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WorksheetsFire Protection System Quiz
Total questions: 200
Worksheet time: 2hrs 40mins
What is the primary purpose of the fire protection system?
To extinguish fires in the cabin only
To prevent fires from starting in the aircraft
To detect and extinguish fires in critical areas like the engines, APU, and cargo compartments
To alert the crew about potential fire risks
Where is the fire detection sensors located?
Only in the engine compartments
In the cockpit and cabin
In the engines, APU, and cargo compartments
Only in the cargo hold
How many fire extinguishers are available for engine fire protection?
One for each engine
Two for each engine
One for the left engine only
One for the right engine only
What happens when the fire detection system in the engine compartment detects a fire?
A warning light illuminates on the flight deck
The engines automatically shut down
The aircraft's autopilot disengages
The APU starts to provide backup power
What must be done after a fire warning light illuminates for an engine?
The crew must attempt to extinguish the fire immediately
The crew must shut down the engine and discharge the fire extinguisher
The aircraft must land immediately
The autopilot should be engaged
How is the fire suppression system activated in the cargo hold?
Automatically when a fire is detected
Manually by the flight crew using a cockpit switch
By a ground crew member before take off
By cabin crew using a button in the galley
What does the cockpit fire warning system consist of?
Warning lights and an audible alarm
A temperature sensor and a visual gauge
A smoke detector
A siren and a cabin display
What type of fire extinguishing agent is used in the cargo compartment?
Halon 1301
Water
Carbon dioxide (CO2)
Dry chemical agents
What happens when a fire is detected in the APU compartment?
The APU automatically shuts down, and the fire extinguisher is activated
The crew must manually shutdown the APU after receiving a warning
The APU continues to run but at a reduced power setting
There is no impact unless the fire escalates
What is the primary purpose of the fuel system?
To supply fuel to the engine and auxiliary power unit (APU)
To store fuel for long-term use
To cool the engines
To measure fuel consumption during flight
How many main fuel tanks are there?
One
Two
Three
Four
What is the function of the fuel cross feed system?
To transfer fuel between the tanks to balance fuel distribution
To allow fuel transfer from the APU to the engines
To supply backup fuel to the engines during emergencies
To prevent fuel contamination
What is the purpose of the fuel jettison system?
To remove excess fuel in case of emergency landing
To prevent fuel contamination
To balance the fuel load in all tanks
To increase engine performance
What happens if a fuel pump fails?
The engine will automatically shut down
The fuel cross feed system will transfer fuel to the affected tank
The APU will supply fuel to the engine
There will be no impact on the flight
How is fuel transferred between the tanks?
Manually by ground crew
Automatically via the fuel cross feed system
By the APU during flight
By the aircraft's autopilot system
What is the purpose of the fuel transfer valves?
To allow fuel to be sent to the APU
To control the flow of fuel between tanks
To monitor fuel quality
To balance the aircraft weight
What does the fuel quantity indicator show?
The total amount of fuel remaining in the aircraft
The fuel flow rate to each engine
The pressure in the fuel lines
The fuel temperature in the tanks
What is the primary function of the APU?
Provide electrical power during flight
Generate thrust for take off
Supply air conditioning and electrical power when the main engines are off
Assist in engine start-up
What is the maximum operating altitude for the APU?
10,000 feet
15,000 feet
25,000 feet
30,000 feet
What is the primary power source of the APU?
Battery
Engine generators
Jet fuel
Ground power unit (GPU)
What is the maximum operating speed of the APU?
50% RPM
75% RPM
100% RPM
110% RPM
What happens if the APU fails to start?
The aircraft will not be able to take off
The pilot will receive an automatic warning
The aircraft can still operate using ground power
The aircraft will automatically switch to backup power
Which of the following is an APU component that is critical for starting the engines?
Power generation system
Pneumatic system
Hydraulic pump
Ignition system
How is the APU shutdown performed?
The pilot manually shuts it off via the cockpit control panel
Automatically when the engines are started
By pressing a button located in the cabin
The ground crew performs the shutdown
Which of the following is NOT a function of the APU?
Starting the main engines
Providing cabin air conditioning
Supplying hydraulic pressure
Powering electrical systems
The engine used on Boeing 737 is CFM 56-3, the type of the engine is:
Low by-pass, dual rotor, axial flow, turbo fan engine
Low by-pass, dual rotor, centrifugal flow turbo fan engine
High by-pass, dual rotor, centrifugal flow, turbo fan engine
High by-pass, dual rotor, axial flow, turbo fan engine
How the accessory gear box?
