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CPL Test Series
Question Bank
Questions for DETERMINATION OF TEMP
Answer the following questions
Test Mode
Training Mode
1. When climbing through an inversion at constant mach number?
TAS increases.
CAS increases.
TAS remains constant
2. If indicated TAT is - 10°C, pressured altitude is 30000 ft. amsl, and mach number is 0.84, what is the temperature deviation?
2°C.
-4°C.
4°C.
3. CAS is IAS corrected for
density error.
instrument error.
position error.
4. When descending through an isothermal level the TAS will _____, the CAS and the LSS will ________ :
Increase, increase, decrease
remain constant, increase, remain constant
remain constant, decrease, increase
5. An Air Data Computer (ADC)
transforms air data measurements into electric impulses driving servo motors in instruments
measures position error in the static system and transmits this information to ATC to provide correct altitude reporting
is an auxiliary system that provides altitude information in the event that the static source is blocked
6. TAT = -25°. SAT = -35°. Find TAS.
- [-25° = -35°[TAS/87.1]2 ; + √10 = [TAS/87.1] ; TAS = 275.4 KTS.]
- [-25° = -35°[TAS/87.1]2 ; + √10 = [TAS/87.1] ; TAS = 273.4 KTS.]
7. The Airspeed Indicator measures
Differential pressure changes
Static pressure changes.
Differential pressure
8. If pressure altitude is 30000 ft., indicated TAT is -10°C, mach number is 0.82, what is the density altitude?
30674 ft.
31000 ft.
30472 ft.
9. 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
-2.5
+5
-5
10. As pressure altitude increases
Temperature decreases.
Temperature increases then remains constant.
Temperature decreases then remains constant.
11. EAS is
CAS corrected for position error
CAS corrected for compressibility
IAS corrected for compressibility
12. A/C is flying at TAS = 400 Kts. SAT = -23°. Find Dynamic rise in temperature
- [DYNAMIC RISE = [TAS/87.1]2 = [400/87.1]2 = 22.09°C.]
- [DYNAMIC RISE = [TAS/87.1]2 = [400/87.1]2 = 21.09°C.]
13. Calibrated air speed is
IAS plus the pressure error
IAS plus density error correction
IAS plus instrument error correction
14. Cruising at FL 390, M.84 is found to give a TAS of 499kt. The ISA deviation at this level will be
-19.
+19.
+17.
15. When descending through an inversion at constant CAS?
Mach number remains constant.
Mach number increases.
TAS decreases.
16. The difference between static air temperature and total air temperature is known as
the ram rise
hot ramp radiation
corrected outside are temperature
17. When climbing through an inversion at constant TAS.
Mach number decreases.
Mach number remains constant.
Mach number increases.
18. When descending through an isothermal layer at a constant Calibrated Airspeed (CAS), the True Airspeed (TAS) will
decrease
increase at a linear rate
increase at an exponential rate
19. An aircraft is flying at FL390, temperature -56.5° C at Mach0.85. The TAS of the aircraft is
472
561
485
20. Total Air Temp is always... than Static Air Temp and the difference varies with....
warmer, TAS.
warmer, altitude.
colder, CAS.
21. In An Air Data Computer (ADC), aero plane altitude is calculated from
The difference between absolute and dynamic pressure at the fuselage
Measurement of outside air temperature (OAT)
Measurement of absolute barometric pressure from a static source on the fuselage
22. When descending through an isothermal layer at a constant Calibrated Airspeed (CAS), the True Airspeed (TAS) will?
Increase at an exponential rate.
Remain constant.
Decrease
23. As pressure altitude increases when climbing at constant mach number?
TAS will increase.
TAS will decrease then remain constant.
CAS will decrease then remain constant.
24. An aircraft is flying at mach 0.86 and the true ambient air temperature is - 42°C. Determine
- [LSS = 39 × √ - 42 + 273 = 39 ×√231 = 593 KTS (B) 0.86 = TAS/593 TAS = 593 × 0.86 = 513 KTS.]
