WorksheetsStudy Guide Systems 2
Total questions: 150
Worksheet time: 38hrs 30mins
Which of the following are correct major components of the electrical system?
Starter/generator, 24 VDC battery, and backup 28 VDC battery pack
External power receptacle, starter/generator, and backup alternator
Starter/generator, external power receptacle, and AC/DC power converter.
Starter/generator, 24 VDC battery, 24 VDC auxiliary battery
The aircraft main battery is rated to provide ________.
18 VDC; 5 amp/hour
24 VDC; 5 amp/hour
24 VDC; 42 amp/hour
28 VDC; 42 amp/hour
The generator function of the starter/generator provides __________.
backup aircraft power
standby power for aircraft avionics
primary aircraft power
power for the starter
On the right console panel in each cockpit are circuit breakers protecting systems and equipment operating from the __________.
generator bus
cockpit power bus
external power bus
battery bus
The BUS TIE switch on the right forward switch panel in the front cockpit is used to __________.
tie the battery bus and generator bus together for normal operation
control the power from the generator
connect the power for all the avionics and radio systems in both cockpits
tie the battery bus and generator bus together for emergency operation
The ability to control the generator using the generator control switch is
__________.
transferable between cockpits
permanently assigned to the front cockpit
permanently assigned to the rear cockpit
transferred automatically if either cockpit control fails
__________are provided to protect aircraft systems and equipment which receive power from the generator and battery buses.
Circuit breakers
Current limiting switches
Surge arrestors
Backup generators
External aircraft lighting for the T-6B is controlled by four individual switches which are the ________ switches.
landing, taxi, strobe, and anti-crash
taxi/landing, strobe, flood, and navigation
landing, taxi, anti-collision, and navigation
taxi/landing, anti-collision, flood, and navigation
The landing light will come on__________.
anytime the LDG switch is on
only when the LDG and taxi switches are both on and the landing gear is down and locked
only when the LDG switch is on and the landing gear is down and locked
automatically when there is low ambient light
Fuel for the T-6B is stored in __________ separate tanks.
three
two
six
four
When using the primary T-6B refueling method, the aircraft fuel system provides approximately __________ of usable fuel.
1200 pounds
1100 pounds
1200 gallons
1100 gallons
The __________ routes fuel to the __________ which controls fuel delivery to the engine.
transfer jet pumps; motive flow line unit
electrical boost pump; engine-driven low pressure fuel pump
engine-driven high pressure fuel pump; fuel management unit
primary jet pump; fuel management unit
The __________ is mounted in the collector rank and provides for initial engine start and serves as a backup to the engine-driven low pressure fuel pump.
engine-driven low pressure fuel pump
primary jet pump
engine-driven high pressure fuel pump
electric boost pump
The single point refueling system refuels__________.
the collector tank first and then gravity feeds the wing tanks
both wing tanks simultaneously
the right wing tank followed by the left wing tank
the left wing tank followed by the right wing tank
Fuel is directed to the collector tank from each wing tank by __________, keeping the collector tank pressurized.
the collector tank pressure pump
the electric boost pump
a primary jet pump
two transfer jet pumps
A pressure switch in the motive flow line activates the __________ anytime fuel
pressure drops below 10 psi and the PCL is above the start ready position.
transfer jet pumps
electric boost pump
engine-driven high pressure pump
primary jet pump
Which of the following statement is correct concerning the engine fuel feed line shutoff valves?
The firewall shutoff valve is provided to isolate the fuel system for engine or fuel maintenance.
The maintenance shutoff valve stops fuel flow to the engine and is activated by the firewall shutoff handle.
The firewall shutoff valve stops fuel flow to the engine and is activated by the firewall shutoff handle.
Both shutoff valves are provided to isolate the fuel filter system for engine or fuel maintenance.
Fuel level sensors in each wing tank cause either right or left fuel level low CAS caution messages to display whenever the fuel quantity in that tank is below __________.
