equipment: 35 lbs, Pilot + Front seat passenger : 300 lbs, Cargo Mass : 350 lbs, Ramp Fuel = Block Fuel : 60 Gal. Trip Fuel : 35 Gal. Fuel density : 6 lbs/Gal.

20. The Dry Operating Mass of an aero plane includes

21. If the details of an aircraft from M to N are given below. No fuel is available at N. Distance M to N 740nm, Average TAS 380 K, Wind component M to N 30 K HW, Average fuel flow 57 Kg/hr, Fuel reserve (assume unused) 500 Kg, Ac mass less fuel & traffic load 52000 Kg, Max T/O mass at M 91000 Kg, Max T/O mass at N 88000 Kg, Max landing mass at N 77500 Kg, Max landing mass at M 75000 Kg. Find : (i) Max traffic load from M to N, (ii) Max traffic load from N to M

22. A revenue flight is planned for the transport aero\plane. The take-off mass is not airfield limited. The following data applies: Dry Operating Mass: 34930kg, Performance limited landing mass : 55000kg Fuel on board at ramp: Taxi fuel : 350kg, Trip fuel : 9730kg Contingency and final reserve fuel : 1200kg, Alternate fuel : 1600kg, Passengers on board : 130, Standard mass for each passenger: 84kg, Baggage per passenger: 14kg Traffic load: Maximum possible Determine the maximum cargo load that may be carried without exceeding the limiting aero plane landing mass.

23. An aero plane it said to be "neutrally stable", This is likely to

24. In relation to an aero plane the Dry Operating Mass is the total mass of the aero plane ready for a specific type of operation but excluding

25. Aero plane Dry Operating Mass : 85000kg, Performance limited take-off mass: 127000kg, Performance limited landing mass: 98500kg, Maximum zero fuel mass: 89899kg, Fuel requirements for flight: Trip fuel : 29300kg, Contingency and final reserve fuel:3600kg, Alternate fuel:2800kg. The maximum traffic load that can be carried on this flight is

26. What determines the longitudinal stability of an aero plane?

27. On an aero plane without central fuel tank, the maximum Zero Fuel Mass is related to

28. A revenue flight is to be made by a jet transport. The following are the aero plane's structural limits: Maximum Ramp Mass:69 900 kg, Maximum Take Off Mass : 69 300 kg, Maximum Landing Mass: 58 900 kg, Maximum Zero Fuel Mass : 52 740 kg, The performance limited take off mass is 67 450kg and the performance limited landing mass is 55 470 kg. Dry Operating Mass : 34 900 kg, Trip Fuel : 6 200 kg, Taxi Fuel : 250 kg, Contingency & final reserve fuel : 1 300 kg, Alternate Fuel : 1 100 kg, The maximum traffic load that can be carried is

29. Prior to departure an aero plane is loaded with 16500 litres of fuel at a density of 780kg/m∧3. This is entered into the load sheet as 16500kg and calculations are carried out accordingly. As a result of this error, the aero plane is

30. The center of gravity of an aero plane

31. When establishing the mass breakdown of an aero plane, the empty mass is defined as the sum of the

32. Max T/o mass - 51.00 Tone, RTOM - 50.00 Tone, Max landing mass - 44.20 Tone, RLM - 43.20 Tone, Max Zero fuel mass- 45.10 Tone, APS mass - 27.50 Tone, Trip fuel - 4.2 Tone. Reserve fuel - 1.00 Ton. Find the traffic load that can be carried

33. An aero plane is weighted and the following recordings are made: nose wheel assembly scale 5330kg, left main wheel assembly scale 12370kg, right main wheel assembly scale 12480kg, If the "operational items" amount to a mass of 1780kg with a crew mass of 545kg, the empty mass, as entered in the weight schedule, is

34. An aero plane must be re-weighed at certain intervals, Where an operator uses an aircraft weighing less than 2000 kgs, this interval is

35. Maximum structural take off mass 80000 lbs, Maximum structural landing mass 64 500 lbs, Dry operating mass 50000 lbs, Flight fuel 6000 kgs. Reserve fuel 1500 kgs. Find the traffic load that can be carried

36. During take-off you notice that, for a given elevator input, the aero plane rotates much more rapidly than expected. This is an indication that

37. An aero plane is to depart from an airfield at a take-off mass of 302550 kg. Fuel on board at take-off (including contingency and alternate of 19450 kg) 121450 kg. The Dry Operating Mass is 161450 kg. The useful load will be

38. If an aero plane is at a higher mass than anticipated, for a given airspeed the angle of attack will

39. In relation to an aero plane, the term 'Basic Empty Mass' includes the mass of the aero plane structure complete with its powerplants, systems, furnishing and other items of equipment considered to be an integral part of the particular aero plane configuration. Its value is

40.

Load sheet reads A/C wt, no fuel, no payload = 63,200 kg Max TOW = 99,000 kg Route-fuel (excluding reserve) = 18,200 kg Reserve (assume unused) = 3,000 kg, If max landing weight is 76,500 kg, and MZFW 74,000 kg, fine: (a) TOW when maximum payload is carried. (b) Maximum payload.

41. The center of gravity of an aero plane is that point through which the total mass of the aero plane is said to act. The weight acts in a direction

42. Total mass : 7500 kg Center of Gravity (cg) location station : 80.5, Aft cg limit station :79.5 How much cargo must be shifted from the aft cargo compartment at station 150 to the forward cargo compartment at station 30 in order to move the cg location to the aft limit?

43. An aero plane may be weighted

44. If the center of gravity is near the forward limit the aero plane will

45. The following data is extracted from an aero plane's loading manifest: Performance limited take-off mass 93500 kg. Expected landing mass at destination 81700kg. Maximum certificated landing mass 86300 kg, Fuel on board 16500 kg, During the flight a diversion is made to an en-route alternate which is not performance limited' for landing. Fuel remaining at landing is 10300 kg. The landing mass

46. The maximum quantity of fuel can be loaded into an aero planes tanks is given as 3800 US Gallons. If the fuel density (specific gravity) is given as 0.79 the mass of fuel which may be loaded is

47. A flight benefits from a strong tail wind which was not forecast. On arrival at destination a straight in approach and immediate landing clearance is given. The landing mass will be higher than panned and

48. The position of the center of gravity can always be determined by

49. In relation to an aero plane, the term "Basic Empty Mass" includes the mass of the aero\plane structure complete with its power plants, systems, furnishings and other items of equipment considered to be an integral part of the particular aero plane configuration. It value is

50. An aero plane is loaded with its center of gravity towards the rear limit. This will result in