WorksheetsOBMS,LIGHT,INSTRUMENTS
Total questions: 38
Worksheet time: 19mins
Which system sends maintenance data to ground?
ACARS
ARINC
OBRM
During the CMC self-test process, if a fault is detected the result is
Displayed on MCDU
Displayed on ECAM
transferred to Air Traffic Information Management System (ATIMS)
The CMS allows the operator to obtain troubleshooting data from the systems and to initiate self-tests via MCDU. This mode is available
In flight only.
on ground only.
during normal system operation.
The CMC records all the fault history in the
volatile memory.
non volatile memory.
Random access memory.
When performing interruptive BITE test, the aircraft must be
In flight mode with airspeed above 80knots.
On ground with airspeed below 80knots.
On ground with airspeed above 80knots.
If a flight crew reported that the aircraft had to be flown with a constant rudder trim and carried out an interruptive BITE check that reveals nothing. What should be the next step?
Check the fault history.
Troubleshoot the rudder trim.
Perform a continuity check on the system.
On-board Maintenance System (OMS) has been developed to assist the Maintenance personnel in
rectifying faults of complex avionics systems.
fault finding complex avionics systems.
identification of complex avionics systems.
How can the Central Maintenance Computer functions be accessed?
Through the Control Display Unit.
Through the Built In Test Equipment system.
Through the Flight Management System.
When the aircraft speed is below 80 kts for more than 30 seconds, the Central Maintenance System (CMS) menu switches to
flight mode.
ground mode.
landing mode.
Failure that is still apparent even after reset is called
Soft failure
Hard failure
Latched failure
Interruptive BITE is carried out
During start up.
Continuously during normal system operation.
By the maintenance personnel on ground.
The tail navigation light should have an angle of divergence of
180 degrees
120 degrees
140 degrees
Port and starboard steady navigation light must be visible through
70 degrees
110 degrees
180 degrees
Fluorescent tubes for the cabin lighting are powered by
AC
DC
Either AC or DC
28V DC is supplied to the emergency lighting system for
Emergency operation
Battery charging
Emergency exit lights only
If the emergency lighting system has to be switched on immediately for safety reasons, this is done by setting the
Switch emergency light to ON.
Switch emergency light to ARM.
switch emergency light to EMG.
Fluorescent escape path lights are installed in the
cabin floor of the aircraft.
above door of the aircraft.
every seat of the aircraft.
Left and right wing strobe lights are coloured in
green.
red.
white.
All internal and external lighting system can be controlled from the
Control Display Unit (CDU).
cockpit overhead switch panel.
cabin main control panel.
An EXIT sign light is installed at each emergency exit to enable the passengers to locate the exits easily in bad light or smoke conditions. It is supplied with
6.1V DC.
115 V AC.
28 V DC.
Before shutting down the engine, the emergency light switch must be
set to the NULL position.
set to the ON position.
set to the OFF position.
How long will the emergency lights stay illuminated when the main aircraft power supply fails?
10 minutes.
20 minutes.
30 minutes.
Port and starboard wing navigation lights are coloured
red for port and green for starboard.
green for port and red for starboard.
white for port and red for starboard.
During the normal straight and level flight, the gyro of an electrical artificial horizon is kept erect in pitch by
pendulous vane erection unit and commutator switch.
ball-type erection unit and mercury switch system.
Torque Motor and Levelling Switch System.
How does a change of gyro rotor speed affect the gyro rate of precession?
If the rotor speed increases, the rate of precession increases.
If the rotor speed decreases, the rate of precession decreases.
If the rotor speed increases, the rate of precession decreases.
Random drift of a gyro is caused by
error in roll when aircraft is turning.
aircraft turning with an error in roll.
gyro friction and imbalance.
During compass swing, the compass recorded North error -2 degrees and South error - 2 degrees. What is the coefficient 'C' of the compass?
+2 degrees.
-2 degrees.
0 degrees.
Which barometric instrument uses a restrictor to compute its output?
Machmeter.
Vertical Speed Indicator.
Airspeed Speed Indicator.
What is the maximum altitude range for radio altimeter?
1,500 ft.
2,500 ft.
10,000 ft.
A Pilot wants to set the Command bars in flight director indicator to provide vertical guidance to hold the aircraft at the desired altitude. The pilot will select
GA mode.
IAS mode.
ALT mode.
What is the warning activated by the Ground Proximity Warning System (GPWS) if it indicates that the aircraft is descent after takeoff?
PULL UP light and DON'T SINK audio
PULL UP light and SINK RATE audio
MINIMUMS audio is heard.
Rapid response type thermocouple is used for
Turbofan engine.
Turbojet engine
Turboprop engine
What is the formula of coefficient 'B' in compass swing procedure?
Deviation on South - Deviation on North divide by 2
Deviation on North - Deviation on South divide by 2
Deviation on east - deviation on west divide by 2
A technician push and turn the caging knob on a heading indicator to set the instrument are to
indicate the same heading as the magnetic compass.
indicate the same heading as the Global Position indicator.
indicate the same heading as the Automatic Direction Finder.
The output voltage of a thermocouple is determined by
the temperature at the hot junction using bridge rectifier.
the resistance of the thermocouple lead using shunt resistor.
the temperature difference between the hot and cold junction.
Magnetic variation is the difference in angle between
true north and magnetic north
magnetic heading and aircraft heading
the compass north and magnetic north
The Ground Proximity Warning Computer in mode 4 would use which inputs to issue a warning?
A low range altimeter and rate of change of low range altimeter
A low range altimeter and configuration of aircraft
A low range altimeter and GPS
During an automatic landing, the aircraft descent rate is sensed by
pitch rate gyros
radio altimeters
vertical accelerometers
