Email
info@vayudootaviation.com
Phone No
+91 7276526726
become a pilot
Home
About us
courses
CPL
ATPL
RTR(A)
Airline Cadet Program
IGRUA Entrance Prep
B.Sc. Aviation
Pilot Training
INDIA
USA
CANADA
SOUTH AFRICA
NEW ZEALAND
EUROPE
Aircraft Type-Rating
Airbus A320
Boeing 737
Blogs
contact
CPL Test Series
Question Bank
Questions for INDIGO INSTRUMENTS (1117-1427)
Answer the following questions
Test Mode
Training Mode
1.
In order to align a strapdown inertial unit, it is required to insert the local geographical coordinates. This is necessary to
Position the computing trihedron with reference to earth
Re-erect laser gyros.
Check operation of laser gyros
Determine magnetic or true heading
2.
At sea level, on a typical servo altimeter, the tolerance in feet from indicated must not exceed
+/-30 feet
+/-60 feet
+/-75 feet
+/-70 feet
3.
On the ground, during a right turn, the turn indicator indicates
needle in the middle, ball to left
needle to the right, ball to left
needle to the right, ball to right
needle in the middle, ball to right
4.
Among the errors of a magnetic compass, are errors
due to cross-wind gusts particularly on westerly or easterly headings
in North seeking, due to bank angle and magnetic heading
due to Schüler type oscillations
of parallax, due to oscillations of the compass rose
5.
The command bars of a flight director are generally represented on an
HSI (Horizontal Situation Indicator)
ADI (Attitude Director Indicator)
RMI (Radio Magnetic Indicator)
ILS (Instrument Landing System)
6.
The Altitude Select System
Engages autopilot Auto Trim at selected altitude
Illuminates a light when selected altitude is attained
Is annunciated by light and/or sound when airplane is approaching selected altitude
Disengages autopilot Auto Trim at selected altitude
7.
The Head Up Display (HUD) is a device allowing the pilot, while still looking outside, to have
a flying and flight path control aid.
a monitoring of engine data
a monitoring only during Cat III precision approaches.
a synthetic view of the instrument procedure
8.
On an autopilot coupled approach, GO AROUND mode is engaged
by the pilot selecting G.A. mode on the thrust computer control panel
by the pilot pushing a button located on the throttles
if the aircraft reaches the decision height selected on the radio altimeter at a higher speed than the one selected.
automatically in case of an autopilot or flight director alarm
9.
VLO is the maximum
speed with flaps extended in a given position
speed at which the landing gear can be operated with full safety
cruising speed not to be exceeded except in still air with caution.
flight speed with landing gear down.
10.
The gimbal error of the directional gyro is due to the effect of
an apparent weight and an apparent vertical
too slow precession on the horizontal gimbal ring
the aircraft's track over the earth
a bank or pitch attitude of the aircraf
11.
A gravity erector system is used to correct the errors on
a turn indicator
a directional gyro.
a gyromagnetic compass.
an artificial horizon
12.
Among the following functions of an autopilot, those related to the airplane stabilization are:1- pitch attitude holding2- horizontal wing holding3- displayed heading or inertial track holding4- indicated airspeed or Mach number holding5- yaw damping6- VOR axis holdingThe combination regrouping all the correct statements is
1, 2, 3 and 6.
1, 2 and 5.
3, 4, 5 and 6.
2, 4, and 5.
13.
All the anemometers are calibrated according to
St-Venant's formula which considers the air as an uncompressible fluid.
St-Venant' formula which takes into account the air compressibility.
Bernouilli's limited formula which considers the air as an uncompressible fluid.
Bernouilli's limited formula which takes into account the air compressibility
14.
The purpose of the altitude alert system is to generate a visual and aural warning to the pilot when the
proximity to the ground becomes dangerous.
airplane altitude differs from a selected altitude
altimeter setting differs from the standard setting above the transition altitude.
airplane altitude is equal to the decision altitude
15.
VLE is the maximum
flight speed with landing gear down
speed with flaps extended in a given position
speed at which the landing gear can be operated with full safety
speed authorized in flight
16.
