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CPL Test Series
Question Bank
Questions for INDIGO INSTRUMENTS (1117-1427)
Answer the following questions
Test Mode
Training Mode
1.
The reading of a Mach indicator is independent of
the differential pressure measurement
the outside temperature
the total pressure
the static pressure
2.
A pilot wishes to turn left on to a southerly heading with 20° bank at a latitude of 20° North. Using a direct reading compass, in order to achieve this he must stop the turn on an approximate heading of
160°
190°
200°
170°
3.
An aeroplane is in a steady climb. The autothrottle maintains a constant Mach number. If the total temperature remains constant, the calibrated airspeed
remains constant
decreases if the static temperature is lower than the standard temperature, increases if higher.
decreases
increases.
4.
Indication of Mach number is obtained from
An ordinary airspeed indicator scaled for Mach numbers instead of knots
A kind of echo sound comparing velocity of sound with indicated speed
Indicated speed (IAS) compared with true air speed (TAS) from the air data computer
Indicated speed and altitude using a speed indicator equipped with an altimeter type aneroid
5.
A closed loop control system in which a small power input controls a much larger power output in a strictly proportionate manner is known as
a servomechanism
a feedback control circuit.
an amplifier
an autopilot.
6.
The operating principle of the vertical speed indicator (VSI) is based on the measurement of the rate of change of
Static pressure
Dynamic pressure
Kinetic pressure
Total pressure
7.
The purpose of the vibrating device of an altimeter is to
reduce the effect of friction in the linkages
inform the crew of a failure of the instrument
reduce the hysteresis effect
allow damping of the measurement in the unit
8.
A radio altimeter can be defined as a
ground radio aid used to measure the true altitude of the aircraft
self-contained on-board aid used to measure the true altitude of the aircraft
ground radio aid used to measure the true height of the aircraft
self-contained on-board aid used to measure the true height of the aircraft
9.
The velocity maximum operating (V.M.O.) is a speed expressed in
equivalent airspeed (EAS).
calibrated airspeed (CAS).
true airspeed (TAS).
computed airspeed (COAS).
10.
VLE is the maximum
speed at which the landing gear can be operated with full safety
flight speed with landing gear down
speed with flaps extended in a given position
speed authorized in flight
11.
Heading information given by a gyro platform, is given by a gyro at
2 degrees-of-freedom in the horizontal axis
2 degrees-of-freedom in the vertical axis
1 degree-of-freedom in the horizontal axis
l degree-of-freedom in the vertical axis
12.
A ""close traffic advisory"" is displayed on the display device of the TCAS 2 (Traffic Collision Avoidance System) by
an orange full circle
a blue or white full lozenge.
a blue or white empty lozenge
a red full square
13.
The Primary Flight Display (PFD) displays information dedicated to
systems.
weather situation
piloting.
engines and alarms
14.
The calibrated airspeed (CAS) is obtained by applying to the indicated airspeed (IAS)
an antenna and compressibility correction
a compressibility and density correction.
an instrument and position/pressure error correction.
and instrument and density correction
15.
The airspeed indicator of a twin-engined aircraft comprises different sectors and color marks. The blue line corresponds to the
speed not to be exceeded, or VNE
minimum control speed, or VMC
optimum climbing speed with one engine inoperative, or Vy
maximum speed in operations, or VMO
16.
If the static source to an altimeter becomes blocked during a climb, the instrument will
gradually return to zero
over-read
under-read by an amount equivalent to the reading at the time that the instrument became blocked
continue to indicate the reading at which the blockage occured
17.
The vertical speed indicator of an aircraft flying at a true airspeed of 100 kt, in a descent with a slope of 3 degrees, indicates
- 300 ft/min
- 250 ft/min
- 500 ft/min.
- 150 ft/min
18.
In automatic landing mode, in case of failure of one of the two autopilots, the system is considered
""fail passive"" or without failure effect but with disconnection
""fail hard"" or without failure effect and disconnection
""fail soft"" with minimized failure effect.
""fail survival"" or without failure effect with function always ensured
19.
