WorksheetsAircraft Systems Quiz
Total questions: 31
Worksheet time: 16mins
In a fully fly by wire system if the rudder becomes disconnected
it is centralized by a spring
its control is maintained by electric trim
It Is centralized by the airflow
The purpose of a yaw damper is to
assist the aerodynamic response
produce a co-ordinated turn
block the Dutch roll frequency
During flight ,the aileron active servo jack has failed to function, therefore servo jacks will
revert to damping mode.
stay in the last position.
retract to zero position.
If the elevator loses all its electrical power in a fly by wire system, it will cause the servos to
locked at their last position.
remain stationary and provide damping.
move to neutral position.
In a fully Fly By Wire aircraft, rudder trim is nullified by the
Flight Augmentation Computer.
Power Management Computer.
Flight Management Computer.
Part of the aircraft structure to reduce lift and aircraft speed is the
rudder .
spoiler.
aileron .
Aileron input is fed into the yaw damper system is to prevent
The nose from pitching down.
The nose from pitching up.
An adverse yaw in a turn.
If the 'Q' feel in a powered system fails,
system stops and it remains in that position.
the pilot feels air loads higher than normal.
the pilot feels air loads lower than normal.
What is the purpose of installing a trim tab?
To correct flying faults due to a change in aircraft center of gravity position.
To correct flying faults due to aircraft flying in turbulence and heavy weather.
To correct flying faults due to pilot mistakes in handling the flight control.
During flight, a pilot rotates the control wheels of the elevator trim in a forward direction. This causes the aircraft to
nose up.
nose down.
turn left.
In order to dampen vibration, maintain cable alignment. Meanwhile, in order to seal openings in bulkheads during installation of aircraft cables, __________ is used.
fairleads.
grommet.
clamp.
Stick pushers are installed in an aircraft as a stall-prevention device. They will operate
after the stall angle.
before the stall angle.
at the stall angle.
When an airplane is parked, damage to the flight control systems due to gusts of wind may be prevented by locking
the aileron and flap is in "down" position while elevator is in the "neutral" position.
the aileron and flap is in "up" position while elevator is in the "down" position
the aileron and rudder is in "neutral" position while elevator is in the "down" position.
A technician is carrying out few tests using Maintenance Access Terminal. The technician must ensure that
control surfaces are locked with latches, tagged, and warning notices are displayed.
control surfaces are locked with safety pins, tagged, and warning notices are displayed.
control surfaces are free to move with no obstructions and warning notices are displayed.
Operational testing of a 406 MHz ELT from the cockpit of an aircraft may be undertaken by maintenance facilities, provided that
the test duration is no longer than 10 seconds and is undertaken within the first 5 minutes of the hour.
the test duration is no longer than 5 seconds and is undertaken within the first 5 minutes of the hour.
the test duration is no longer than 3 seconds and is undertaken within the first 5 minutes of the hour.
After making an announcement, a cabin crew noticed that a group of seat still has their videos played. This might be because of
Seat Electronic Box is malfunctioned.
Passenger Control Unit overrides the announcement.
Passenger Services Unit Decoder is disconnected.
A passenger reported that he/she cannot increase or decrease the volume of the video he/she was watching. It may be the fault of the
Passenger Services Unit Decoder.
Passenger Control Unit.
Column Time Decoder.
What is a disadvantage of fibre optics?
It needs high degree of precision when fitting cables and connectors.
It is electrically isolated and free from earth/ground loops.
It can significantly induce noise and cross-talk.
How to reset the attendant call button after it has been activated?
The button is pressed again.
The button is pulled out.
The button is auto reset.
The emergency locator transmitter is located at the
aft in the fuselage.
middleof the fuselage.
below the cockpit.
The emergency Locater transmitter, when activated, will
Transmit a digital signal for every 50 sec on frequency of 406 Mhz
Transmit a digital signal for every 120 sec on frequency of 406 Mhz
Transmit a digital signal for every 50 sec on frequency of 121 Mhz
The specific gravity readings of all lead acid cells taken after charging shows substantially lower value .What is the possible cause?
All cells are defective.
Battery is fully charged.
Cell is in good condition.
When replacing the brushes on a DC generator, the brushes must be bedded first, this can be done
with the generator fitted to the aircraft and bedding done in situ.
with the generator removed and bedding done on bench.
by the manufacturers or approved service centre.
The voltage regulation in the generator control unit is accomplished by
reducing the generator output.
varying the control winding field strength.
varying the generator exciter field strength.
A lead-acid battery found with several cell low on Specific Gravity requires
topping up with distilled water.
topping up with sulphuric acid.
rechargingthe battery.
If voltage and frequency of the generator drop to zero in flight, possible cause could be due to
CSD drives shaft had sheared.
phase sequence detection circuit has operated .
bus tie interlock is inoperative.
What would indicate the state of charge of a lead acid battery?
Fluctuations in the level of the electrolyte
Fluctuations in the SG of the electrolyte
Fluctuations in the terminal voltage
Batteries removed from aircraft must always be stored in
fully charged condition.
fully discharged condition.
half charged condition.
During generator servicing, it is found that there is an indication of localized blackening on the commutator surface. This may indicate
localized circuit either between the commutator segments or in an armature winding.
open circuit either between the commutator segments or in an armature winding.
short circuit either between the commutator segments or in an armature winding.
Ground crew tries to start the APU, but it is not starting. The possible cause for this situation is because of
Aircraft batteries discharge.
TRU line disconnected.
External power is connected.
The type of power supply needed for equipments requiring 200V AC is
single phase AC supply.
two phase AC supply.
three phase AC supply.