It is installed to the fan case, right hand side
It is installed to the fan case, left hand side
It is driven by LP turbine via radial and horizontal driven shaft
It is driven the inlet gear box directly via radial drive shaft
The type of engine bearing are roller bearing and ball bearing:
Ball type for bearing no. 1 and no. 5
Ball Type for bearing no.1 and no. 3, Roller type for bearing no. 2, 4 and 5
Ball type for bearing no. 1 and no. 4, Roller type for bearing no. 2, 3 and 5
Ball type for bearing no. 1 and no. 2, Roller type for bearing no. 3, 4 and 5
In working around a running engine, for safety reason be aware of the following, Except:
Not to wear any lose articles
Hot and high speed exhaust blast is quite dangerous
Ear protector is not so necessary when the engine is only at idle speed
Use the safety corridor in approaching the engine
Concerning fan blade installation, with statement is correct?
Spacer is to limit axial movement of the blade
Fan balancing is done to shorten landing roll
Balancing screw is on spinner rear cone
Retainer is to limit radial movement of the blade
The engine has two fuel pump and HP fuel pump:
The LP pump is gear type
Fuel pump assembly contains LP pump and HP pump
The HP pump is centrifugal type
As mentioned on A, B and C
The fuel shut off valve (Start valve) is located in the MEC:
It is controlled electrically from the cockpit
It is driven mechanically by the start lever
It is a normally open valve
It is driven mechanically by the throttle lever from flight deck
The installation of the fuel flow transmitter is:
Upstream of the MEC
Upstream of the fuel Pump
Downstream of the Fuel pump
Downstream of the MEC
In the operational, how does the MEC monitors the position of the VBV, VSV and HPTCC?
VBV and VSV position is monitored mechanically
VBV positioned is monitored hydraulically
HPTCC position is monitored electrically
A, B and C are correct
The engine idle control system:
On MEC, solenoid energized for low idle
On MEC, solenoid energized for high idle
Low idle light always illuminated on the ground
Low idle light always illuminated in flight
What adjustment do you have on MEC?
Idle speed adjustment, Part power adjustment and SG adjustment
Acceleration and deceleration adjustments
Part power adjustment and SG adjustments
Idle speed adjustment, part power adjustment and pull power adjustment
Where is the location of the CIT sensor?
In the engine inlet, at 12.00 O'clock
In HP compressor outlet
Between LP Compressor and HP Compressor at 06.00 O'clock
Between LP Compressor and HP Compressor at 12.00 O'clock
On the VSV system, some stages of HP compressor stator vanes are made variable:
IGV, stage 1, stage 2, and stage 3 vanes
IGV, stage 1, and stage 2 vanes
Stage 1, stage 2, stage stator vanes
IGV and stage 1 stator vanes
The HPTCC timer is active as follows:
Aircraft on the ground with engine RPM 95% N2
Aircraft in flight
One time operation for maximum 182 seconds per engine cycle
A and C are correct
What indication do you have, when an engine anti icing valve is closed due to the operation of over pressure protection?
Amber light ON, blue light bright
Amber light ON, blue light OFF
Amber light OFF, Blue light ON
Amber Light ON, Blue light OFF
The oil tank is vented to
Forward sump
Aft sump
Accessory gear box
Over board directly
The oil FILTER BYPASS Light illuminate when:
Differential oil pressure filters 25-27 psid
Oil pressure filter is being bypass
Oil pressure filter is clogged
All above are correct
During engine starting when the start switch is selection to GND, so:
Start valve open
5" stage bleeds valve open
Start valve light illuminate
As mentioned on A, B, and C
About the ignition system:
The LH is DC ignition and RH is AC ignition system
Both are AC ignition system
The ignition plugs are always operating together
The LH is AC ignition and The RH is DC ignition system
Where the location of the ignition exciters?
On the engine fan case
On the engine core case
In the E/E compartment
In the flight deck
Concerning starter duty cycle. Which statement is not correct?
2 minutes ON, 20 seconds OFF
15 minutes ON, 15 Minutes OFF
2 minutes ON, 20 second OFF then 2 minutes ON again and let the starter become cool for three minutes
20 minutes ON then 2 minutes OFF for cooling down
The precaution to be obeyed prior to working on ignition system is:
We can work directly on the system after a failure is identified
Pull the system CB and disconnect the low tension connector
Wait for enough time there is no high voltage in the system
B and C are correct
Choose the correct statement for N1 indicating system is:
The sensor is an induction type tachometer generator
The sensor is installed to the accessory gear box
The indicator is on secondary engine display unit
As mentioned on A, B and C
The limitations of the engine are as follow, except:
Maximum EGT during starting is 930 degree
Maximum N1 is 106 %
Maximum N2 is 105 %
Maximum EGT during T/O 930 Degree C
Engine performance will be done for the following reasons, except:
To warm up the engine during pre-flight check
As required to check an aircraft system
After engine installation or component replacement that effect engine performance
To conform inconclusive reported fault or to prove an adjustment
What is the primary function of the air conditioning system?
To provide cabin pressurization during flight
To control the temperature and ventilation in the cabin and cockpit
To supply hydraulic power to actuators
To regulate fuel flow to the engines
The turbo-fan valve of an air conditioning unit opens?
