Question Bank

1. When climbing through an inversion at constant CAS?

2. Total air temp is _____ than _____ by an amount which is proportional to _____.

3. If indicated TAT is - 10°C, pressured altitude is 30000 ft. amsl, and mach number is 0.84, what is the temperature deviation?

4. As pressure altitude increases

5. Mach number is the ratio of?

6. When descending through an isothermal layer at constant TAS?

7. If pressure altitude is 40,000 ft. amsl, indicated TAT is -29°C what is the mach number assuming ISA conditions?

8. CAS is IAS corrected for

9. M 0.80, OAT - 50°C, FL 330, GS 490 kt, VAR 20°W, Magnetic heading 140°, drift is 11° right. Calculate the true W/V?

10. If a Decrease of 0.12 in the Mach number results in a decrease of 80 Knots in the TAS, what is the local speed of sound?

11. For a constant Calibrated Airspeed (CAS) and a level flight, a fall in ambient temperature will result in a

12. When descending through an inversion at constant CAS?

13. When climbing through an inversion at constant CAS?

14. FL120, OAT is ISA standard, CAS is 200 kt, Track is 222°(M), Heading is 215°(M), Variation is 15°W. time to fly 105 NM is 21 MIN. what is the W/V?

15. EAS is?

16. When climbing through an inversion at constant TAS.

17. When descending through an isothermal layer at a constant Calibrated Airspeed (CAS), the True Airspeed (TAS) will?

18. The difference between static air temperature and total air temperature is known as

19. Total Air Temp is always... than Static Air Temp and the difference varies with....

20. An is aircraft flying at a TAS of 1100 knots at FL650. A change in 0.1M causes a change i TAS of 57 knots. The temperature deviation at FL 650 assuming an ISA atmosphere is

21. As pressure altitude increases when climbing at constant IAS?

22. TAS = 485 kt, OAT = ISA + 10°C, FL 410. Calculate the Mach number?

23. In An Air Data Computer (ADC), aero plane altitude is calculated from

24. When climbing at a constant Mach number below the tropopause, in ISA conditions =, the Calibrated Airspeed (CAS) will

25. FL250,OAT -15°C, TAS 250 kt, Calculate the Mach No.?

26. When descending through an isothermal layer at a constant Calibrated Airspeed (CAS), the True Airspeed (TAS) will

27. As pressure altitude increases when climbing at constant mach number?

28. At a fixed pressure altitude an increase in temperature will?

29. IAS 120 kt, FL 80, OAT + 20°C. What is the TAS?

30. When descending through an inversion at constant TAS?

31. A/C is flying at TAS = 400 Kts. SAT = -23°. Find Dynamic rise in temperature

32. An Air Data Computer (ADC)

33. When climbing through an inversion at constant mach number?

34. An increase of 0.15 Mach results in an increase of 93 kt TAS of an aircraft. The local speed of sound is

35. When climbing through an isothermal layer at constant TAS?

36. The Airspeed Indicator measures

37. If pressure altitude is 30000 ft amsl and mach number is 0.84 what is the ISA TAT?

38. Cruising at FL 390, M.84 is found to give a TAS of 499kt. The ISA deviation at this level will be

39. M: Mach number Ts: static temperature Tt: total temperature Which of the following statements is correct?

40. When descending through an inversion at constant CAS?

41. At any given height or altitude, an aircraft will always lift-off at the same?

42. A/C is flying at TAS = 520 Kts. SAT is - 20°C. Find TAT.

43. TAS 487kt, FL 330, Temperature ISA + 15. Calculate the MACH number?

44. TAT = -25°. SAT = -35°. Find TAS.

45. FL 350, Mach 0.80, OAT - 55°C. Calculate the values for TAS and local speed of sound (LSS)?

46. When descending through an isothermal level the TAS will _____, the CAS and the LSS will ________ :

47. When descending through an inversion at constant mach number?

48. If the outside temperature at 35000ft is -40°C , the local speed of sound is

49. EAS is

50. If pressure altitude is 30000 ft., indicated TAT is -10°C, mach number is 0.82, what is the density altitude?