C-17 PIQ End Of Course Test (Updated)
2026-2027
Expert-Verified Questions and Answers
(With A+ Grades Guarantee)
,The APU and EPU supply electrical power to the b) left and right sides
__________ of the aircraft, respectively.
a) right and left sides
b) left and right sides
c) forward and aft ends
d) aft and forward ends
Crewmembers should silence any aural warning as soon True
as the cause of the warning is recognized.
True
False
The transformer/rectifiers perform the function of d) converting AC power to DC power.
a) providing power for APU start.
b) converting DC power to AC power.
c) providing emergency power for the DC buses.
d) converting AC power to DC power.
When using the DC electrical system, the __________ a) split-parallel
configuration is the normal mode for operation.
a) split-parallel
b) conversion
c) isolated
d) parallel
Which generator buses are the normal sources of power c) 1 & 4
for the battery chargers?
a) 2 & 3
b) 1 & 2
c) 1 & 4
d) 2 & 4
Which of the following buses is always powered even if the b) Battery direct bus
battery switch is OFF?
a) Emergency power bus
b) Battery direct bus
c) AC transfer bus
d) DC transfer bus
Which position of the avionics bus switch (AV BUS) c) AUTO
enables automatic load shedding when the aircraft is on
the ground with inadequate cooling?
a) ORIDE
b) OFF
c) AUTO
d) OPEN
Which component(s), during emergency/backup system a) Static inverter
operations, converts DC power into AC power for the AC
emergency bus?
a) Static inverter
b) Battery chargers
c) Emergency power relay
d) AC and DC transfer buses
,Power for the backup emergency system is provided by c) aircraft batteries
the
a) electrical power unit.
b) auxiliary power unit.
c) aircraft batteries.
d) integrated drive generators.
What should be done if the battery bus fails? a) Land as soon as possible
a) Land as soon as possible
b) Recycle the right generator tie bus
c) Continue to flight destination
d) Recycle the battery switch
If a GEN OIL caution message appears on the WAP, the d) turn the generator off.
corrective action is to
a) increase power on that engine to promote cooling.
b) reduce the electrical load on that generator bus.
c) place that engine in reverse idle to cool the generator.
d) turn the generator off.
If all generators fail, what becomes inoperative with a d) Yaw damping
subsequent failure of one of the remaining flight control
computers (FCC 1 or 4) or IRUs (1 or 4)?
a) Flaps
b) Landing gear
c) Mission computer
d) Yaw damping
When performing the Electrical Fire and Smoke checklist, a) pause after each step which depowers a portion of the aircraft.
a) pause after each step which depowers a portion of the
aircraft.
b) do each step in rapid succession.
c) wear asbestos gloves at all times.
d) never pull out any circuit breakers.
The engine-driven hydraulic pumps provide continuous a) 4,000
hydraulic pressure of _____________ psi.
a) 4,000
b) 4,200
c) 4,500
d) 5,000
The engine-driven hydraulic pumps are located in the a) respective engine accessory gear box.
a) respective engine accessory gear box.
b) right aft gear pod.
c) wheel wells.
d) cargo compartment.
There is/are _______ engine driven hydraulic pump(s) per b) two
system, located on and driven by their respective engine
accessory gearbox.
a) one
b) two
c) three
d) four
, The primary purpose of the _____ pump is to assist in b) transfer
landing gear retraction or cargo door/ramp closing in the
event of No. 2 or 3 engine loss.
a) auxiliary
b) transfer
c) primary
d) secondary
The RAT, located in the forward right main gear pod, d) all engine-out emergency.
develops enough hydraulic pressure to control the aircraft
for
a) takeoff and refueling.
b) emergency refueling.
c) LAPES delivery.
d) all engine-out emergency.
During ground operations, you have been using hydraulic d) failure of AUX pump 1.
system 1 without any engines running. The MASTER
CAUTION light comes on as well as the HYD cue light and
a LOW in the Sys 1 Aux pump switchlight. You should
conclude that you have
a) low temperature in system 1.
b) asymmetric slats.
c) overpressure condition in system 1.
d) failure of AUX pump 1.
Transfer pump automatic shut off may be caused by a) a low quantity condition in System 2 or 3.
a) a low quantity condition in System 2 or 3.
b) overpressure in System 2.
c) a low quantity condition in System 1 or 4.
d) pressure between 3400 and 4000 in System 2 or 3.
If the hydraulic system pressure increases above 4200 psi, a) all PRI, SEC, and AUX HYD pumps.
depressurize
a) all PRI, SEC, and AUX HYD pumps.
b) the pumps one at a time.
c) all engine-driven pumps.
d) the transfer and auxiliary pumps
The primary source of oxygen for the crew system is a) one 25-liter
_______ liquid oxygen converter(s).
a) one 25-liter
b) one 75-liter
c) two 25-liter
d) two 75-liter
The oxygen crossfeed switch is used to d) connect the crew and passenger oxygen systems.
a) connect the auxiliary system to the passenger system.
b) isolate the passenger oxygen converter.
c) isolate the crew oxygen converter.
d) connect the crew and passenger oxygen systems.
The CREW OXY LOW warning illuminating on the WAP a) quantity remaining is less than 5 liters or supply pressure is below 60 +/- 5 psi.
indicates the oxygen
a) quantity remaining is less than 5 liters or supply
pressure is below 60 +/- 5 psi.
b) quantity remaining is less than 7.5 liters or supply
pressure is below 75 +/- 5 psi.
c) pressure is below 75 psi.
d) pressure is above 80 psi.