When the aircraft is on the ground only
When the aircraft is on the ground or in flight when flaps are extended
Only when the RAM DOOR FULL OPEN light is illuminated
When the aircraft is in flight only
The RAM DOOR FULL OPEN lights are normally extinguished
During the cruise
After take-off and flaps are up
Just before landing
After landing
The E & E compartment is cooled by?
The equipment cooling system
The ram air system
The AUTO or STANDBY pressurisation systems
Engine bleed air
The air supply for the Re-circulating Fan is?
Exhaust air from the main cabin and electrical equipment bay and forward outflow valve collected in a shroud located above the aft cargo compartment
Exhaust air from the main cabin and electrical equipment bay collected in a shroud located above the aft cargo compartment
Exhaust air from the electrical equipment bay collected in a shroud located above the forward cargo compartment
Exhaust air from the main cabin and electrical equipment bay collected in a shroud located above the forward cargo compartment
Pack Valve automatically closed and PACK TRIP OFF light illuminates for following conditions, except...
Overheat in the turbine outlet
Overheat in the compartment duct
Overheat in the turbine inlet
Overheat in the compressor discharge
The Re-circulating Fan air shroud is located
Forward of the E & E compartment
Forward cargo compartment aft ceiling
Above the aft cargo compartment
Under the Cockpit floor
The position of the forward outflow valve
Is open when the main outflow valve is closed
Is closed when the re-circulating fan is not operating
Is closed when the re-circulating fan is operating
Is open when the main outflow valve is open
During inspection, it is found that the indicator on the water separator is the 'red range'...
The water separator must be replaced
The bypass valve must be replaced
The coalescer bag must be replaced
The pack system must be replaced
During operation, the mix valve modulate...
It controls the cold air flow
It controls the hot air flow
It controls the ram air
It controls the hot air and cold air flow
The cabin Altitude Warning horn will
Sounds (steady horn) when the cabin altitude reaches 10,000 feet altitude
Sounds (steady horn) when the cabin altitude reaches 14,000 feet altitude
Sound (intermittent horn) when cabin altitude reaches 14,000 feet altitude
Sound (intermittent horn) when cabin altitude reaches 10,000 feet altitude
The Re-circulating Fan system provides?
A filtered air supply into the mix manifold
An unfiltered air supply into the mix manifold
An air supply directly from the mix manifold into the passenger cabin only
An air supply directly from the mix manifold into the control cabin only
The Re-circulation Fan is
Aircraft battery powered
A.C. powered
Pneumatically powered from APU or engine bleed air
D.C. powered
The safety relief valves are normaly closed valve, and will automatically open at...
The differential pressure 8.65 psid
The differential pressure 7.50 psid
The differential pressure 7.80 psid
The differential pressure 8.50 psid
The cabin pressure controller is located in the
Flight compartment
Electronic compartment
Forward cargo
Aft fuselage, near the outflow valve
With aircraft on ground, how is the ram air system
Deflector door retracted, modulation panels open
Deflector door retracted, modulation panels closed
Deflector door extended, modulation panels open
Deflector door extended, modulation panels closed
Where is location of the Ram Air Controller?
In the air conditioning bay
In the cockpit
In the forward cargo
In the electrical compartment
The cabin pressurization system selection is...
Auto mode, Standby mode and manual mode
Auto mode, Alternate mode and manual mode
Auto mode, Alternate mode and Standby mode
Auto mode and Alternate mode
The illumination of an OVERHEAT light on the air conditioning control panel (P5) show...
Supply duct overheat at 250 degrees fahrenheit
Supply duct overheat at 190 degrees fahrenheit
Supply duct overheat at 140 degrees fahrenheit
Supply duct overheat at 110 degrees fahrenheit
The temperatur indicator on the air conditioning control panel (P5)
Cockpit duck or cockpit zone temperature as selected
Cabin zone or cockpit zone temperature as selected
Cabin zone temperature
Cabin duct or cabin zone temperature selected
The right No.2 window heating input is controlled by
The left No.1 window heat control system
The right No.1 window heat control system
The right SIDE window heat control system
The left SIDE window heat control system
If a window overheats light illuminates this indicates that
The associated window has reached an overheat condition and it must be selected OFF manually to remove power before any damage takes place