The angle of attack transmitters placed laterally on the forward part of the fuselage supply an electrical signal indicating:1- the angular position of a wind vane2- a differential pressure in a probe, depending on the variation of the angle of attack3- a differential pressure in a probe, depending on the variation of the speedThe combination regrouping all the correct statements is
1, 2, 3.
2, 3.
1, 2.
1, 3.
17.
The pendulum type detector system of the directional gyro feeds
a torque motor on the sensitive axis
a nozzle integral with the outer gimbal ring
2 torque motors arranged horizontally
a levelling erection torque motor
18.
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, 3 and 6.
1, 2, and 6.
1, 3, 4 and 5.
3, 4 and 5.
19.
In a non-pressurized aircraft, if one or several static pressure ports are damaged, there is an ultimate emergency means for restoring a practically correct static pressure intake
breaking the rate-of-climb indicator glass window
slightly opening a window to restore the ambient pressure in the cabin
calculating the ambient static pressure, allowing for the altitude and QNH and adjusting the instruments
descending as much as possible in order to fly at a pressure as close to 1013.25 hPa as possible
20.
An automatic pilot is a system which can ensure the functions of
piloting and guidance of an aircraft in both the horizontal and vertical planes.
piloting from take-off to landing without any action from the human pilot.
navigation.
piloting only.
21.
In accordance with (ICAO) Annex 6 part I, the flight data recorder is to be located in the aircraft
as far to the rear as practicable
as near to the landing gear as practicable
as far forward as practicable
at the right or left wing tip
22.
Flight Director Information supplied by an FD computer is presented in the form of command bars on the following instrument
HSI Horizontal Situation Indicator
RMI Radio Magnetic Indicator
BDHI Bearing Distance Heading Indicator
ADI Attitude Display Indicator
23.
When descending through an isothermal layer at a constant Calibrated Airspeed (CAS), the True Airspeed (TAS) will
increase at a linear rate
increase at an exponential rate
remain constant
decrease
24.
The error in altimeter readings caused by the variation of the static pressure near the source is known as
position pressure error
hysteresis effect
barometric error
instrument error
25.
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, 2, 3 and 4.
1 and 3.
1 and 5.
1, 2, 3, 4 and 5.
26.
An aeroplane is in steady descent. The autothrottle maintains a constant calibrated airspeed. If the total temperature remains constant, the Mach number
decreases.
increases.
remains constant
increases if the static temperature is lower than the standard temperature, decreases if higher
27.
During the approach, a crew reads on the radio altimeter the value of 650 ft. This is an indication of the true
height of the lowest wheels with regard to the ground at any time.
altitude of the aircraft
height of the aircraft with regard to the ground at any time.
height of the aircraft with regard to the runway
28.
In low altitude radio altimeters, the reading is zero when main landing gear wheels are on the ground. For this, it is necessary to
compensate residual altitude due to antennas height above the ground and coaxial cables length
place the antennas on the bottom of the aeroplane
change the display scale in short final, in order to have a precise readout
account for signal processing time in the unit and apply a correction factor to the reading
29.
Compared with a conventional gyro, a laser gyro
has a longer life cycle
has a fairly long starting cycle
is influenced by temperature
consumes a lot of power
30.
When flying from a sector of warm air into one of colder air, the altimeter will
overread.
underread.
show the actual height above ground
be just as correct as before
31.
The Ground Proximity Warning System (GPWS) is a system working according to a height span ranging from
the ground to 500 ft
the ground to 1 000 ft
50 ft to 2 500 ft
30 ft to 5 000 ft
32.
In automatic landing mode, in case of failure of one of the two autopilots, the system is considered
""fail survival"" or without failure effect with function always ensured
""fail soft"" with minimized failure effect.
""fail passive"" or without failure effect but with disconnection
""fail hard"" or without failure effect and disconnection
33.
When climbing at a constant Mach number below the tropopause, in ISA conditions, the Calibrated Airspeed (CAS) will
remain constant
increase at a linear rate
increase at an exponential rate
decrease
34.