2026-2027
Expert-Verified Questions and Answers
(With A+ Grades Guarantee)
,The APU and EPU supply electrical power to the b) left and right sides
__________ of the aircraft, respectively.
a) right and left sides
b) left and right sides
c) forward and aft ends
d) aft and forward ends
Crewmembers should silence any aural warning as soon True
as the cause of the warning is recognized.
True
False
The transformer/rectifiers perform the function of d) converting AC power to DC power.
a) providing power for APU start.
b) converting DC power to AC power.
c) providing emergency power for the DC buses.
d) converting AC power to DC power.
When using the DC electrical system, the __________ a) split-parallel
configuration is the normal mode for operation.
a) split-parallel
b) conversion
c) isolated
d) parallel
Which generator buses are the normal sources of power c) 1 & 4
for the battery chargers?
a) 2 & 3
b) 1 & 2
c) 1 & 4
d) 2 & 4
Which of the following buses is always powered even if the b) Battery direct bus
battery switch is OFF?
a) Emergency power bus
b) Battery direct bus
c) AC transfer bus
d) DC transfer bus
Which position of the avionics bus switch (AV BUS) c) AUTO
enables automatic load shedding when the aircraft is on
the ground with inadequate cooling?
a) ORIDE
b) OFF
c) AUTO
d) OPEN
Which component(s), during emergency/backup system a) Static inverter
operations, converts DC power into AC power for the AC
emergency bus?
a) Static inverter
b) Battery chargers
c) Emergency power relay
d) AC and DC transfer buses
,Power for the backup emergency system is provided by c) aircraft batteries
the
a) electrical power unit.
b) auxiliary power unit.
c) aircraft batteries.
d) integrated drive generators.
What should be done if the battery bus fails? a) Land as soon as possible
a) Land as soon as possible
b) Recycle the right generator tie bus
c) Continue to flight destination
d) Recycle the battery switch
If a GEN OIL caution message appears on the WAP, the d) turn the generator off.
corrective action is to
a) increase power on that engine to promote cooling.
b) reduce the electrical load on that generator bus.
c) place that engine in reverse idle to cool the generator.
d) turn the generator off.
If all generators fail, what becomes inoperative with a d) Yaw damping
subsequent failure of one of the remaining flight control
computers (FCC 1 or 4) or IRUs (1 or 4)?
a) Flaps
b) Landing gear
c) Mission computer
d) Yaw damping
When performing the Electrical Fire and Smoke checklist, a) pause after each step which depowers a portion of the aircraft.
a) pause after each step which depowers a portion of the
aircraft.
b) do each step in rapid succession.
c) wear asbestos gloves at all times.
d) never pull out any circuit breakers.
The engine-driven hydraulic pumps provide continuous a) 4,000
hydraulic pressure of _____________ psi.
a) 4,000
b) 4,200
c) 4,500
d) 5,000
The engine-driven hydraulic pumps are located in the a) respective engine accessory gear box.
a) respective engine accessory gear box.
b) right aft gear pod.
c) wheel wells.
d) cargo compartment.
There is/are _______ engine driven hydraulic pump(s) per b) two
system, located on and driven by their respective engine
accessory gearbox.
a) one
b) two
c) three
d) four
, The primary purpose of the _____ pump is to assist in b) transfer
landing gear retraction or cargo door/ramp closing in the
event of No. 2 or 3 engine loss.
a) auxiliary
b) transfer
c) primary
d) secondary
The RAT, located in the forward right main gear pod, d) all engine-out emergency.
develops enough hydraulic pressure to control the aircraft
for
a) takeoff and refueling.
b) emergency refueling.
c) LAPES delivery.
d) all engine-out emergency.
During ground operations, you have been using hydraulic d) failure of AUX pump 1.
system 1 without any engines running. The MASTER
CAUTION light comes on as well as the HYD cue light and
a LOW in the Sys 1 Aux pump switchlight. You should
conclude that you have
a) low temperature in system 1.
b) asymmetric slats.
c) overpressure condition in system 1.
d) failure of AUX pump 1.
Transfer pump automatic shut off may be caused by a) a low quantity condition in System 2 or 3.
a) a low quantity condition in System 2 or 3.
b) overpressure in System 2.
c) a low quantity condition in System 1 or 4.
d) pressure between 3400 and 4000 in System 2 or 3.
If the hydraulic system pressure increases above 4200 psi, a) all PRI, SEC, and AUX HYD pumps.
depressurize
a) all PRI, SEC, and AUX HYD pumps.
b) the pumps one at a time.
c) all engine-driven pumps.
d) the transfer and auxiliary pumps
The primary source of oxygen for the crew system is a) one 25-liter
_______ liquid oxygen converter(s).
a) one 25-liter
b) one 75-liter
c) two 25-liter
d) two 75-liter
The oxygen crossfeed switch is used to d) connect the crew and passenger oxygen systems.
a) connect the auxiliary system to the passenger system.
b) isolate the passenger oxygen converter.
c) isolate the crew oxygen converter.
d) connect the crew and passenger oxygen systems.
The CREW OXY LOW warning illuminating on the WAP a) quantity remaining is less than 5 liters or supply pressure is below 60 +/- 5 psi.
indicates the oxygen
a) quantity remaining is less than 5 liters or supply
pressure is below 60 +/- 5 psi.
b) quantity remaining is less than 7.5 liters or supply
pressure is below 75 +/- 5 psi.
c) pressure is below 75 psi.
d) pressure is above 80 psi.