Cabin differential pressure must be reduced to a maximum of 5 PSI
The power has been automatically removed from the associated window system and will be re-introduced automatically when the window has cooled
The power has been automatically removed from the associated window system
With all window heaters selected ON and OVHT selected on the window heat test switch
All OVERHEAT lights illuminate and the ON lights may extinguish immediately, or remain illuminated for as long as 70 seconds
All OVERHEAT lights illuminate and the ON lights will extinguish immediately
All OVERHEAT lights and ON lights will extinguish immediately
The ON lights will not be affected but observe a rise in on the AC ammeters
The right No.2 window heat is supplied from
Standby AC BUS
Battery Bus
Generator BUS No. 1
Generator BUS No. 2
After the overheat lights have illuminated during OVHT test
The window heat switches must be momentarily positioned to RESET to reset the system
The window heat switches must be momentarily positioned to OFF to reset the system
No action is required as the resetting of the system is automatic
Push overheat light to reset
The wing anti-ice valves will
Close when the temperature in the anti-ice ducting reaches a preset limit on the ground only
Close when the temperature in the anti-ice ducting reaches a preset limit on the ground or in flight
Close when the pressure in the anti-ice ducting reaches a preset limit on the ground or in flight
Close when the pressure in the anti-ice ducting reaches a preset limit on the ground only
The wing anti-ice control valves
Are pneumatically operated
Are DC motor operated
Pneumatically control and DC motor operated
Are AC motor operated
The source of air for wing anti-ice is
Pneumatic manifold from 5th stage engine bleed air only
Pneumatic manifold from 5th and 9th stage engine bleed air
Pnematic manifold from 9th stage engine bleed air only
Fan air
The thermal protection of the wing anti-ice ducting is
An inflight function only
An inflight and flap not fully retract
An on-ground function only
Operative at all times
With all windshield heating switches ON and the aircraft on the ground
If a green ON light extinguishes and an OVERHEAT light comes ON, the Master Caution light will not come ON
all lights remain extinguished until the aircraft is airborne because of touchdown relays
if a green ON light extinguishes and an OVERHEAT light comes ON, the Master Caution light will also come ON
failure of engine bleed switch
Both windshield wipers are controlled by
Their own respective rotary switches
One rotary switch
Their own respective lock-toggle switches
Window heat switch
Window NO.3 in the control cabin is
Is fully anti-fogged from the air conditioning system
Electrically heated
Not electrically heated
B and C are correct
The Window Heat ON light (green) illuminates to indicate
The window heat controller is applying heat to the associated window
The associated window heat switch has been selected to OVHT TEST
The associated window heat switch is positioned to ON
The associated window heat switch is positioned to OFF
What is the function of the four windows heat control units in electronic compartment
To control heating for windows no.1, no.2
To control heating for windows no.4, no.5
To control heating for windows no.1, no.2, no.4 and no.5
To control heating for windows no.1, no.2, no.3 and no.4
When the wiper control on P5 panel is selected to PARK, wiper blade moves to such as position
Blade moves outboard in high speed, then stop
Blade moves outboard in low speed, then stop
Blade moves inboard in high speed, then stop
Blade moves inboard in low speed, then stop
The amount of fan air that is ducted through the pre-cooler is controlled by the
Ram air controller
Pneumatic activated pre-cooler valve
Modulating and shut-off valve
Engine Bleed Valve
APU bleed air used to start NO.1 engine is
Routed direct to the No.1 engine starter valve
Controlled by the modulating and shut-off valve
Routed via the No. 1 engine bleed air valve to the No.1 engine starter valve
Routed via Isolation Valve
With the Isolation Valve switch in AUTO, both engine bleed switches ON and both Air Conditioning Pack switches selected to AUTO or HIGH
The isolation valve will be closed
The isolation valve will be closed when the flaps are extended
The isolation valve stay at last position
The isolation valve will be open
The DUAL BLEED light will be on
With No. 2 engine bleed valve open, the isolation valve closed and APU bleed valve open
With the air-conditioning panel set for a bleeds-off take off
