InterviewSolution

Explore topic-wise InterviewSolutions in .

This section includes InterviewSolutions, each offering curated multiple-choice questions to sharpen your knowledge and support exam preparation. Choose a topic below to get started.

51.	Sideslip sensors are only used in experimental aircraft and not in general aviation or commercial aircraft.(a) True(b) FalseI had been asked this question by my school principal while I was bunking the class.This is a very interesting question from Temperature, Angle of Attack and Angle of Side Slip Measurements in chapter Air Data Systems, Altitude and Heading Reference of Avionics
Answer» Correct ANSWER is (a) True The EXPLANATION is: Sideslip sensors are usually USED only in developmental flight test instrumentation and experimental aircraft. In commercial and general aviation aircraft, sideslip is approximated by a BODY mounted ACCELEROMETER and displayed on the pilot’s ball bank indicator.

52.	The angle between the relative wind and the longitudinal datum line on the fuselage is called as?(a) Flight path angle(b) Glide angle(c) Relative angle(d) Angle of attackThe question was asked during an internship interview.Enquiry is from Temperature, Angle of Attack and Angle of Side Slip Measurements in chapter Air Data Systems, Altitude and Heading Reference of Avionics
Answer» The correct choice is (d) Angle of attack The BEST I can explain: Angle of attack is the angle, in the normally vertical plane of symmetry of the aircraft, at which the relative wind MEETS an arbitrary longitudinal datum line on the fuselage. Angle of attack, is important as it corresponds to the amount of lift PRODUCED and the dangerous condition of stall.

53.	What error will a 10°C error in temperature shown in true airspeed?(a) 10 Knots(b) 20 Knots(c) 0.2 Knots(d) Greater than 1 KnotI have been asked this question in exam.My question is taken from Temperature, Angle of Attack and Angle of Side Slip Measurements in portion Air Data Systems, Altitude and Heading Reference of Avionics
Answer» The correct option is (d) Greater than 1 Knot To explain: A 10°C error in the temperature will RESULT in a true airspeed greater than 1 knot at a TYPICAL TRANSPORT aircraft flight CONDITIONS.

54.	The temperature is probe is actually an electric coil whose resistance varies with temperature.(a) True(b) FalseI got this question by my school principal while I was bunking the class.My enquiry is from Temperature, Angle of Attack and Angle of Side Slip Measurements topic in section Air Data Systems, Altitude and Heading Reference of Avionics
Answer» Correct OPTION is (a) True The BEST I can explain: The temperature PROBE mounted on the outside of the aircraft is usually a small coil of wire whose RESISTANCE varies with temperature. ELECTRIC heaters used for deicing must be isolated from thermometer element.

55.	The recovery factor for computing the static temperature does not account for _____(a) Friction heating(b) Re-radiation(c) Nonisentropic compression(d) Isentropic compressionI got this question during an interview.Query is from Temperature, Angle of Attack and Angle of Side Slip Measurements in section Air Data Systems, Altitude and Heading Reference of Avionics
Answer» The correct answer is (d) Isentropic compression The explanation is: The RECOVERY factor of the probe corrects the ORIGINAL MEASURED temperature readings for frictional HEATING in the SKIN, re-radiation from the aircraft to the flow, and nonisentropic compression of air. It is given by η and is measured empirically.

56.	Which is the optimum place for a temperature probe?(a) Landing gear(b) Inside cockpit(c) Exit of engine(d) Tip of vertical tailI have been asked this question in semester exam.My doubt stems from Temperature, Angle of Attack and Angle of Side Slip Measurements topic in division Air Data Systems, Altitude and Heading Reference of Avionics
Answer» CORRECT choice is (d) Tip of vertical tail For EXPLANATION: Probes may be MOUNTED on the wing tips, vertical tail, forward fuselage or other areas where the local mach NUMBER is the same as the free stream mach number for all EXPECTED flight altitudes and speeds.

57.	Why is a hole required at the rear end of the temperature probe?(a) Dual measurements(b) Redundancy(c) Reduce time lag(d) Convective coolingThe question was asked in exam.I'd like to ask this question from Temperature, Angle of Attack and Angle of Side Slip Measurements in division Air Data Systems, Altitude and Heading Reference of Avionics
Answer» Right option is (c) Reduce time lag To EXPLAIN I would say: To avoid time lags in the TEMPERATURE measurements, a leakage hole at the rear end of the probe ALLOWS for RAPID exchange. For REDUNDANCY, multiple temperature probes are placed in different parts of the aircraft.

58.	What is the temperature of the air surrounding the aircraft called as?(a) Stagnation temperature(b) Static temperature(c) Total temperature(d) Overall temperatureThis question was posed to me by my college professor while I was bunking the class.Asked question is from Temperature, Angle of Attack and Angle of Side Slip Measurements in division Air Data Systems, Altitude and Heading Reference of Avionics
Answer» Right choice is (b) STATIC temperature The best explanation: The outside air temperature is ALSO called the static air temperature and is necessary for computing various PARAMETERS such as true airspeed, air density and for fire control AIMING solutions.

59.	What is the temperature measured by a probe on the exterior of a moving aircraft?(a) Static temperature(b) Stagnation temperature(c) Free stream temperature(d) Constant temperatureThis question was posed to me in an interview for internship.The query is from Temperature, Angle of Attack and Angle of Side Slip Measurements in division Air Data Systems, Altitude and Heading Reference of Avionics
Answer» Correct option is (b) STAGNATION TEMPERATURE Best explanation: The temperature measured by the temperature probe on the exterior of a moving aircraft is called the stagnation temperature. It is always HIGHER than the STATIC temperature due to the heating effects of compressing AIR at higher speeds.