50 lbs
50 gallons
110 lbs
110 gallons
The fuel flow indicator in the EICAS display presents fuel flow in __________.
gallons per minutes
gallons per hour
pounds per minute
pounds per hour
Display of the FUEL BAL message may indicate an imbalance exceeding
__________ pounds for more than _______ minutes between left and right fuel tanks.
20; 2
30; 2
50; 3
70; 3
What are the two major components for the propulsion system?
Engine cowling and PCL
Propeller and reduction gearbox
Engine and propeller
PCL and engine
What three elements are necessary for operation of the engine?
Air, oil, and fuel
Air, fuel, and electricity
Air, fuel, and heat
Oil, fuel, and heat
What are the three major sections of the engine?
Compressor, combustion, and reduction areas
Compressor, combustion, and power sections
Accessory compartment, gas generation section, and power turbine section
Accessory compartment, compressor section, and combustion section
What is meant by the term “free turbine”?
This is where the free air temperature is measured.
Air does not move from the compressor to the power turbine.
The “free” air stream drives the power turbine.
The compressor and power turbines are not physically connected.
The starter/generator __________ until the engine starts and is able to sustain itself.
turns the propeller
turns the power turbine
provides fuel
turns the compressor
For autostart, the ignition switch should be placed in the __________.
START position
NORM position
START detent
ON position
The oil system provides oil under pressure to which of the following?
Nose wheel steering
Engine bearings and propeller
Engine-driven fuel pump and engine bearings
Propeller, generator, and fuel management unit
With the engine above IDLE power a red OIL PX message illuminates when oil
pressure falls below __________psi.
15
40
50
90
The __________ and the __________ control propeller speed to maintain a
constant propeller speed of 2000 RPM and achieve varying levels of thrust by
automatically adjusting propeller pitch.
fuel flow regulator; fly weights
PMU; propeller interface unit
feathering spring; regulator unit
torque probe; scavenger unit
Which propeller position will the propeller be in during most flight conditions?
high propeller pitch
thrust position
low propeller pitch
feather position
The fire warning system consists of a core element, sensor tube, and responder assembly. The sensor tubes are built such that __________don’t affect system reliability.
kinks, twists, or dents
core element disintegration
responder assembly malfunctions
helium gas leaks
Air for cockpit heating, canopy defogging, and cockpit pressurization is provided by __________.
recirculated engine exhaust
ram intake air
engine bleed air
compressed air tanks
The __________, combined with input from two temperature sensors, controls the position of the heat exchanger bypass valve to maintain desired cockpit
temperature.
BLEED AIR INFLOW switch
RAM AIR FLOW switch
temperature controller
vent control lever
The RAM AIR FLOW switch on the environmental control panel in the front cockpit controls the amount of fresh air entering the cockpit and is overridden when __________.
the weight-on-wheels switch is activated after takeoff and the pressurization system begins to operate
either cockpit vent control lever is moved to the OFF position
the TEMP CONTROL switch is moved to the MANUAL position
the aircraft reaches an altitude of about 8000 feet and the pressurization system begins to operate
The air conditioning system’s __________ draws warm cockpit air through the
evaporator coils to absorb the heat from the air.
evaporator blower
compressor
high-pressure pump
condenser
The air conditioning system’s __________ converts refrigerant vapor to a high
pressure liquid.
condenser
compressor
evaporator blower
evaporator module
The environmental control system panel is located on the __________ in the front cockpit.
right side console
lower right instrument panel
upper left instrument panel
left side console
Once emergency oxygen flow is started, the emergency cylinder will supply oxygen for approximately __________ minutes.
5
10
15
20
The T-6B cockpit is pressure sealed by the seal around the bottom of the canopy and the __________.
firewall, aft pressure flooring, and center bulkhead
firewall and aft pressure bulkhead
firewall and pressure flooring
firewall, pressure flooring, and aft pressure bulkhead
After takeoff, power is applied to the __________which closes, allowing the control valve to regulate cockpit pressure as the aircraft approaches 8000 feet pressure
altitude.
delta P regulator
dump solenoid
cockpit pressure regulator
safety valve
Each of the following components/systems are part of the T-6B canopy system, EXCEPT the _________.
canopy pressurization sealing system
canopy locking/latching system
canopy quick release maintenance handle
canopy fracturing system
Which of the following canopy sections provide enhanced birdstrike protection?
