WorksheetsTest 2 737MAX PAJ
Total questions: 74
Worksheet time: 37mins
The amber TR UNIT light illuminates when:
TRU 3 fails in flight only
TRU 2 fails in flight only
TRU 1 fails in flight only
AC power is not available
The TR Unit BITE test is performed from:
P8 overhead panel
P6 circuit breaker panel
P5-13 electrical panel
CDU maintenance pages
The amber DRIVE light illuminates when:
The generator is overloaded
The IDG oil pressure is low or temperature is high
The bus is unpowered
The generator breaker is open
The EPC contactor is located in the:
Flight deck
FWD compartment
Main electrical power panel
Battery compartment
To reconnect an IDG, the aircraft must be:
In flight
On ground with engine running
On ground with engine shutdown
Powered by GPU only
The amber BAT DISCHARGE light illuminates when:
Battery temperature is high
Battery is supplying excessive current
Battery voltage is normal
Battery charger is operating
The primary function of the BPCU is to:
Control TR units
Monitor battery charging and protection
Control IDG operation
Control external power
When external power is connected, which system controls battery charging?
TR Unit
Generator Control Unit
BPCU
EPC
A failed TR unit will result in:
Loss of all AC power
Reduced DC power redundancy
Loss of battery protection
Generator disconnect
Which bus is normally powered by the battery?
AC Transfer Bus
DC Ground Service Bus
Battery Bus
Standby AC Bus
The Fuel Quantity Processor Unit (FQPU) is located in the:
Flight deck
Cargo compartment
EE compartment
Wheel well
The INSUFFICIENT FUEL indication appears when:
Fuel temperature is low
Fuel quantity is below dispatch requirements
Fuel imbalance exists
Fuel pumps fail
The FUEL DISAGREE message indicates:
Fuel differences is detected by FMC
Left and right fuel indications differ beyond limits
Fuel temperature disagreement
Refuel valve failure
The USING RSV FUEL message indicates:
Center tank fuel is being used
Main tank fuel is depleted
Reserve fuel is being consumed
Fuel pumps are off
The FQIS BITE test is performed from:
P5 overhead panel
P6 circuit breaker panel
CDU maintenance pages
EEC test panel
Fuel quantity is measured using:
Flow meters
Pressure sensors
Capacitance probes
Temperature sensors
A failure of the FQPU will result in:
Fuel leak warning
Fuel quantity blanking
Engine shutdown
Crossfeed inoperative
Fuel temperature is primarily used to:
Control fuel pumps
Correct fuel density calculations
Control engine thrust
Detect contamination
The APU can supply pneumatic air up to approximately:
FL100
FL170
FL200
FL250
The APU ECU is located in the:
Flight deck
Tail cone
EE compartment
Wheel well
The Data Memory Module (DMM) stores:
Flight data
APU maintenance fault history
Navigation databases
Engine trend data
APU bleed air is Controlled by:
EEC
ECU
IASC
Fuel system
The APU ECU is located:
FWD Compartment
AFT Cargo Compartment
E/E Compartment
Cockpit
An APU shutdown may be caused by:
Low oil pressure
Overspeed
High EGT
All of the above
The main engine modules include:
Fan, Core and LP Modules
Fan and exhaust only
Gearbox and accessories only
Fuel and ignition systems
The High Pressure Compressor (HPC) has:
5 stages
8 stages
10 stages
12 stages
The High Pressure Turbine (HPT) has:
One stage
Two stages
Three stages
Four stages
The Low Pressure Turbine (LPT) has:
Two stages
Five stages
Six stages
Eight stages
The engine has how many main bearings?
3
5
7
9
Ball bearings are primarily used to:
Carry axial loads
Carry radial loads only
Reduce oil pressure
Drive accessories
Roller bearings are primarily used to:
Carry axial loads
Carry radial loads
Balance the rotor
Drive the fan
Engine balance weights are installed on the:
Fan blades
Platform front shroud
Rotating shafts
Turbine blades
The Accessory Gearbox (AGB) drives:
Fuel pump, oil pump, IDG
Fan only
Turbine only
Starter only
The AGB is driven by the:
Fan shaft
LPC shaft
HP shaft
Gear train only
Each engine has how many EGT sensors?