During a Category II automatic approach, the height information is supplied by the
encoding altimeter
altimeter.
radio altimeter
GPS (Global Positioning System).
20.
A gravity type erector is used in a vertical gyro device to correct errors on
a directional gyro unit
a turn indicator
a gyromagnetic indicator
an artificial horizon
21.
The two main sources of information used to calculate turbojet thrust are the
fan rotation speed (or N1) or the total pressure at the high pressure compressor outlet.
fan rotation speed (or N1) or the total pressure at the low pressure turbine outlet
high pressure turbine rotation speed or the EPR (Engine Pressure Ratio).
fan rotation speed (or N1) or the EPR (Engine Pressure Ratio).
22.
A transport airplane is compelled to carry on board a Ground Proximity Warning System (GPWS). This system will warn the crew in case of :1 - keeping the altitude at a lower level than the one shown in the flight plan entered in the FMS.2 - dangerous ground proximity.3 - loss of altitude during take-off or missed approach.4 - wrong landing configuration.5 - descent below glidepath, within limits.The combination regrouping all the correct statements is
1,3,4
2
2,5
2,3,4,5
23.
All the last generation aircraft use flight control systems. The Flight Management System (FMS) is the most advanced system , it can be defined as a
management system optimized in the horizontal plane
management system optimized in the vertical plane
global 3-D Flight Management System
global 2-D Flight Management System
24.
The airspeed indicator of an aircraft is provided with a moving red and white hatched pointer. This pointer indicates the
maximum speed in VMO operation, versus temperature
speed indicated on the autothrottle control box, versus temperature
speed indicated on the autothrottle control box versus altitude
maximum speed in VMO operation versus altitude
25.
The Decision Height (DH) warning light comes on when an aircraft
passes over the outer marker
descends below a pre-set barometric altitude
descends below a pre-set radio altitude
passes over the ILS inner marker
26.
The oncoming stall of a large transport airplane appears in the form of
a natural buffeting which occurs prior to the simulated buffeting
an orange light on the warning display
control stick vibrations simulating natural buffeting.
a bell type warning
27.
Machmeter readings are subject to
position pressure error
setting error
temperature error.
density error.
28.
During an acceleration phase at constant attitude, the resetting principle of the artificial horizon results in the horizon bar indicating a
constant attitude
nose-down followed by a nose-up attitude
nose-up attitude
nose-down attitude
29.
The altimeter consists of one or several aneroid capsules located in a sealed casing.The pressures in the aneroid capsule (i) and casing (ii) are respectively
(i) vacuum (or a very low pressure) (ii) static pressure
(i) static pressure at time t (ii) static pressure at time t - t
(i) static pressure (ii) total pressure
(i) total pressure (ii) static pressure
30.
The limits of the green scale of an airspeed indicator are
VS1 for the lower limit and VLO for the upper limit
VS1 for the lower limit and VNE for the upper limit
VS1 for the lower limit and VNO for the upper limit
VS0 for the lower limit and VNO for the upper limit
31.
With a pitot probe blocked due to ice build up, the aircraft airspeed indicator will indicate in descent a
fluctuating speed
constant speed
increasing speed
decreasing speed
32.
The TCAS 2 (Traffic Collision Avoidance System) provides :1- traffic information (TA: Traffic Advisory)2- horizontal resolution (RA: Resolution Advisory)3- vertical resolution (RA: Resolution Advisory)4- ground proximity warningThe combination regrouping all the correct statements is
1, 2, 3, 4
1, 3
1, 2, 3
1, 2
33.
Among the following functions of an autopilot, those related to the airplane guidance are:1- pitch attitude holding2- horizontal wing holding3- indicated airspeed or Mach number holding4- altitude holding5- VOR axis holding6- yaw dampingThe combination regrouping all the correct statements is
1, 2, and 6.
3, 4 and 5.
1, 2, 3 and 6.
1, 3, 4 and 5.
34.
The static pressure error of the static vent on which the altimeter is connected varies substantially with the
Mach number of the aircraft
deformation of the aneroid capsule
aircraft altitude
static temperature
35.
