3 FLIG. PER. EXAM. PREP.

1. 151 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?]
   

   1. AO '18,3 USG.
   2. BO '16,2 USG.
   3. CO '15,7 USG.
   4. DO '17,1 USG.
2. 252 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?
   

   1. AO '15 USG.
   2. BO '12 USG.
   3. CO '6 USG.
   4. DO '9 USG.
3. 353 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
   

   

   1. AO '105 Ib.
   2. BO '120 Ib.
   3. CO '90 Ib.
   4. DO '751b.
4. 454 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
   

   

   1. AO '83.0 within limits.
   2. BO '78.2. out of the CG envelope.
   3. CO '88.3. within limits.
   4. DO '80,2. out of the CG envelope.
5. 555 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
   

   

   1. AO '40 USG.
   2. BO '34 USG.
   3. CO '24 USG.
   4. DO '46 USG.
6. 656 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.
   

   

   1. AO '77,7 Ib-inches.
   2. BO '69,9 Ib-inches.
   3. CO '73,9Ib-inches.
   4. DO '38,7Ib-inches.
7. 757 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/
   

   

   1. AO within limits, normal category.
   2. BO within limits, utility category.
   3. CO out of the CG envelope, to the left of the diagram.
   4. DO out of the CG envelope ,to the right of the diagram.]
8. 858 The Accelerate-Stop Distance Available is :
   

   1. AO TORA + Stopway
   2. BO TORA + Clearway + Stopway
   3. CO TORA + Clearway
   4. DO Stopway + Clearway + Taxiway
9. 959 The Take-off Distance Available is :
   

   1. AO TORA + Clearway
   2. BO TORA + Stopway
   3. CO TORA + Stopway + Clearway
   4. DO None of them.
10. 1060 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 :
    

    1. AO (ι) 15°C (ιι) 1013 hPa (ιιι) 1.225 kg/m³ (iv) 6.5°C/1000m
    2. BO (ι) -15°C (ιι) 1013 mb (ιιι) 1.225 kg/m³ (iv) 35.6°F/1000ft
    3. CO (ι) ISA+15 (ιι) 1.013 mb (ιιι) 1225 g/m² (iv) 1.98°C/1000ft
    4. DO (ι) 15°C (ιι) 29.92 in.Hg (ιιι) 1013.25 kg/m³ (iv) 19.8°C/1000m.

11. 1161 The Service Ceiling is the pressure altitude where :
    

    1. AO the rate of climb reaches a specified value,
    2. BO the rate of climb is zero
    3. CO the rate of climb is 100fpm.
    4. DO the a/c flies more efficient.
12. 1263 The load factor is the:
    

    1. AO Total lift/ Weight ratio.
    2. BO Ratio of Lift/ Drag at the neutral angle of attack
    3. CO Same independently of the a/c's attitude.
    4. DO Thrust/ Weight ratio.
13. 1364 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
    

    1. AO (i) sea level (ii) above sea level
    2. BO (i) Sea level (ii) Sea level
    3. CO (i) above sea level (ii) below sea level
    4. DO (i) below sea level (ii) above sea level
14. 1465 The rolling friction drag of an aircraft's wheels during take-off:
    

    1. AO Depends on the total load on the wheels and decreases during take-off.
    2. BO Depends on the aircraft weight and is constant during take-off.
    3. CO Is of no value.
    4. DO Depends on tire's air-tube distortion and increases with speed during take-off.
15. 1566 The speeds Vx and Vy are, respectively?
    

    1. AO Speed for best angle of climb and speed for best rate of climb
    2. BO Maximum achievable speed with max. continuous thrust and maximum take-off thrust
    3. CO Speed for best rate of climb and speed for best angle of climb
    4. DO Max. speed with flap extended and max. speed with gear extended
16. 1667 For a given aircraft mass, the climb gradient:
    

    1. AO decreases if flap angle increases, and if temperature increases.
    2. BO increases if flap angle increases, and if temperature decreases.
    3. CO decreases if flap angle increases, and if temperature decreases.
    4. DO increases if flap angle increases, and if temperature increases.
17. 1768 With a headwind, compared to still air conditions, the rate of climb (i) and the climb angle, relative to the ground (ii) will:
    

    1. AO (i) remain the same (ii) increase,
    2. BO (i) increase (ii) increase
    3. CO (i) Decrease (ii) decrease
    4. DO (i) increase, (ii) remain the same
18. 1869 Consult Fig. 5. The rate of climb depends on :
    

    

    1. AO the excess power available
    2. BO the excess thrust available
    3. CO the excess total lift available
    4. DO the CLmax on each wing.
19. 1970 The speed to give the maximum rate of climb, will be :
    

    1. AO higher than the speed for best angle of climb, at any altitude.
    2. BO always the same as the speed for best angle of climb, at any altitude.
    3. CO is the same to all light aircrafts.
    4. DO lower than the speed for best angle of climb, at any altitude.
20. 2071 Consult Fig.5. With increasing altitude, the rate of climb :
    

    

    1. AO decreases because power available decreases and power required increases.
    2. BO decreases because power available decreases and power required is constant.
    3. CO remains constant.
    4. DO decreases because power available is constant and power required increases.
21. 2172 In a power-off glide in still air, to obtain the maximum glide range, the aircraft should be flown at a speed:
    

    1. AO corresponding to maximum L / D,
    2. BO close to the stall.
    3. CO corresponding to minimum Cd.
    4. DO close to VA
22. 2273 The climb gradient will be reduced in conditions of :
    

    1. AO high temperature, high pressure altitude, contaminated airframe.
    2. BO high mass, low temperature, high flap angle
    3. CO high pressure altitude, low DA, low temperature
    4. DO power required will be decreased.
23. 2374 When an aircraft reaches its service ceiling :
    

    1. AO it will have a small positive rate of climb
    2. BO the excess power will be zero
    3. CO the rate of climb will be zero
    4. DO power required will decrease.
24. 2475 In a power-off glide, an increase in aircraft mass will;
    

    1. AO not affect the glide angle, but increase the speed for minimum glide angle,-,
    2. BO increase the glide angle and increase the speed for minimum glide angle,
    3. CO increase the glide angle, but not affect the speed for minimum glide angle,
    4. DO not affect anything at all.
25. 2576 The minimum total drag of an aircraft in level flight occurs :
    

    1. AO when CL / CD is a maximum.
    2. BO when the induced drag is a minimum and the parasite is maximum.
    3. CO when the parasite drag is a minimum and the induced is maximum.
    4. DO when CDtota| is a minimum

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3 FLIG. PER. EXAM. PREP.

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