6
8
12
18
Engine vibration is calculated using inputs from:
N1 and N2 sensors
N1 Bearing Accelerometer
N1 Bearing Accelerometer
All of the above
The maximum EGT limit is monitored during
Cruise only
Start and takeoff
Shutdown
Taxi
The ENG FAIL message indicates
Engine fire
Loss of thrust or severe malfunction
Fuel leak
EGT exceedance only
Engine vibration data is processed by the
ADIRS
EEC
FCC
FDR
Excessive vibration may result in
Maintenance message only
Engine shutdown
Autothrottle disconnect
All of the above
The engine fuel pump contains:
One pump only
Low pressure pump only
Low- and high-pressure pumps
Electric pumps only
The PMA provides electrical power when:
Engine is shut down
N2 reaches a minimum speed
Battery voltage is low
Generator fails
The Data Entry Plug is located on the:
Engine case
EEC
Flight deck
Pressure sub-system
The function of the Data Entry Plug is to:
Store engine trust configuration
Control fuel flow
Measure vibration
Control ignition
P3B pressure input is used to:
Control oil pressure
Control Start scheduling
Control ignition timing
Monitor Engine Bleed Air
The ALTN light on the EEC indicates:
Backup channel mode operation
Engine shutdown
Fire detection
ADIRU Data Lost
The ENGINE CONTROL light indicates:
Normal operation
EEC fault or non-dispatchable fault
Fire detection
Fuel imbalance
The PMA begins supplying power at approximately:
8.5% N2
12.5% N2
32% N2
51% N2
The MTC function is to:
Control thrust reverser
Colds HPT first stage
Control fuel temperature
Control oil pressure
The TBV controls:
HPC airflow
LPC airflow
Fuel flow
Oil flow
The SB/BAI position is sensed by:
Pressure switches
LVDT
RVDT
Proximity switches
SB/BAI actuators use which fluid?
Hydraulic
Oil
Electrical
Fuel
The EEC receiving the ODMS signal is:
EEC A only
EEC B only
Both EECs
Neither EEC
The Sump Eductor uses air from the:
HPC 7th stage air
Bleed air system
Core exhaust
Ram air
In normal operation, standby ignition powers:
Igniter A only
Igniter B only
Both igniters
Neither igniter
The EEC calculates motoring time using:
N1 only
N2 and EGT
T3 and TCF
Fuel flow
During motoring, the EEC controls:
Fuel flow
Ignition
Starter and air flow
Thrust reverser
The starter valve closes at approximately:
35% N2
41% N2
56% N2
63% N2
Thrust reverser movement is controlled by the:
EEC
TCM
Hydraulics only
FCC
REVERSER LIMITED indicates:
Reverser fully deployed
Limited reverser operation
Reverser stowed
Engine shutdown
The PTU function is to:
Transfer fuel
Transfer electrical power
Transfer hydraulic power
Cool hydraulic fluid
The PTU activates when:
Both systems are pressurized
EDP B pressure drops
Engine is shut down
Parking brake is set
The landing gear lever contains how many microswitches?
Two
Three
Ten
Five
Opening the manual gear extension panel causes:
Gear to extend
Selector valve to bypass mode
Hydraulics to shut down
Gear lever lock
The Broken Cable Compensator is part of the:
Landing gear
NW steering system
Brake system
Flap system
FLAP SKEW occurs when:
One flap corner moves faster
Left and right flap positions differ
Slats fail
Asymmetry protection activates
TAKEOFF CONFIG warning occurs when:
Aircraft speed is low
Configuration is unsafe for takeoff
Engine fails
Autopilot is engaged
The IASC contains separate sections for:
Air supply and air conditioning
Fuel and bleed air
Cooling only
Pressurization only
The duct pressure indication is provided by:
Pressure transmitter (PM)
Temperature sensor (TM)
Pressure transmitter 2 (PM2)
CPC
The DVV opens at approximately:
20 psi
100 psi
148 psi
70 psi
The ZONE TEMP light illuminates when duct temperature exceeds:
Normal range
190F
80 C
100F
Cabin altitude warning occurs at approximately:
8,000 ft
10,000 ft
12,500 ft
14,000 ft
The NGS controller is located in the:
Flight deck
EE compartment
Cargo compartment
Tail cone
The equipment cooling smoke detection will result in:
Advisory only
Automatic cooling reconfiguration
Fire warning
System shutdown