With No. 2 engine bleed valve open, the isolation valve open and APU bleed valve open
With No. 1 and No. 2 bleed valves closed and APU bleed valve open
An engine BLEED TRIP OFF light will illuminate
Only if engine bleed air pressure exceeds a predetermined limit
Engine Bleed Air Switch OFF
Only if engine bleed air temperature exceeds a predetermined limit
When engine bleed air temperature or pressure exceeds a predetermined limit
The pneumatic duct pressure gauge
Indicates pressure in left and right pneumatic ducts
Is DC powered
Indicates pressure available for engine anti-icing
Indicates pressure in left pneumatic ducts
With a ground pneumatic source connected and the isolation valve switch selected to CLOSE
The pneumatic pressure would be indicated by the right hand pointer on the pneumatic duct pressure indicator
The pneumatic pressure would be indicated by the left hand pointer on the pneumatic duct pressure indicator
The pneumatic pressure would be indicated by both the left and right pointers on the pneumatic duct pressure indicator
The pneumatic pressure would be indicated by left or right pointers on the pneumatic duct pressure indicator depend on Air conditioning pack switch
The 9th stage modulating and shut-off valve
Will open if the 5th stage air is insufficient in maintaining proper pressure
Will open if the APU is insufficient in maintaining proper pressure
Is open at all times irrespective of 5th stage air pressure output
Will open if the 5th stage air is sufficient in maintaining proper pressure
The engine bleed valves are
Pneumatically activated and operated
DC activated and operated
DC activated and pneumatically operated
AC activated and pneumatically operated
The sources of engine bleed are
5th and 9th stages of the fan section
5th and 13th stages of the fan section
5th and 9th stages of the turbine section
5th and 9th stages of the compressor section
Water tank pressurisation in flight is normally provided by
5th and 9th stage air from the No. 1 engine
5th and 9th stage air from the No. 2 engine
Bleed air from the APU
5th and 9th stage air from the both engines
Both hydraulic reservoirs are pressurised by
5th and 9th stage air from engine No. 2 only
5th and 9th stage air from engine No. 1 only
Separate engine bleeds directly to the reservoirs
Air from the pneumatic manifold
The source air ducted through the pre-cooler is
5th stage bleed air
Pressure controlled ram air
Fan air
9th stage bleed air
The isolation valve is
DC controlled and pneumatically operated
DC operated
AC operated
AC controlled and pneumatically operated
During operation, what condition makes the high stage valve closed
The downstream pressure to high
The engine is on idle speed
The 9th stage air > 110 psi
The 5th stage air > 110 psi
The airplane has three main jack point
Wing jack point
Aft body jack point
Forward jack point
A and B are correct
The airplane has auxiliary jack point
Wing jack point
Aft body jack point
Forward jack point
All are correct
The airplane is normally towing movement max
70⁰
78⁰
80⁰
68⁰
The boing 737 classic type design fuselage is
Monocoque fuselage
Semi monocoque fuselage
Full monocoque fuselage
Buckets fuselage
How many entry door to the passenger cabin
Base entry door
Two entry door
Three entry door
Four entry door
The airstair can be retracted or extended with airplane use
Hydraulic power
Battery power
AC power
B and C are correct
How many time to extend or retract the air stair
20 second
30 second
35 second
40 second
Power to operate the air stairs door is
AC power
DC power
Hydraulic power
All above correct
How many of the gally service door
One galley service door
Two galley service door
Three galley service door
Four galley service door
Emergency exit hatch operation can re open
Inside removal
Outside removal
Only inside removal
A and B correct
The fixed window location no is
1, 2, 3, 4
1, 3, 4, 5
1, 2, 4, 5
1, 2, 3, 5
The window location use power for heating for anti icing and defogging is
No 1 and no 2
No 1 and no 3
No 3 and no 4
No 4 and no 5
The window no use power for heating is
Window no 1
Window no 3
Window no 4
Window no 5
The seat can the adjustment control for sliding and to height is
Pilot seat
Observer seat
Cabin crew seat/ attendant seat
Passenger seat
The air grilles functional for
The recirculation fan
The pressure differential
That prevents debris
All above answer true
The crew oxygen system used
A high pressure gaseous oxygen
A chemically -- generated oxygen
A and B correctly
Portable oxygen
Where location the crew oxygen bottle system component
In the passenger compartment
In the attendant compartment
In the forward cargo compartment
A, B and C no correct