All canopy sections
Front windscreen and forward transparency
Forward and rear transparencies
Front windscreen and rear transparency
In order to close the canopy from the outside, you must first __________.
connect external aircraft power
deflate the canopy seal
pull the canopy lock release handle in either cockpit
latch the canopy release control handle
What aircraft power must be available for the Canopy Fracturing System (CFS) to operate?
electrical
hydraulic
pneumatic
aircraft power is not required
The internal CFS handles initiate the process that__________.
fractures both canopy transparencies
unlocks and opens the canopy
only fractures the transparency for its respective cockpit
fractures the canopy frame and transparencies
The T-6B ejection seat is designed to provide rapid ejection capability at zero
altitude and zero airspeed up to __________feet and __________ KIAS.
30,000; 300
31,000; 350
35,000; 370
37,000; 370
During the ejection sequence, the __________ignites as the seat reaches the top of the rails.
manifold cartridge
rocket motor
manifold cartridge and the rocket motor
rocket motor and the CFS
Where is the ejection seat safety pin installed when you want to safe the seat?
Directly into the ejection seat MOR handle
Into the ejection seat armrest
Into the SSK selector valve
Directly into the ejection handle mechanism
With the ISS set to BOTH, the sequence of the two seat ejections is __________.
front, then rear
determined by which pilot initiates it
rear, then front
simultaneous
The (PIRD) Powered Inertia Retraction Device __________.
secures the harness to the lap belt assembly
properly positions the pilot during ejection
ensures freedom of movement by the pilot during ejection
secures the SSK to the lap belt assembly
The electrical component which regulates and monitors the starter/generator is called the ________.
generator control unit
electrical regulator
electronic monitoring unit
starter/generator monitor
The generator provides ________ power to operate aircraft electrical equipment.
12 VDC
24 VDC
28 VDC
120 VAC
When the occupant of either cockpit moves the generator control switch to ON, the switch in the other cockpit (if already selected ON) ________.
is locked in its current position
trips the GEN SW circuit breaker
is tripped to the OFF position
remains in the ON position
The ability to control the battery using the battery control switch is ________.
permanently assigned to the front cockpit
transferable between cockpits
permanently assigned to the rear cockpit
transferred automatically if either cockpit control fails
Under normal operating conditions, T-6B electrical power is distributed across the ________ and the ________.
generator bus; battery bus
standby bus; generator bus
standby bus; external power bus
external power bus; battery bus
With the BUS TIE switch engaged (in the NORM position), the generator provides electrical power to the ________.
avionics bus only
generator and battery buses
battery bus only
generator bus only
On the left console panel in each cockpit are circuit breakers protecting systems and equipment operating from the ________.
cockpit power bus
generator bus
external power bus
battery bus
The secondary electrical system’s auxiliary battery is rated at ________.
12 VDC, 5 amp/hour
24 VDC, 5 amp/hour
24 VDC, 42 amp/hour
28VDC, 42 amp/hour
Instrument panel lights are controlled through a knob labeled INST. This includes LSK and UFCP backup illumination levels.
TRUE
FALSE
Fuel is stored in ________.
a storage tank, a collector tank, and a feed tank
two wing tanks and a collector tank
a refuel staging tank and two wing tanks
a wing tank, a centerline feed tank, and a scavenger tank
The ________ provides fuel for initial engine start and acts as a backup to the engine-driven low pressure fuel pump.
electric boost pump
transfer jet pump
primary jet pump
engine-driven high-pressure fuel pump
The ________ tank stores approximately 40 pounds of fuel.
left wing
right wing
aft fuselage
collector
When using the primary T-6B refueling method, maximum useable fuel in each wing tank is approximately ________ pounds.
500
530
560
590
The ________ ensures a minimum of 15 second supply of fuel is available regardless of aircraft orientation.
electric boost pump
primary jet pump
wing tank flapper valve
flip-flop valve
Which refueling method can place more fuel in the wing tanks?
