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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 CAS?
TAS remains constant.
Mach number decreases.
TAS increases.
2. In An Air Data Computer (ADC), aero plane altitude is calculated from
Measurement of absolute barometric pressure from a static source on the fuselage
The difference between absolute and dynamic pressure at the fuselage
Measurement of outside air temperature (OAT)
3. 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
-5
-2.5
+5
4. When descending through an inversion at constant CAS?
TAS decreases.
TAS increases.
Mach number increases.
5. At any given height or altitude, an aircraft will always lift-off at the same?
Ground speed.
CAS.
EAS.
6. An Air Data Computer (ADC)
transforms air data measurements into electric impulses driving servo motors in instruments
is an auxiliary system that provides altitude information in the event that the static source is blocked
measures position error in the static system and transmits this information to ATC to provide correct altitude reporting
7. EAS is?
CAS corrected for adiabatic compression.
IAS corrected for pressure sensing errors.
IAS corrected for adiabatic compression.
8. When climbing through an inversion at constant mach number?
TAS increases.
CAS increases.
TAS remains constant
9. An increase of 0.15 Mach results in an increase of 93 kt TAS of an aircraft. The local speed of sound is
560 kt
580 kt
620 kt
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?
- [MACH NUMBER = TAS/LSS ; LSS = 80/12 = 669 KTS.]
- [MACH NUMBER = TAS/LSS ; LSS = 80/12 = 667 KTS.]
11. EAS is
CAS corrected for compressibility
IAS corrected for compressibility
CAS corrected for position error
12. FL 350, Mach 0.80, OAT - 55°C. Calculate the values for TAS and local speed of sound (LSS)?
460 kt, LSS 567 kt.
465 kt, LSS 575 kt.
460 kt, LSS 575 kt.
13. TAS 487kt, FL 330, Temperature ISA + 15. Calculate the MACH number?
0.83.
0.79.
0.81.
14. CAS is?
EAS corrected for position error and compressibility error.
IAS corrected for position error and instrument error.
IAS corrected for density error and position error.
15. As pressure altitude increases when climbing at constant IAS?
TAS will increase.
CAS will increase.
CAS will decrease.
16. At a fixed pressure altitude an increase in temperature will?
Not affect density altitude.
Increase density but decrease density altitude.
Decrease density but increase density altitude.
17. FL250,OAT -15°C, TAS 250 kt, Calculate the Mach No.?
0.38.
0.45.
0.40.
18. 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.
19. CAS is IAS corrected for
position error.
instrument error.
density error.
20. When descending through an isothermal layer at a constant Calibrated Airspeed (CAS), the True Airspeed (TAS) will?
Remain constant.
Increase at an exponential rate.
Decrease
21. Mach number is the ratio of?
TAS:LSS.
IAS:TAS.
CAS:LSS.
22. Total Air Temp is always... than Static Air Temp and the difference varies with....
warmer, TAS.
colder, CAS.
warmer, altitude.
23. When descending through an isothermal layer at constant TAS?
Mach number increases.
Mach number decreases.
Mach number remains constant.
24. What corrections must be applied to indicated airspeed to produce true airspeed?
Correction for altitude and wind.
Correction for heading and altitude.
Correction for altitude and temperature.
25. 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) / 50 kt.
050°(T) / 70 kt.
050°(T) / 75 kt.
26. Total air temp is _____ than _____ by an amount which is proportional to _____.
Higher, SAT, TAS
Higher, SAT, LSS
Higher, SAT, CAS
27. The velocity of sound at the sea level in a standard atmosphere is
1059kt
644kt
661kt
28. 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?
18.8°C
6.7°C.
5°C.
29. If pressure altitude is 30000 ft., indicated TAT is -10°C, mach number is 0.82, what is the density altitude?
30674 ft.
30472 ft.
31000 ft.
30. When descending through an inversion at constant TAS?
Mach number remains constant.
CAS decreases.
Mach number increases.
31. 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°/80 kts.
020°/95 kts.
025°/90 kts.
32. If the outside temperature at 35000ft is -40°C , the local speed of sound is
596kt
307kt
686kt
33. When descending through an isothermal layer at constant CAS?
Mach number increases.
Mach number remains constant.
Mach number decreases.
34. 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 = 15.63°C.]
- [TAT = SAT+ [TAS/87.1]2 = -20°C+[520/87.1]2 = 15.64°C.]
35. As pressure altitude increases
Temperature decreases.
Temperature increases then remains constant.
Temperature decreases then remains constant.
36. If pressure altitude is 30000 ft amsl and mach number is 0.84 what is the ISA TAT?
-12°C.
-10°C.
10°C
37. As pressure altitude increases when climbing at constant mach number?
TAS will decrease then remain constant.
CAS will decrease then remain constant.
TAS will increase.
38. 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
lower True Air Speed (TAS) due to an increase in air density
higher True Air Speed (TAS) due to an increase in air density
39. The difference between static air temperature and total air temperature is known as
hot ramp radiation
the ram rise
corrected outside are temperature
40. IAS 120 kt, FL 80, OAT + 20°C. What is the TAS?
135 kts.
141 kts.
144 kts.
41. When climbing at a constant Mach number below the tropopause, in ISA conditions =, the Calibrated Airspeed (CAS) will
decrease
increase at a linear rate
increase at an exponential rate
42. 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.]
43. TAS = 485 kt, OAT = ISA + 10°C, FL 410. Calculate the Mach number?
0.852.
0.833.
0.825.
44. When climbing through an isothermal layer at constant TAS?
Mach number increases.
Mach number decreases.
Mach number remains constant.
45. An aircraft is flying at FL390, temperature -56.5° C at Mach0.85. The TAS of the aircraft is
472
561
485
46. When descending through an inversion at constant mach number?
CAS decreases.
TAS increases.
TAS decreases.
47. 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
48. 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 = 510 KTS.]
- [LSS = 39 × √ - 42 + 273 = 39 ×√231 = 593 KTS (B) 0.86 = TAS/593 TAS = 593 × 0.86 = 513 KTS.]
49. If mach number is 0.88 and TAT is -4°C, what is the pressure altitude in the international standard atmosphere?
28000 ft.
26000 ft.
22000 ft.
50. 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.]
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