How many pressure crew oxygen flow regulator reduces in the distribution system
1850 psi to 75 psi
1850 psi to 80 psi
1850 psi to 100 psi
1850 psi to 50 psi
If used the oxygen generator for passenger on the generator turns change color to
Green
Red
Black
Yellow
Oxygen is generated inside the generator by the chemical use
Natrium chlorate and iron
Sodium chlorate and iron
Sodium chlorate and alumunium
Sodium chlorate and copper
The major light system is
Flight compartment light
Passenger compartment light
Cargo and service compartment light
A, B, and C correct
The passenger compartment light is exception
Reading light
Dome light
Window light
Taxi light
The exterior compartment light is
Logo light
Turn off light
Position light
A, B and C correct
Power supplied passenger reading light is
115 VAC
28 VAC
28 VDC
24 VDC
The exterior position red light navigation is
Left side position
Right side position
Tail side position
A, B and C correct
THE EXTERIOR POSITION GREEN LIGHT NAVIGATION IS
LEFT SIDE CONTROL
RIGHT SIDE CONTROL
TAIL SIDE POSITION
A,B,C ARE CORRECT
THE STROBE LIGHT FLASH RATE IS
65± 3 PER MINUTES
60± 3 PER MINUTES
65± 5 PER MINUTES
60± 5 PER MINUTES
EMERGENCY EXIT LIGHT THE BATTERY PACK CONTAIN
FOUR NICAD BATTERIES
FIVE NICAD BATTERIES
SIX NICAD BATTERIES
SEVEN NICAD BATTERIES
THE POWER FOR BATT CHARGER IS
NORMAL GROUND SERVICE BUS, ALTERNATE MAIN BUS
ALTERNATE MAIN BUS 2, ALTERNATE GROUND SERVICE BUS
NORMAL GROUND SERVICE BUS, ALTERNATE TRANSFER BUS
NORMAL GROUND SERVICE BUS, ALTERNATE MAIN BUS 2
GENERATOR CONTROL UNIT 3 ARE LOCATED IS
E /E COMPARTMENT
P6 PANEL
P18 PANEL
LOWER NOSE COMPARTMENT R/H SIDE
IN FLIGHT APU POWER
CAN SUPPLY ONLY ONE GEN BUS
CAN SUPPLY BOTH GEN BUS
CAN SUPPLY ONLY GEN BUS 1
CAN SUPPLY ONLY
GEN BUS 2
WHEN BATTERY TEMPERATURE EXCEED 58⁰C
THE BATTERY OVER TEMPERATURE LIGHT IS ON
THE HOT BUS UN POWERED
THE BATTERY STOP CHARGING AUTOMATICALLY
THE BATTERY VOLTAGE DROP TO ZERO
GCR (GENERATOR CONTROL RELAY) WILL TRIP IF
OVER FREQUENCY OCCUR
UNDER VOLATGE OCCURE
GEN SWITCH ON
UNDER FREQUENCY OCCUR
1. THE GENERATOR CONTROL RELAYS (GCR) ARE LOCATED IN THE
A. NOSE WHEEL WELL
A. E-3RACK IN THE E/E COMPARTMENT
A. GENERATOR CONTROL UNIT (GCU’S)
A. P5-4
THE MAXIMUM AMPERAGE FOR ANY GENERATOR LOADIN FLIGHT IS
125 AMPERE
65 AMPERE
50 AMPERE
28 AMPERE
FIRST PRIORITY THE GEN BUS IS
ENGINE GENERATOR
APU GENERATOR
EXTERNAL POWER
NO PRIORITY
WHEN THE GROUND SERVICE PANEL LIGHT ILLUMINATE IF
GROUND SERVICE PANEL ON POSITION
EXTERNAL POWER PLUG IN POSITION
GROUND SERVICE POWER OFF POSITION
EXTERNAL POWER FLIGHT IN SWITCH OFF POSITION
IF GROUND SERVICE PLUG IN EXTERNAL POWER AVAIL, WHATCOLOUR OFLIGHT WILL ILLUMINAE AT THE GROUND
AMBERE
GREEN
PINK
BLUE
AC POWER FREQUENCY ACD VOLTAGE IS
A. 240 HZ/115 VAC
400 HZ/115 VAC
60 HZ/115 VAC
90 HZ/115 VAC
THE DC VOLTAGE OF THE BATTERY AND TRANSFORMER INTERIOR OUTPUT IS
12 V
115 V
28VDC
16 V
TO CHECK THE BATTERY CHARGE ON DISCHARGE THE SELECTION MUST BE
BATT MUST POSITION
BATT POSITION
STANDBY POWER POSITION
TEST POSITION
WHEN YOU DISCONNECT THE CSD FOR GENETATOR, WHAT THREE LIGHT OF ELECTRICAL SYSTEM ILLUMINATE (APU NOT RUNNING)
CSD LOW OIL PRESSURE GEN OFF BUS ,BUS OFF
CSD LOW OIL PRESSURE, APU GEN OFF BUS, STBY POWER
TRANSFER BUS OFF, BUS OFF, GEN BUS OFF
STBY POWER, HIGH OIL TEMP, GEN OFF BUS
ENGINE CSD DISCONNECT HANDLE IS PULLED, WHICH LIGHT ILLUMINATE ON N 328
FEEDER FAULT (FF) LIGHT
LOW VOLTAGE (LV) LIGHT
MANUAL TRIP (MT) LIGHT
HIGH VOLTAGE (HV) LIGHT
MAX CSD OIL TEMPERATURE
1570⁰C
157⁰C
145⁰C
145⁰F
IF THE CSD OIL TEMPERATUR INCREASE TO 157⁰C
THE CSD DISCONNECT WILL ENGAGE AND REMOVE THE INPUT DRIVE TO CSD
THE GENERATOR CONTROL RELAY (GCR) WILL TRIP
THE GENERATOR BREAKER (GB) WILL TRIP
THE CSD OIL HIGH OIL TEMPT LIGHT WILL ILUMINATE
SWITCH IN ALL TO POSITION, NO SMOKING LIGHT WILL ILLUMINATE IF
L/G LEVER HANDLE DOWN
T/E FLAP DOWN
L/G LEVER HAND
. ONLY NO SMOKING SWITCHES ON
GROUND SERVICE PANEL SWITCH IS LOCATED ON
GROUND SERVICE PANEL
EXTERNAL NOSE LEFT WING
P5 COCKPIT PANEL
FORWARD ATTENDANT
ENTRY DOOR SHOULD BE EQUIPPED EMERGENCY LIGHT SWITCH IS INSTALLED AT THE FUSELAGE, WHERE IS THE LOCATION OF BATTERY POWER SUPPLY
FWD CARGO COMPARTMENT
AFT CARGO COMPARMENT
CEILING CABIN
A AND B CORRECT
OVER FREQUENCY (OF) OCCUR, WHICH RELAY / BREAKER WILL TRIP
POWER READY RELAY AND GENERATOR BREAKER
ONLY POWER READY RELAY (PRR)
GCR, BPR, AND GB
ONLY GENERATOR BREAKER(GB)
THE BATTERY CAN BE CHARGE BY
BATTERY CHARGER
DC EXTERNAL POWER
DC BUS 1
DC BUS 2
The standby hydraulic system provide power to operate :
Landing gear, thrust reserve, and flight control
Trust reserve, rudder, and leading edge devices
Rudder, leading edge devices, and alternate brake.
