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50 Cards in this Set
- Front
- Back
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1. Describe the power units of B737 300/400/500 A. CFM 66 - 3A1 B. CFM 66 - 3B1 C. CFM 56 - 3C1 D. CFM 56 - 3D1 |
CFM 56 - 3C1 |
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2. The maximum operational altitude for B737 300/400/500 is A. 39.000 feet B. 37.000 feet C. 35.000 feet D. 33.000 feet |
37.000 feet |
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3. The maximum operational pressure altitude for takeoff and landing is A. 8.700 feet B. 8.600 feet C. 8.500 feet D. 8.400 feet |
8.400 feet |
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4. The maximum landing weight of B733 is A. 57.709 kg B. 57.907 kg C. 51.709 kg D. 51.907 kg |
51.709 kg |
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5. What flaps setting are available for landing B737 Classic ? A. 10, 30 and 40 degree B. 15, 30 and 40 degree C. 20, 30 and 40 degree D. 15, 25 and 40 degree |
15, 30 and 40 degree |
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6. What flaps setting are available for takeoff B734 ? A. 5 and 15 degree B. 1 and 5 degree C. 10 and 15 degree D. 1, 5 and 15 degree |
5 and 15 degree |
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7. The maximum tail wind component for takeoff and landing is A. 5 knots B. 10 knots C. 15 knots D. 25 knots |
10 knots |
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8. The maximum depth of standing water for takeoff is A. 13 mm B. 10 mm C. 8 mm D. 6 mm |
13 mm |
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9. The maximum demonstrated crosswind for takeoff and landing is A. 45 knots B. 35 knots C. 25 knots D. 10 knots |
35 knots |
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10. Field length available is displayed on AFM or on AOM chart form, the variables is/are : A. Pressure altitude B. Down slope or up slope C. DRY or WET runway D. All answer above are correct |
All answer above are correct |
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11. The required takeoff field length is A. Decreases with up slope condition B. Decreases with tail wind condition C. Increases with up slope condition D. Increases with down slope condition |
Increases with up slope condition |
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12. The required takeoff field length is A. Decreases with head wind condition B. Decreases with up slope condition C. Increases with head wind condition D. Increases with down slope condition |
Decreases with head wind condition |
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13. The required landing field length is A. Increases with up slope condition B. Increases with wet runway condition C. Decreases with down slope condition D. Decreases with tail wind condition |
Increases with wet runway condition |
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14. The required landing field length is A. Increases with down slope conditin B. Increases with up slope condition C. Decreases with down slope condition D. Decreases with wet runway condition |
Increases with down slope conditin |
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15. Given runway elevation PNK 10 feet, QNH 29.88 in Hg. Pressure altitude PNK is A. Zero feet B. 10 feet C. 50 feet D. 100 feet |
10 feet |
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16. Given runway number TIM 12 and 30, W/V is 240/40. The aircraft takeoff from runway 30, find the wind component. A. 20 knots cross wind and 34.5 knots tail wind B. 20 knots cross wind and 34.5 knots head wind C. 20 knots tail wind and 34.5 knots cross wind D. 20 knots head wind and 34.5 knots cross wind |
20 knots head wind and 34.5 knots cross wind |
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17. Refer question number 16 above, find the wind component if the aircraft takeoff from runway 12 A. 20 knots cross wind and 34.5 knots tail wind B. 20 knots cross wind and 34.5 knots head wind C. 20 knots tail wind and 34.5 knots cross wind D. 20 kmots head wind and 34.5 knots cross wind |
20 knots tail wind and 34.5 knots cross wind |
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18. Refer question number 16 above, find wind component if W/V 030/36 A. cross wind 36 knots and tail wind 36 knots B. cross wind 36 knots and head wind 36 knots C. cross wind 36 knots and tail wind 0 knots D. cross wind 0 knots and head wind 36 knots |