An ""intruding traffic advisory"" is represented on the display system of the TCAS 2 (Traffic Collision Avoidance System) by displaying
a blue or white empty lozenge
a yellow full circle
a red full square
a blue or white full lozenge.
35.
A stall warning system is based on a measure of
aerodynamic incidence
airspeed.
attitude.
groundspeed.
36.
An aeroplane is in steady cruise at flight level 270. The autothrottle maintains a constant calibrated airspeed. If the total temperature increases, the Mach number
decreases.
increases.
remains constant
decreases if the outside temperature is higher than the standard temperature, increases if lower
37.
During deceleration following a landing in Northerly direction, the magnetic compass will indicate
a heading fluctuating about 360°.
an apparent turn to the East.
an apparent turn to the West
no apparent turn
38.
Except for airplanes under 5,7 t airworthiness certificate of which is subsequent to 31 march 1998, a flight data recording system must be able to store the recorded data for a minimum of the last
30 minutes.
25 hours
60 minutes
10 hours
39.
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
- 150 ft/min
- 500 ft/min.
- 250 ft/min
40.
In low altitude radio altimeters, the height measurement (above the ground) is based upon
a triangular amplitude modulation wave, for which modulation phase shift between transmitted and received waves after ground reflection is measured
a frequency modulation wave, for which the frequency variation between the transmitted wave and the received wave after ground reflection is measured
a wave transmission, for which the frequency shift by DOPPLER effect after ground reflection is measured
a pulse transmission, for which time between transmission and reception is measured on a circular scanning screen
41.
Which one of the following statements is true with regard to the operation of a Mach trim system
It only operates above a pre-determined Mach number
It operates over the full aircraft speed range
It operates to counteract the larger than normal forward movements of the wing centre of pressure at high subsonic airspeeds
It only operates when the autopilot is engaged.
42.
A rate integrating gyro is a detecting element used in1. An inertial attitude unit2. An automatic pilot3. A stabilizing servo system4. An inertial navigation system5. A rate-of-turn indicatorThe combination of correct statements is
2,3,5.
1,2,3,4,5.
1,4.
2,3,4.
43.
The TCAS 1 (Traffic Collision Avoidance System) provides :1- traffic information2- 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, 2
1
1, 2, 3
44.
In an auto-pilot slaved powered control circuit, the system which ensures synchronisation
can itself, when it fails, prevent the automatic pilot from being engaged
is inhibited when the automatic pilot is engaged.
prevents uncommanded surface deflection when the automatic pilot is disengaged
intervenes only when the automatic pilot has been engaged
45.
An aeroplane is in a steady climb. The autothrottle maintains a constant Mach number. If the total temperature remains constant, the calibrated airspeed
decreases
decreases if the static temperature is lower than the standard temperature, increases if higher.
increases.
remains constant
46.
Modern low altitude radioaltimeters emit waves in the following frequency band
SHF (Super High Frequency).
UHF (Ultra High Frequency).
VLF (Very Low Frequency).
HF (High Frequency).
47.
In the Southern hemisphere, during deceleration following a landing in a Westerly direction, the magnetic compass will indicate
an apparent turn to the North.
an apparent turn to the South
no apparent turn
a heading fluctuating about 270°.
48.
In a standard atmosphere and at the sea level, the calibrated airspeed (CAS) is
lower than the true airspeed (TAS).
equal to the true airspeed (TAS).
higher than the true airspeed (TAS).
independent of the true airspeed (TAS).
49.
When only one autopilot is used for climbing, cruising and approach, the system is considered
""fail soft"" or with minimized failure effect.
""fail survival"" or without failure effect with function always ensured.
""fail passive"" or without failure effect but with disconnection.
""fail safe"" with failure effect without disconnection
50.
Today's airspeed indicators (calibrated to the Saint-Venant formula), indicate, in the absence of static (and instrumental) error
The conventional airspeed (CAS) in all cases
The true airspeed
The equivalent airspeed, in all cases
The airspeed, whatever the altitude
Submit
Make New Set