Both methods have the same maximum fill capacity
Over-the-wing gravity refueling
Single point pressure refueling
Aerial refueling
When a fuel imbalance occurs, a transfer (solenoid) valve closes the motive flow line to the ________.
manifold valve
collector tank
light tank
heavy tank
The CAS warning message, FUEL PX, is activated by the ________ and indicates the fuel pressure in the motive flow line is less than 10 psi.
electric boost pump
low pressure switch
high pressure switch
motive flow switch
The fuel gauging system uses seven fuel probes inside the fuel tanks to ________.
transmit the fuel from the wing tanks to the collector tank
send a signal to the UFCP for visual display of fuel flow
reduce corrosion within the fuel tank
send a signal to the Engine Indication and Crew Altering System (EICAS) for visual display of fuel quantity
________ is measured by the fuel flow transmitter and is displayed in ________.
Inter-wing fuel transfer; pounds per second
Engine fuel consumption; pounds per hour
Refueling rate; pounds per hour
Boost pump pressure; psi
The ________ delivers fuel to the ________, which manages fuel flow to the engine.
transfer jet pump; engine-driven high pressure fuel pump
transfer jet pump; FMU
engine-driven low pressure fuel pump; primary jet pump
engine-driven high pressure fuel pump; FMU
The primary purpose of the engine is to _______.
produce power
produce lift
compress air
turn engine accessories
The engine cowling does all of the following EXCEPT ________.
provides 2% additional lift
reduces drag
provides air intake for engine cooling
protects the engine components
What are the three major sections of the engine?
compressor, combustion, and reduction areas
compressor, combustion, and power sections
accessory compartment, gas generation section, and power turbine section
accessory compartment, compressor section, and combustion section
The power turbine section contains which of the following components?
the propeller shaft, reduction gearbox, exhaust case, and power turbine
the reduction gearbox, combustion chamber, and exhaust case
the exhaust case, compressor turbine, combustion chamber, and propeller
the compressor turbine, propeller shaft, and power turbine
What is the function of the reduction gearbox?
provides power to engine accessories
provides a mechanical link between the compressor and combustion sections
reduces power turbine output shaft speed and drives the propeller
reduces the pressure of the exhaust
During a normal start, the starter remains engaged until ________.
the engine starts and is able to run at idle
the starter switch is moved to the NORM position
the starter switch is moved to manual
30 seconds have elapsed
The chip detector sensor is located _________.
in the hot oil return line
in the reduction gear box
in the oil tank
in the cooling assembly
With the engine at IDLE power a red OIL PX message illuminates when oil pressure falls below _________ psi.
15
40
50
90
The propeller converts engine power into ______.
torque
shaft horsepower
thrust
vertical lift
Which of the following propeller positions produce the least amount of thrust and drag?
high propeller pitch
low propeller pitch
feather position
all propeller positions create equal thrust and drag
The engine fire warning system consists of a core element, a sensor tube, and ____________.
a thermostat
a responder assembly
a temperature gauge
microswitches
The pilot in the rear cockpit has control of which environmental system component?
rear cockpit bleed air inflow
rear cockpit blower fan speed only
all environmental systems
rear cockpit heating temperature
Cockpit heat is provided by _______, routed through a heat exchanger and/or a heat exchanger bypass valve, through the firewall, and into the cockpit.
filtered engine exhaust
warm engine bleed air
electrically heated air
recirculated cockpit air
T-6B cockpit cooling is provided by a vapor cycle ________ system.
evaporator blower
ventilation
ram air
air conditioning
The EVAP BLWR control(s) is/are located in the ________ and provide(s) power to the _________.
front and rear cockpits; outside ram air
rear cockpit only; rear evaporator blower
front cockpit only; front evaporator blower
front and rear cockpits; evaporator blowers
The bleed air inflow control switch controls how much _______ air will be provided to the environmental system.
cool engine bleed
hot engine bleed
recirculated
outside ram
Setting the _______ switch to ON opens the bi-level flow control bypass valve (defog valve) to provide a higher volume of bleed air flow to the system.