The fields affecting a magnetic compass originate from:1. magnetic masses2. ferrous metal masses3. non ferrous metal masses4. electrical currentsThe combination of correct statements is
1, 2, 3
1, 2, 3, 4
1, 3, 4
1, 2, 4
36.
The purpose of compass swinging is to determine the deviation of a magnetic compass
on a given heading
at any latitude
at a given latitude
on any heading
37.
The purpose of Auto Trim function in autopilot is to
help Auto Pilot compensate for crosswind influence
control elevator trim tab in order to relieve elevator load
trim throttles to obtain smooth engine power variation
tell the pilot when elevator trimming is required
38.
In a Turn-indicator, the measurement of rate-of-turn consists for
low bank angles , in measuring the roll rate
low bank angles, in measuring the yaw rate
high bank angles, in measuring the roll rate
high bank angles,in measuring the yaw rate
39.
At a constant Mach number, the calibrated air speed (CAS)
remains unchanged when the outside temperature decreases
decreases when the altitude increases
remains unchanged when the outside temperature increases
increases when the altitude increases
40.
Concerning the TCAS (Traffic Collision Avoidance System)
No protection is available against aircraft not equipped with a serviceable SSR transponder
In one of the system modes, the warning : ""TOO LOW TERRAIN"" is generated
Resolution Advisory (RA) must not be followed without obtaining clearance from ATC
In one of the system modes, the warning : ""PULL UP"" is generated
41.
The calculator combined with the stick shaker system of a modern transport airplane receives information about the: 1- angle of attack2- engine R.P.M.3- configuration4- pitch and bank attitude5- sideslipThe combination regrouping all the correct statements is
1 and 5.
1, 2, 3, 4 and 5.
1, 2, 3 and 4.
1 and 3.
42.
The flight data recorder must automatically stop data recording when the
airplane cannot any longer move by its own power
airplane clears the runway.
main gear shock strut compresses when touching the runway
landing gear is extended and locked
43.
A failed RMI rose is locked on 090° and the ADF pointer indicates 225°. The relative bearing to the station is
135°.
225°.
Impossible to read, due to failure RMI.
315°.
44.
Magnetic compass swinging is carried out to reduce as much as possible
deviation.
variation.
regulation.
acceleration.
45.
The compass heading can be derived from the magnetic heading by reference to a
map showing the isoclinic lines
map showing the isogonic lines
compass swinging curve
deviation correction curve
46.
In the Southern hemisphere, during deceleration following a landing in an Easterly direction, the magnetic compass will indicate
no apparent turn
an apparent turn to the South.
a heading fluctuating about 090°.
an apparent turn to the North
47.
The GPWS (Ground Proximity Warning System) is active for a height range from
50 ft to 5 000 ft measured by the radio altimeter
50 ft to 2 500 ft measured by the radio altimeter
0 ft to 5 000 ft measured by the radio altimeter
0 ft to 2 500 ft measured by the radio altimeter
48.
According to the JAR-OPS regulations, the Cockpit Voice Recorder of a 50 seat multi-engined aircraft having been granted the airworthiness certificate after 1st April 1998 will record:1- the radiotelephonic communications transmitted or received by the cockpit crew2- the audio environment of the cockpit3- the cabin attendants communications in the cabin via the interphone4- the flight crew members communications in the cockpit via the interphone5- the flight crew members communications in the cockpit via the public address system6- the audio signals identifiying the navigation or approach aidsThe combination regrouping the correct statements is
1,2,3,4,5,6
1,2,4,5,6
1
1,3,4,5
49.
In a transport airplane, an autopilot comprises, in addition to the mode display devices, the following fundamental elements :1- Airflow valve2- Sensors3- Comparators4- Computers5- Amplifiers6- Servo-actuatorsThe combination regrouping all the correct statements is
1, 2, 6
1, 3, 4, 6
2, 3, 4, 5, 6
2, 3, 4, 5
50.
At sea level, on a typical servo altimeter, the tolerance in feet from indicated must not exceed
+/-30 feet
+/-70 feet
+/-60 feet
+/-75 feet
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