cross wind 36 knots and tail wind 0 knots |
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19. Refer question number 18 above, is it possible B737 classic for takeoff ? A. YES (Possible) B. NO (Impossible) |
NO (Impossible) |
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20. Refer question number 18 above, find the wind velocity if wind component 26 knots head and 15 knots cross wind A. W/V 030/30 B. W/V 330/30 C. W/V 270/30 D. Answer B and C above are correct |
Answer B and C above are correct |
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21. If power management control (PMC) ON A. Fuel consumtion increases B. Fuel consumtion decreases C. Takeoff weight decreases D. All answer above are false |
All answer above are false |
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22. Changing the takeoff flap setting from 5 to 1, the result is A. A longer takeoff field length and lower climb gradient B. A longer takeoff field length and better climb gradient C. A shorter takeoff field length and lower climb gradient D. A shorter takeoff field lenght and better climb gradient |
A longer takeoff field length and better climb gradient |
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23. Given runway length MDC 9000 feet, B737-300 takeoff with antiskid inoperative. Find the reduce weight. A. 5.000 kg B. 6.000 kg C. 7.000 kg D. 8.000 kg |
7.000 kg |
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24. If engine and wing anti-ice ON, the takeoff weight is A. Decreases B. Increases C. No effect D. All answer above are false |
Decreases |
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25. If A/C auto for packs off, the takeoff weight is A. Decreases B. Increases C. No effect D. All answer above are false |
Increases |
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26. Given takeoff weight 56.000 kg (DRY runway), runway elevation 4.000 feet, suddenly slush/Standing water depth 6 mm, maximum reverse thrust. Weight adjusment must be : A. Reduce B. Increase C. No correction D. All answer above are correct |
Reduce |
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27. Given runway length available 11.000 feet, elevation 1.000 feet, slope 1% up, temperature 34 deg. celsius, wind component 0 knots, flaps setting 1deg.Find takeoff weight B733/20 K. A. 62.000 kg B. 61.000 kg C. 60.000 kg D. 59.000 kg |
61.000 kg |
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28. Refer question number 27 above, find takeoff weight if engine anti-ice ON A. 61.800 kg B. 61.200 kg C. 60.800 kg D. 60.200 kg |
61.200 kg |
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29. Refer question number 27 above, find takeoff weight if temperature 25 deg. celcius and airport pressure altitude at MSL A. 61.000 kg B. 62.000 kg C. 63.000 kg D. 64.000 kg |
64.000 kg |
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30. Given takeoff climb limit at Kualanamu airport 55.500 kg, flap setting 5 deg. Find climb weight improvement, if takeoff weight limited by runway length is 65.000 kg. B733/20 K A. 4.000 kg B. 3.500 kg C. 3.000 kg D. 2.500 kg |
4.000 kg |
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31. Refer question number 30 above, find climb weight impromement if flaps setting 15 deg. A. 4.000 kg B. 3.500 kg C. 3.000 kg D. 2.500 kg |
3.500 kg |
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32. Refer question number 30 above, find takeoff weight at Kualanamu after improved climb A. 58.000 kg B. 58.500 kg C. 59.000 kg D. 59.500 kg |
59.500 kg |
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33. Given field length available 4.000 feet, runway surface DRY, airport pressure altitude at MSL, wind component 40 knots head, flaps setting 40 deg, anti skid normal. Find limited landing weight B737-300 A. 56.000 kg B. 55.800 kg C. 54.600 kg D. 53.400 kg |
54.600 kg |
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34. Refer question number 33 above, find limited landing weight if flaps setting 30 deg. A. 55.000 kg B. 53.000 kg C. 51.000 kg D. 50.000 kg |
53.000 kg |
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35. Trip fuel and time calculation on flight plan are based on : A. 290 KIAS / 0.94 M B. 290 KIAS / 0.84 M C. 280 KIAS / 0.94 M D. 280 KIAS / 0.74 M |
280 KIAS / 0.74 M |