Leading edge devices, alternate brake, and thrust reverse.
The pressure generation for system A is from :
One EDP and one PTU.
Two Engine Driven Pumps
One EDP and one EMDP.
Two Electric Motor Driven Pumps.
Low quantity in standby reservoir can be seen From:
Quantity indicator at standby reservoir.
Quantity indicator at P2 is shown below 88%.
Quantity indicator on P2 shown below 50%.
Low quantity amber light on P5.
The PTU is powered from:
System A pressure.
Standby system pressure.
System B Pressure.
AC bus 1
The PTU valve will open in flight if EDP low pressure and flap
Extended.
Not UP but < 15 units.
Extended.
Extend > 15 units
Retracted.
System B supplies:
Standby rudder
Alternate brake
Trailing Edge flap
Standby rudder and leading edge devices.
During engine Running with EDP switch is ON position:
Depressurization solenoid energized and blocking valve open.
Depressurization solenoid energized and blocking valve closed
Depressurization solenoid de-energized and blocking valve closed.
Depressurization solenoid de-energized and blocking valve open.
EDP low pressure amber light will illuminate if:
Fire handle is pulled and system pressure LOW.
Fire handle is pulled and system pressure normal
Fire handles normal and EDP output low pressure.
Fire handles normal and reservoir low
The over heat sensors EMDP are located on:
Reservoir.
Motor case housing and case return line of the EMDP.
Heat Exchanger.
Selecting EMDP switch to Off for 5 minutes.
After different current occurs, the EMDP can be reset by:
Push Reset button at P6-1
Automatic reset after EMDP removal
Selecting EMDP switch to OFF and then ON again.
Selecting EMDP switch to OFF for 5 minutes
Brake wear limits are checked by:
Measuring brake wear indication pin with brake release
Measuring brake wear indication pin brake applied.
Measuring length of return spring pins
Using GO/NO GO gage between brake rotor and stator plate
Landing gear is hydraulically operated
Using system A for alternate retraction
Using system B for alternate retraction and extension.
Using system A for alternate extension.
Using system B for alternate retraction.
With hydraulic system A available and system B failure:
Brake are operated by system A pressure.
Brake are operated by accumulator pressure.
Parking is operated by system A pressure.
A and C are the correct answers.
To prevent brake release during retraction of the landing gear:
The landing gear lever up switch
The alternate brake selector valve is opened.
The parking brake SOV close
The normal antiskid valves are provided an over dump signal.
When auto brake RTO is selected the amber light
Remain OFF if the system is good
Flashed for 1,5 seconds and comes on steady if system is bed.
Illuminate after 1,5 seconds if the system is bed.
Illuminate for 1,5 seconds and extinguishes if system is good.
Hydraulic pressure for auto brake operation is provided by:
System A.
PTU
System A and B.
System B.
Main gear air and ground safety sensor are controlled by
Extension and compression of the right main gear.
Ground proximity radar waves.
Extension and compression of the left main gear.
Wheel speed relays for the right main gear.
To prevent Hydraulic lock during landing gear manual extension:
Depressurized System A.
Place the landing gear control lever OFF.
Push the nose steering bypass vale
Place the gear control lever DOWN
In Flight the landing gear bypass closes when auto slat commanded and
PTU valve close.
System B low pressure
Transfer valve transferred condition.
Engine 1 failure N2 < 56%.
The normal antiskid system is monitored for Failure:
When the parking brake is set.
A. Only when the normal brake system is being used.
Continuously when antiskid is turn ON.
Only in the air with the parking brake released.
Two transfer valve test switches are located:
In The electronic equipment compartment.
On the rear of the transfer valve.
On the face of the E11 shelf.
On The Overhead panel.
When The Landing Gear transfer valve solenoid energized, the slide valve actuated by :
System A pressure.
Spring.
System B pressure
Standby system pressure.
After manual extension of the landing gear, the indication on the fight deck that correct procedure are
The light 3 green and 3 red illuminate.
The light 3 red or 3 green extinguish.
The light 3 green extinguish and 3 red illuminate.
The light 3 green Illuminate and 3 red extinguish.
Changing over from normal to alternate brake is controlled by
A solenoid operated transfer valve
An electric motor operated control valve.
A pressure operated selector valve
Manual lever on pilot centre panel.
During take-off climb, the landing gear transfer valve will operate and allows system B to rise when the:
Number 1 engine N2 below 56% and the gear is in transit up
System A fluid is lost.
Number 1 engine is at idle and the landing gear is not up.