TEMP CONTROL
Vent lever
AIR COND
DEFOG
The emergency oxygen cylinder is considered adequately charged if the pointer is anywhere in the black band, otherwise ________.
flight is restricted to below 10,000' MSL
maintenance should be notified
only unpressurized flight is authorized
flight is restricted to below 8000' MSL
Cockpit pressure altitude is maintained by the control valve at ______ feet until a cockpit pressure differential of 3.6 ±0.2 psi is reached at 18,069 feet.
8000
10,000
12,000
16,000
Oxygen ________ are installed in the right side console in each cockpit and control OBOGS electrical power and oxygen flow.
regulators
plenums
concentrators
supply monitors
The T-6B is equipped with a single, side-opening, __________ operated canopy.
electrically
hydraulically
pneumatically
manually
Do not open the canopy if surface winds exceed ______ knots.
25
30
35
40
The major canopy components of the T-6B are the ________.
environmental system, canopy frame, canopy fracturing system
canopy latching system, electric canopy motor, canopy frame, front and rear transparencies
canopy frame assembly, hydraulic canopy motor, front and rear transparencies
canopy frame assembly, front windscreen, forward transparency , and rear transparency
The _______ light and _______ message illuminate if the canopy is not down and locked.
MASTER WARN; UNLOCK
MASTER CAUT; UNLOCK
MASTER WARN; CANOPY
MASTER CAUT; CANOPY
The external CFS handles initiate the process that _______.
fractures the canopy frame and transparencies
jettisons the transparency for its respective cockpit
unlocks and opens the canopy
fractures both canopy transparencies
The T-6B ejection seat is designed to provide rapid ejection capability at zero altitude and zero airspeed up to _______ feet and _______ KIAS.
30,000; 300
35,000; 370
31,000; 350
37,000; 370
When flying dual, the ISS should be set to _______ to allow _______.
BOTH; simultaneous ejections
BOTH; either pilot to initiate dual ejections
SOLO; both pilots to initiate dual ejections
SOLO; either pilot to initiate dual ejections
During ejection, the _______ automatically retracts the shoulder harness straps.
Headbox Power Retraction Unit
Automatic Reel Retraction Unit
Powered Inertia Retraction Device
Harness Reel Activation Drive
What happens if the SSK; Automatic Deployment Unit (ADU) mode selector value is set to the AUTO position?
The SSK is lowered 10 seconds after ejection
The SSK is lowered 4.0 seconds after seat-pilot separation
The SSK is lowered 4.0 seconds after ejection
The SSK is lowered 10 seconds after seat-pilot separation
When should the Manual Override (MOR) Handle be used?
To manually initiate seat/pilot separation if the automatic system fails
If seat/pilot separation is desired above 14,000 feet MSL
If ejection over mountainous terrain exceeding 8000 feet MSL
All of the above are correct
Which of the following are correct major components of the electrical system?
Start/generator, 24 VDC battery, and backup 28 VDC battery pack
Starter/generator, 24 VDC battery, and 24 VDC auxiliary battery
External power receptacle, starter/generator, and backup alternator
Starter/generator, external power receptacle, and AC/DC power converter
In normal operation, components assigned to the battery and generator buses are fed by power supplied from __________.
the primary battery
the generator
the external power receptacle
the auxiliary battery
The generator provides ______ power to operate aircraft electrical equipment.
12 VDC
28 VDC
24 VDC
120 VAC
On the right console panel in each cockpit are circuit breakers protecting systems and equipment operating from the ________.
cockpit power bus
external power bus
generator bus
battery bus
The ability to control the battery using the battery control switch is _____.
permanently assigned to the front cockpit
permanently assigned to the rear cockpit
transferred automatically if either cockpit control fails
transferable between cockpits
If a component or circuit malfunction occurs, the affected circuit breaker should ___________.
illuminate to indicate the problem while shutting off electrical current flow to that component or circuit
"pop", or open, shutting off electrical current flow to that component or circuit
"click" closed and activate an aural tone
"pop", or close, maintaining electrical current flow to that component or circuit
The ______ switch must be set to ON for external power to be available in the aircraft.
avionics master
generator
auxiliary battery
battery
The battery powers select aircraft systems if the generator is not available, and provides power for _________.
the auxiliary generator
engine starts
starting the generator prior to engine start
charging the auxiliary battery
The utility light on the right console of each cockpit can be detached and relocated to the _______ for use as an area or map light.
top of the instrument panel
right canopy rail
seat side panel
canopy bow
When using the primary T-6B refueling method, the aircraft fuel system provides approximately _______ of usable fuel.