60.	At supersonic speeds, a normal pitot tube cannot be used for speed measurements.(a) True(b) FalseI had been asked this question during an interview.I'm obligated to ask this question of Pressure Measurements topic in chapter Air Data Systems, Altitude and Heading Reference of Avionics
Answer» The CORRECT answer is (a) True To explain: At supersonic speeds, the pressure sensed inside the pitot tube is ideally the pressure after the formation of shock WAVES inside the tube. Hence the value of stagnation pressure is DIFFERENT from that ACTUALLY EXPERIENCED by the aircraft.

61.	Which of the following instruments use the pitot-static probe for its input?(a) Airspeed indicator(b) Altitude indicator(c) Vertical speed indicator(d) Attitude indicatorI have been asked this question by my college director while I was bunking the class.Enquiry is from Pressure Measurements in portion Air Data Systems, Altitude and Heading Reference of Avionics
Answer» The correct CHOICE is (d) Attitude indicator For explanation: The instruments that use pitot-static PROBE are AIRSPEED indicator, altitude indicator or the altimeter and the vertical SPEED indicator. The attitude indicator uses the gyro to MEASURE the orientation of the aircraft.

62.	The impact pressure and the dynamic pressure are the same.(a) True(b) FalseThis question was posed to me during an online interview.Enquiry is from Pressure Measurements in division Air Data Systems, Altitude and Heading Reference of Avionics
Answer» Right choice is (b) False To elaborate: Both impact and DYNAMIC pressures are the DIFFERENCE between the stagnation and the static pressure but impact pressure is the dynamic pressure with compressibility effects TAKEN into ACCOUNT.

63.	What is the difference between the static pressure and the stagnation pressure when the aircraft is stationary?(a) Infinite(b) Any random value(c) No difference(d) Static pressureThe question was posed to me by my school principal while I was bunking the class.This intriguing question originated from Pressure Measurements topic in division Air Data Systems, Altitude and Heading Reference of Avionics
Answer» Correct option is (d) Static pressure To elaborate: when the aircraft is stationary, the pressure SENSED by the static PORT is the free stream air pressure and the stagnation pressure ports are ZERO. Since the aircraft is not MOVING stagnation pressure is zero and hence the DIFFERENCE between the two values is the static pressure.

64.	What are the tubes in the aircraft that carry the air pressure to the instruments is called as?(a) Pneumatic plumbing(b) Pressure lines(c) Pressure tubes(d) Blue linesThis question was posed to me in a job interview.My question is from Pressure Measurements in portion Air Data Systems, Altitude and Heading Reference of Avionics
Answer» RIGHT OPTION is (a) Pneumatic plumbing The best I can explain: PIPES that carry the air pressure sensed from the pitot tube or the pitot-static tube to the air data COMPUTER and the various other flight instruments such as the airspeed indicator, altitude indicator and the vertical SPEED indicator is collectively referred to as pneumatic plumbing.

65.	What is the difference between the actual free stream pressure and the measured static pressure called?(a) Static error(b) Static defect(c) Free stream error(d) Dynamic pressureI have been asked this question in semester exam.I'd like to ask this question from Pressure Measurements in portion Air Data Systems, Altitude and Heading Reference of Avionics
Answer» Correct option is (B) Static defect The explanation: The pressure that is SENSED via the pitot-static port will be different from the actual free stream pressure due to the interference from the SKIN, angle of ATTACK and the sideslip angle. This difference is referred to as the static defect.

66.	Which of the following is done to reduce the static defect?(a) Streamlined configuration of the whole aircraft(b) Less weight as payload(c) Wind tunnel tests to find spots of body-flow interference(d) Deploy Flaps and slatsThe question was asked by my college director while I was bunking the class.The query is from Pressure Measurements topic in section Air Data Systems, Altitude and Heading Reference of Avionics
Answer» The correct option is (c) Wind tunnel tests to find SPOTS of BODY-flow interference Easy explanation: Various wind tunnel tests are done to predict the OPTIMUM location for the static port so that the interference of the flow with the body is minimum. Since static DEFECT is predictable, it can be corrected in the air-data computer.

67.	Where are self-aligning pitot tubes used?(a) Bomber planes(b) Commercial airliners(c) High angle of attack fighter aircraft(d) General aviationI got this question during an online exam.This is a very interesting question from Pressure Measurements topic in division Air Data Systems, Altitude and Heading Reference of Avionics
Answer» Right option is (c) High ANGLE of attack FIGHTER aircraft Explanation: When the angle of attack and the SIDESLIP angle are under 10°, they do not affect the pressure measurements much. In APPLICATIONS such as high angle of attack fighters, special self-aligning PITOT tubes are used to measure the stagnation pressure.

68.	The absolute pressure of the still air surrounding the aircraft is called as______(a) Static pressure(b) Stagnation pressure(c) Constant pressure(d) Absolute pressureI have been asked this question in homework.The query is from Pressure Measurements topic in division Air Data Systems, Altitude and Heading Reference of Avionics
Answer» Right choice is (a) Static pressure Explanation: static pressure is the pressure of the still air SURROUNDING the aircraft BODY even when the aircraft is moving. It is measured using static PORTS PLACED ALONG the aircraft skin.

69.	The different probes that disturb the airflow is called ______(a) Air data probe(b) Data probe(c) Intrusive probe(d) Static probesThis question was posed to me in examination.The query is from Pressure Measurements in section Air Data Systems, Altitude and Heading Reference of Avionics
Answer» Right answer is (c) Intrusive probe The best explanation: All of the SENSING PROBES, EXCEPT for the flush mounted STATIC probe, are intrusive because they disturb the local flow over the BODY of the aircraft. Thus they are also called intrusive probes.