System A the EDP and EMDP fail and gear is in transit up
The primary flight controls are:
Ailerons, Elevators, Flaps and Rudder
Ailerons, Elevators, Rudder and Spoiler.
Ailerons, Elevators, horizontal stabilizers, flaps and Rudder.
Aileron, Elevators and Rudder
The Flap asymmetry test switch is located:
In the avionic compartment.
On the P6
In the wheel well
On the P2.
When flight control switch A is selected to off:
Standby pump ON.
Flight control SOV A Close.
Flight control SOV A & B Close.
A & C are the correct answer
The Operation of the trailing edge flaps:
In normal it is powered by system B, and controlled by flap control lever.
In alternate it is powered by standby system, and control by alt control switch.
In normal is powered by system B and PTU.
A & B are correct answer.
With hydraulic pressure Available, the Aileron trim actuator electrically actuates:
Balance.
Control wheel.
Aileron and control wheel.
Aileron.
SPEED BRAKE DO NOT ARM light is illuminate if speed brake lever in armed position and:
Total antiskid OFF.
Speed brake lever actuator not in lower position.
Speed brake electrical circuit malfunction.
All Above are the correct answer.
The Stabilizer is operated in three ways:
Manual, main electric and autopilot.
Main electric, autopilot, and hydraulic.
Manual, main electric, and hydraulic
Manual, autopilot, and hydraulic.
The elevator can be moved by different input from:
Pilot command, pitot tube, feel computer and autopilot.
Pilot command, autopilot, Mach trim and stabilizer.
Feel computer, autopilot, Mach trim and stabilizer.
Pitot tube, feel computer, autopilot and Mach trim.
During normal operation the rudder is powered by:
Hydraulic system A
Hydraulic system B
Hydraulic system A & B
Standby System.
The AUTO SLAT FAIL light illuminates when:
Both channels are invalid.
One channel is invalid and master caution is recalled.
Dynamic alpha compares disagreement followed by master caution recalled.
All above are correct answer.
When the airplane is on ground and either throttle is advanced, the intermittent aural warning horn will sound if:
A. Speed brake lever down detent
A. Stabilizer green range.
Trailing edge flaps > 15 unit.
Leading edge flaps extend.
The Elevator feel force will increase if:
System A failure.
Airspeed increases.
System B failure.
All Above are correct.
During landing The speed brake lever will be placed:
In FLT DETEND.
At any is setting up to FLT DETEND.
In ARM
At any setting.
The Rudder Trim actuator is:
Hydraulic motor.
Electric motor.
Mechanical.
A and C are correct answers.
When asymmetry condition takes placed on the trailing edge flaps system:
A. Trailing edge flap is supplied by PTU.
A. Standby system automatically ON.
A. The bypass valve moves to bypass.
A. All above are correct.
The AUTO SLAT system will automatically cause the movement of:
Leading edge flaps from intermediate to full extend position.
Leading edge Slats from retract to full extend position.
Leading edge Slats from intermediate to full extend position.
Leading edge flaps from retract to full extend position.
With loss pressure on hydraulic system A and B What system operated the elevator:
Electrical system.
Standby Hydraulic system
Elevator cannot be controlled.
Mechanical control system.
During Rejected Take-Off (RTO) The speed brake lever will be lifted up by:
A. Wheel spin up to signal.
A. Right hand main gear.
A. Thrust reverser cam.
A. Throttle lever.
Whenever the aileron control is jammed, a force is exerted overcome a spring on the control system:
By First Officer to control aileron.
By firs Officer to control flight spoiler
By the Captain to control aileron.
By the captain to control flight spoiler.
The Flight control hydraulic module is installed to control the hydraulic power for:
Aileron, Rudder, Elevator and flight spoiler.
Aileron, Rudder and Elevator.
Aileron, Rudder and Trailing edge Flaps
Aileron, Rudder, Elevator and ground spoiler
The ELEVATOR FEEL DIFFERENTIAL light illuminates when:
Trailing edge flap are fully retracted
A difference of 25% between system A and B Output pressure is detected.
A & B are the correct answers.
Trailing edge are fully retracted and three no hydraulic pressure available.
To operated Trailing edge Flaps electrically:
Select alternate flap arm switch to ARM and moved flap lever.
Select flight control switch to STANDBY RUDD and move flap lever.
Select Alternate Flap arm switch to ARM and Move the alternate flap control switch.
Select flight control switch to STANDBY RUDD and move the alternate flap control switch.
The ground Spoiler are powered by:
The standby Hydraulic System.
Both A and B Hydraulic system.
The B Hydraulic system.
The A Hydraulic System.
The tailing edge Flaps asymmetry protection available:
Only when normal flaps system is operative.
In flight only
Only when the trailing edge flaps are in take-off position.
Only when alternate flap system is used.
The Yaw damper operation result in:
Rudder pedal movement.
No Rudder pedal movement provide the autopilot is engaged.
No Rudder pedal movement.
Rudder pedal movement and provide the autopilot is engaged