1100 gallons
1200 gallons
1100 pounds
1200 pounds
Fuel for the T-6B is stored in _______ separate tanks.
two
six
three
four
The ________ provides fuel for initial engine start and acts as a backup to the engine-driven low pressure fuel pump.
transfer jet pump
electric boost pump
primary jet pump
engine-driven high-pressure fuel pump
The ________ is located in the collector tank and ensures an uninterrupted fuel supply to the engine during inverted flight operations.
flip-flop valve
defuel valve
engine-driven low pressure fuel pump
electric boost pump
The ________ routes fuel to the _________ which controls fuel delivery to the engine.
transfer jet pumps; motive flow line unit
engine-driven high pressure fuel pump; fuel management unit
electrical boost pump; engine-driven low pressure fuel pump
primary jet pump; fuel management unit
The single point refueling system refuels _________.
the collector tank first and then gravity feeds the wing tanks
the right wing tank followed by the left wing tank
the left wing tank followed by the right wing tank
both wing tanks simultaneously
Fuel is directed to the collector tank from each wing tank by ________, keeping the collector tank pressurized.
two transfer jet pumps
the collector tank pressure pump
the electric boost pump
a primary jet pump
Fuel level sensors in each wing tank cause either right or left fuel low CAS caution messages to display whenever the fuel quantity in that tank is below ________.
50 lbs
50 gallons
110 gallons
110 lbs
The CAS warning message, FUEL PX, is activated by the ________ and indicates the fuel pressure in the motive flow line is <10 psi.
electric boost pump
high pressure switch
motive flow switch
low pressure switch
________ is measured by the fuel flow transmitter and is displayed in ________.
Inter-wing fuel transfer; pounds per second
Refueling rate; pounds per hour
Engine fuel consumption; pounds per hour
Boost pump pressure; psi
Display of the FUEL BAL message may indicate an imbalance exceeding ________ pounds for more than two minutes between the left and right fuel tanks.
10
20
30
40
The engine and propeller combine to create _________.
energy
drag
lift
thrust
What three elements are necessary for operation of the engine?
Air, oil, and fuel
Air, fuel, and heat
Air, fuel, and electricity
Oil, fuel, and heat
After combustion, the expanding gases _________.
drive the compressor turbine, which perpetuates the cycle
drive the reduction gear box
drive the reduction turbine
drive the power turbine, which perpetuates the cycle
The oil tank, accessory gearbox, battery, and starter/generator are located in the _______.
compression section
accessory compartment
power turbine section
gas generation section
What is meant by the term "free turbine"?
This is where the free air temperature is measured.
Air does not move from the compressor to the power turbine.
The “free” air stream drives the power turbine.
The compressor and power turbines are not physically connected.
During engine start, the starter turns the ______ via linkage in the accessory gearbox.
compressor
power turbine
propeller
distributor shaft
The oil system provides oil under pressure to which of the following?
Nose wheel steering
Engine-driven fuel pump and engine bearings
Engine bearings and propeller
Propeller, generator, and fuel management unit
If the oil pressure remains between 15 and 40 psi at IDLE for more than 5 seconds, _____ will be illuminated.
the yellow(amber) OIL PX message
the red OIL PX message
both the red and yellow (amber) message
neither OIL PX message
The _______ and the ________ control propeller speed to maintain a constant propeller speed of 2000 RPM and achieve varying levels of thrust by automatically adjusting propeller pitch.
fuel flow regulator; fly weights
feathering spring; regulator unit
PMU; propeller interface unit
torque probe; scavenger unit
With a loss of oil pressure to the pitch change mechanism, the ______ and ______ move the propeller to feather.