- [LSS = 39 × √ - 42 + 273 = 39 ×√231 = 593 KTS (B) 0.86 = TAS/593 TAS = 593 × 0.86 = 510 KTS.]
25. If pressure altitude is 30000 ft amsl and mach number is 0.84 what is the ISA TAT?
10°C
-12°C.
-10°C.
26. At any given height or altitude, an aircraft will always lift-off at the same?
Ground speed.
CAS.
EAS.
27. As pressure altitude increases when climbing at constant IAS?
TAS will increase.
CAS will decrease.
CAS will increase.
28. 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?
- [MACH NUMBER = TAS/LSS ; LSS = 80/12 = 669 KTS.]
- [MACH NUMBER = TAS/LSS ; LSS = 80/12 = 667 KTS.]
29. When climbing through an inversion at constant CAS?
TAS increases.
TAS remains constant.
Mach number decreases.
30. At a constant Mach number, the calibrated airspeed (CAS)
decreases when the altitude increases
remains unchanged when the outside temperature increases
increases when the altitude increases
31. An increase of 0.15 Mach results in an increase of 93 kt TAS of an aircraft. The local speed of sound is
580 kt
620 kt
560 kt
32. 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?
020°/95 kts.
025°/90 kts.
020°/80 kts.
33. FL250,OAT -15°C, TAS 250 kt, Calculate the Mach No.?
0.40.
0.45.
0.38.
34. TAS 487kt, FL 330, Temperature ISA + 15. Calculate the MACH number?
0.81.
0.83.
0.79.
35. For a constant Calibrated Airspeed (CAS) and a level flight, a fall in ambient temperature will result in a
higher True Air Speed (TAS) due to an decrease in air density
higher True Air Speed (TAS) due to an increase in air density
lower True Air Speed (TAS) due to an increase in air density
36. TAS = 485 kt, OAT = ISA + 10°C, FL 410. Calculate the Mach number?
0.825.
0.852.
0.833.
37. When descending through an inversion at constant TAS?
Mach number increases.
CAS decreases.
Mach number remains constant.
38. When descending through an inversion at constant CAS?
Mach number increases.
TAS increases.
TAS decreases.
39. When climbing at a constant Mach number below the tropopause, in ISA conditions =, the Calibrated Airspeed (CAS) will
increase at an exponential rate
decrease
increase at a linear rate
40. When climbing through an inversion at constant CAS?
Mach number decreases.
TAS increases.
TAS decreases.
41. A/C is flying at TAS = 520 Kts. SAT is - 20°C. Find TAT.
- [TAT = SAT+ [TAS/87.1]2 = -20°C+[520/87.1]2 = 15.64°C.]
- [TAT = SAT+ [TAS/87.1]2 = -20°C+[520/87.1]2 = 15.63°C.]
42. The velocity of sound at the sea level in a standard atmosphere is
644kt
661kt
1059kt
43. What corrections must be applied to indicated airspeed to produce true airspeed?
Correction for heading and altitude.
Correction for altitude and temperature.
Correction for altitude and wind.
44. Total air temp is _____ than _____ by an amount which is proportional to _____.
Higher, SAT, CAS
Higher, SAT, TAS
Higher, SAT, LSS
45. When climbing through an isothermal layer at constant TAS?
Mach number remains constant.
Mach number increases.
Mach number decreases.
46. A temperature sensor having a recovery factor of 0.75 indicates 30°C. Static Air Temperature (SAT) is 25°C. How high is the Ram-rise?
5°C.
18.8°C
6.7°C.
47. EAS is?
CAS corrected for adiabatic compression.
IAS corrected for adiabatic compression.
IAS corrected for pressure sensing errors.
48. Mach number is the ratio of?
CAS:LSS.
TAS:LSS.
IAS:TAS.
49. When descending through an isothermal layer at constant TAS?
Mach number increases.
Mach number decreases.
Mach number remains constant.
50. 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?
050°(T) / 75 kt.
050°(T) / 50 kt.
050°(T) / 70 kt.
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