SY106/107 Electrical and Fuel Systems Flashcards
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What allows isolation of electical buses?
Bus tie switch
Starter/Generator VDC and amps
Lead Acid Battery VDC
Auxiliary Battery VDC
External power receptacle VDC
28 VDC, 300 amp
24 VDC
24 VDC
28 VDC
the starter/generator is regulated and monitored by a _____ _____ _____
Generator Control Unit
Power for the generator control switch is provided by a circuit breaker labeled _______
GEN SW
What are the two primary buses (on each side of the cockpit)?
Generator Bus
Battery Bus
The rear cockpit battery bus is controlled by a circuit breaker labeled _____.
AFT BAT
Power for all avionics and radio systems in both cockpits (except backup UGH control unit and UHF transceiver) is furnished through _______________
Avionics Master Switch
What does the BUS TIE switch do if opened?
The battery and generator buses become isolated and each powers only equipment attached to that bus
To test of the Auxillary Battery, position the AUX BAT switch forward and hold for a minimum of ___ seconds
5 seconds
To use external power, the BAT switch must be set to _____
ON
Lighting controls for EFIS, RMU, AOA, and GPS are ______________________
mounted on the individual units
To activate the LDG light, the switch must be turned to ON and ______________
The gear must be down and locked
The T-6A fuel system uses 3 integral fuel tanks built into the single-piece wing to store approximately ______ pounds of fuel
1100 pounds
Fuel is fed to the engine by a _______ _______ system. This system results as fuel moves through the fuel lines creating a pressure differential between the fuel lines and fuel tanks.
Motive Flow System
A _____-_____ valve in the central collector tank supplies fuel feed during negative-G flight operations.
flip-flop
Maximum over-the-wing fuel
Maximum single point refueling fuel
1200
1100
When single point refueling is used, each wing tank can be filled to a maximum of ______ lbs each
530
Using pressurization, the tanks can be filled in approximately ___ to ___ minutes
3 to 5 minutes
Refueling shutoff is automatically controlled by the _______________ valves located on the outboard tip of each wing. These valves close when fuel reaches them which in turn cause the ___________________ valves to close.
level control pilot valves
level control shutoff valves
The aircraft can be defueled in approximately ___ minutes by applying suction through the single point adapter.
5 minutes
A manifold valve in the collector tank connects the _______ and ______ to the engine feed line.
Electric Boost Pump and the Primary Jet Pump
What are the two shutoff valves located in the engine feed line?
Maintenance Shutoff Valve
Firewall Shutoff Valve
From the fuel filter, fuel continues down the fuel line to the _____ pump and the _____ pump
Engine-Driven Low Pressure Fuel Pump
Engine-Driven High Pressure Fuel Pump
The engine-driven high pressure fuel pump routes fuel to the _____________ which controls fuel delivery to the engine
Fuel Management Unit
Fuel flows from the engine-driven high pressure fuel pump to the _____________ which sends a signal to the AEDD
Fuel Flow Transmitter
Excess fuel not used by the engine is sent from the engine-driven high pressure pump through a ____________ back to the collector tank
Purge Line
Some fuel is routed from the engine-driven low pressure fuel pump down the _____________ and used to drive the primary and transfer jet pumps
motive flow line
A _____ psi pressure switch senses fuel pressure in the motive flow line and activates the electric boost pump anytime the fuel pressure drops below ____ psi and the PCL is above the start ready position. Also illuminates the ________ annunciator.
10 psi
FUEL PX annunciator (red)
Fuel delivered by the motive flow line drives the _________ pump which then begins to deliver fuel from the collector tank to the engine-driven low pressure fuel pump.
Primary Jet Pump
As fuel is drawn from the collector tank, ______________ pumps in the wing tanks direct fuel from the wing tanks to the collector tank. This keeps the collector tank pressurized.
Transfer Jet Pumps
The Jet Pumps operate on _________ flow.
Venturi Flow
Which pump in the collector tank activates AFTER engine start?
Primary Jet Pump
There are ____ fuel level probes in the T-6A
7 fuel level probes. 3 in each wing tank, 1 in the collector tank.
The FUEL QTY arrows turn yellow when there is ______ lbs remaining in each tank
150 lbs
Fuel low level sensors, located at the rear edge of the inboard ends of the wing tanks, activate the L FUEL LO or R FUEL LO annunciators when the fuel level falls below ______ lbs in the respective tank.
110 lbs
The FUEL BAL annunciator indicates that the fuel imbalances has exceeded ___ lbs for more than ___ minutes.
30 lbs for more than 2 minutes
It also lights if a fuel probe fails
What are the 3 ways to activate the BOOST PUMP (and annunciator)?
During Startup
Manually with the BOOST PUMP switch
Activation os the low pressure switch (which also activates the FUEL PX (red) annunciator
A ______ valve installed in the vent opening at the tip end of each wing tank will close when rising fuel reaches it.
Float Valve
The Fuel balance system maintains balance within ___ lbs
20 lbs
Wing tanks are vented to each other through the _____ _____ line.
Cross Vent Line
The _____ _______ valve maintains fuel balance by shutting off fuel flow to the light wing tank.
Transfer (Solenoid) valve
What are the 3 primary functions of the Generator?*
Provides 28VDC/300 amp primary aircraft power
Operate generator bus and battery bus equipment
Charges batteries
What items are on the Hot Battery Bus?
Ram Air Valves Clocks (internal) ELT Battery Switch OBOGS EMERG FLAPS FDR MAINT
Power for aircraft avionics is supplied by which bus? *
BOTH generator and battery buses supply power to the avionics and radio
Which component prevents fuel from overflowing out of the wing?*
Float Valves
Loss of Generator Indications
MASTER WARN
GEN (red) annunciator
Engine/Systems/NACWS indications confirming generator failure
Less than 24v and amps discharging
With GEN failure and Bus Tie open, the following systems will fail*
EHSI, ASI, VSI, altimeter (primary) VHF comm and nav radios (primary) PEDD and ESND Air conditioning and blowers Speed brake, NWS and TAD Rear cockpit EFIS control panel and GPS
Inoperative Generator Bus indications
MASTER WARN and MASTER CAUT
Annunciators: GEN BUS, FUEL BAL, TAD FAIL, TAD OFF
Loss of all electronic instrument displays except EADI and AEDD
CWS circuit breaker open indications:*
MASTER WARN switchlight flashing
GEN BUS annunciator illuminates
All other indications will operate normally
Indications of a front cockpit CWS battery bus circuit breaker open:*
MASTER WARN switchlight illuminated
BAT BUS annunciator
BATTERY BUS inoperative Indications:
MASTER WARN and MASTER CAUT switchlight flashing
Annunciators lit
Failure of AOA, EADI, GPS and AEDD; front cockpit EFIS Control Panel inoperative; clock display; pressurization
Power off flags in standby ADI and standby turn and bank indicator
Fuel Probe Failure Indications
MASTER CAUT
FUEL BAL annunciator
FP FAIL will display on the AEDD