feathering spring; torque probe
airflow; counterweights
counterweights; feathering spring
airflow; feathering spring
The engine fire warning system monitors _______.
discrete engine temperature and engine oil temperature
average and discrete engine temperatures
engine oil temperature, and average and discrete engine temperatures
average engine temperature and engine oil temperature
Air for cockpit heating, canopy defogging, and cockpit pressurization is provided by _________.
recirculated engine exhaust
engine bleed air
ram intake air
compressed air tanks
With the front cockpit vent control lever set to FOOT, a control valve in each cockpit is set to divert the airflow to the ________ below the instrument panel.
electric distribution fans
floor ducts
footwarmers
cockpit side vents
The air conditioning system operates only ________.
when the engine is on and functioning, the generator is on-line, and the AIRCOND or DEFOG switch is ON
after external electrical power is disconnected, the battery is ON, and the DEFOG switch is ON
when the airplane is airborne, the generator is on-line, and the vent control lever is set to FOOT
when the engine is on and functioning, the battery is ON, and the AIR COND or DEFOG switch is ON
Controls for the defogging system are located within ________ on the environmental control panel and on the vent control panel.
the front cockpit
the rear cockpit
the ECS maintenance access bay
both cockpits
Setting the ________ switch to ON opens the bi-level flow control bypass valve (defog valve) to provide a higher volume of bleed air flow to the system.
TEMP CONTROL
DEFOG
Vent lever
AIR COND
The air conditioning system's ____ converts refrigerant vapor to a high pressure liquid.
condenser
compressor
evaporator blower
evaporator module
Cockpit pressure altitude is maintained by the control valve at _______ feet until a cockpit pressure differential of 3.6 ±0.2 psi is reached at 18,069 feet.
16,000
12,000
10,000
8000
The CAS warning message, CKPT PX, indicates the cockpit pressure differential exceeds ______ psi.
2.9 to 3.0
3.3 to 4.0
3.9 to 4.0
3.6 to 3.8
A concentrator in the OBOGS unit automatically adjusts the oxygen ________ for the current altitude based on the current cockpit pressure.
pressure
flow
temperature
concentration
Which type aircraft power must be available to open or close the canopy?
pneumatic
electrical
hydraulic
none of the above, the canopy is manually operated
The weight of the T-6B canopy is counterbalanced by ________ during opening/closing operations.
pneumatic cylinders
electrical clutches
oil-filled struts
mechanical counterweights
The canopy pressure seal activates automatically when __________.
the PCL is moved from ST READY to IDLE
bleed air inflow is available and weight is off the right main landing gear
immediately after engine start with the canopy locked
the interior canopy control handle is placed to CLOSE
When closing the canopy, a ______ indicator in the mechanical latch indicator view port indicates proper latching.
red
orange
yellow (amber)
green
The canopy fracturing system _____.
only operates when the pilot(s) eject
uses pneumatic power to eject the entire canopy frame assembly for the pilot(s) to egress
uses explosive charges to shatter canopy transparencies
uses explosive charges to shatter the forward windscreen allowing the pilot to climb out
The T-6B ejection seat is designed to provide rapid ejection capability at zero altitude and zero airspeed up to ______ feet and _____KIAS.
30,000; 300
31,000; 350
37,000; 350
35,000; 370
When flying dual, the ISS should be set to _______ to allow ________.
SOLO; either pilot to initiate dual ejections
SOLO; both pilots to initiate dual ejections
BOTH; simultaneous ejections
BOTH; either pilot to initiate dual ejections
The powered inertia retraction device _________.
secures the harness to the lap belt assembly
ensures freedom of movement by the pilot during ejection
properly positions the pilot during ejection
secures the SSK to the lap belt assembly
When should the Manual Override (MOR) Handle be used?
To manually initiate seat/pilot separation if the automatic system fails
If seat/pilot separation is desired above 14,000 feet MSL
If ejection over mountainous terrain exceeding 8000 feet MSL
All of the above are correct
The ejection seat CFS initiator activates the canopy fracturing system _________.
when the rocket motor ignites
before the seat moves
when the CFS circuit breaker is tripped
as the seat rises up the catapult rails