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36. What is the requirement for level, flight single engine ? A. Single engine net ceiling must be 2.000 feet above obstacle B. Single engine net ceiling must be 1.500 feet above obstacle C. Single engine net ceiling must be 1.000 feet above obstacle D. Single engine gross ceiling must be 1.000 feet above obstacle |
Single engine net ceiling must be 1.000 feet above obstacle |
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37. One engine inoperative enroute, the flight level is : A. Higher than initial flight level B. Better than initial flight level C. Lower than initial flight level D. Answer A and B above are correct |
Lower than initial flight level |
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38. Fuel tank available Boeing 737-400 is A. 17.100 kg B. 16.100 kg C. 15.750 kg D. 14.750 kg |
17.100 kg |
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39. Refer question number 38 above, find the endurance if fuel flow 2.595 kg/hour A. 6 hours 35 minutes B. 6 hours 59 minutes C. 6 hours 12 minutes D. 6 hours 02 minutes |
6 hours 35 minutes |
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40. Engine fuel flow, which statement is correct ? A. Fuel flow increases with increases altitude B. Fuel flow decreases with decreases altitude C. Fuel flow decreases with increases altitude D. Fuel flow is constant at all altitude |
Fuel flow decreases with increases altitude |
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41. Given takeoff weight 58.000 kg, long range cruise / 0.74 M. Find the optimum altitude Boeing 737-400 is A. 32.000 feet B. 32.500 feet C. 33.000 feet D. 33.500 feet |
33.500 feet |
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42. Refer question number 41 above, determine the flight level from DPS to KOE (non RVSM flight) A. FL. 28.000 feet B. FL. 31.000 feet C. FL. 33.000 feet D. FL. 33.500 feet |
FL. 33.000 feet |
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43. What is the minimum block fuel for a flight with one destination alternate ? A. Trip fuel, route reserve, alternate and final reserve fuel B. Taxi fuel, trip fuel, alternate and final reserve fuel C. Trip fuel, fuel to alternate and final reserve fuel D. Taxi fuel, trip, route reserve, alternate and final reserve fuel |
Taxi fuel, trip, route reserve, alternate and final reserve fuel |
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44. What is the zero fuel weight ? A. Maximum takeoff weight minus payload and fuel required B. Aircraft weight, plus total fuel required C. Aircraft weight, payload, standard equipment and operation D. Aircraft weight, payload, and total fuel required |
Aircraft weight, payload, standard equipment and operation |
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45. What is ARM ? A. The horizontal distance from forward to aft in inches or meters B. The horizontal distance from body station to center of gravity C. The horizontal distance from reference datum to body station D. The true measure in inches from body station to center of gravity |
The horizontal distance from reference datum to body station |
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46. What is Index ? A. Moment divided with a constant B. A value use to facilitate the center of gravity calculation C. A value describing the moment at the center of gravity D. All answer above are correct |
All answer above are correct |
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47. The maximum fuel unbalance for taxi, takeoff, inflight and landing is A. 453 kg B. 435 kg C. 534 kg D. 543 kg |
453 kg |
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48. Given aircraft data's Boeing 737-500 / PK-MNA, below : Max. Takeoff weight : 55.882 kg Max. Zero Fuel Weight : 46.493 kg Max. Landing Weight : 49.895 kg kg D.O.W. : 32.088 kg Trip fuel : 4.700 kg Takeoff fuel : 8.500 Find the allowed traffic load A. 40.588 kg B. 14.070 kg C. 14.007 kg D. 14.700 kg |
14.007 kg |
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49. Refer question number 48 above, find the operating weight A. 50.488 kg B. 50.844 kg C. 40.584 kg D. 40.588 kg |
40.588 kg |
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50. Refer question number 48 above and 96 above, find the actual takeoff weight, if LMC two Passenger adult offload A. 54.545 kg B. 54.455 kg C. 55.455 kg D. 55.545 kg |
54.455 kg |
