3 FLIG. PER. EXAM. PREP.

51 If an aircraft is overloaded by 110 lbs (55 kgs),how much fuel does the pilot have to remove so that the aircraft loading will be within limits?]

52 If an aircraft is overloaded by 90 lbs (48 kgs),how much fuel has to be removed so that the aircraft loading will be within limits?

53 What is the maximum baggage weight that can be loaded on the aeroplane so that the center of gravity remains within limits?(Fig FPP07) Empty Weight = 1350 lb moment(/1000) = 51,5., Pilot and front passengers = 250 lb, Rear Passengers =400lbs, Fuel = (30

54 calculate the moment/1.000 of the following aircraft and check if it is loaded within the CG envelope limits.(Fig FPP07)], Βάρος κενό/Empty Weight = 1350 lb ροπή/moment(/1000) = 51,5. Πιλότος και επιβάτης εμπρός/Pilot and front passengers = 310 lb. Επιβάτ

55 What is the maximum amount of fuel which can be loaded on the aeroplane before take off, so that the total moment remains within the envelope limits? (Fig FPP07)]. Βάρος κενό/ Empty Weight = 1350 lb ροπή/moment(/1000) = 51,5. Πιλότος και επιβάτης εμπρός/P

56 Calculate the total moment and check if it is within the envelope limits. (Fig FPP07)]. Βάρος κενό/Empty Weight = 1350 lb ροπή/moment(/1000) = 51,5. Πιλότος και επιβάτης εμπρός/Pilot and front passengers = 340 lb. Επιβάτες πίσω/Rear Passengers = 310lbs.

57 Calculate the CG position and check if it is located within the envelope limits.(Fig FPP07)]. Βάρος κενό/Empty Weight = 1350 lb ροπή/moment(/1000) = 51,5. Πιλότος και επιβάτης εμπρός/Pilot and front passengers = 380 lb. Αποσκευές/Baggage = 45 lb. Καύσιμο/

58 The Accelerate-Stop Distance Available is :

59 The Take-off Distance Available is :

60 The International Standard Atmosphere defines an atmosphere where Sea level temperature (i) Sea level pressure (ii) Sea level density (iii) temperature lapse rate (iv) are :

61 The Service Ceiling is the pressure altitude where :

63 The load factor is the:

64 An aerodrome has a pressure of 1013 hPa and a temperature of 30°C(ISA+15), the pressure altitude (i) and the density altitude (ii) would be

65 The rolling friction drag of an aircraft's wheels during take-off:

66 The speeds Vx and Vy are, respectively?

67 For a given aircraft mass, the climb gradient:

68 With a headwind, compared to still air conditions, the rate of climb (i) and the climb angle, relative to the ground (ii) will:

69 Consult Fig. 5. The rate of climb depends on :

70 The speed to give the maximum rate of climb, will be :

71 Consult Fig.5. With increasing altitude, the rate of climb :

72 In a power-off glide in still air, to obtain the maximum glide range, the aircraft should be flown at a speed:

73 The climb gradient will be reduced in conditions of :

74 When an aircraft reaches its service ceiling :

75 In a power-off glide, an increase in aircraft mass will;

76 The minimum total drag of an aircraft in level flight occurs :