The Trim Aid Device (TAD) assists trimming for which control surface during airspeed and power changes?
rudder trim tab position
True or false? Engine exhaust augments the thrust of the propeller
True. Exhaust gases are ejected rearward providing thrust which augments that produced by
the propeller.
Primary aircraft electrical power is provided by which component of the electrical system?
The generator function of the starter/generator.
Tuning for each of the communications and navigation radios and the transponder is provided by which component?
RMU
True or false? The VHF navigation system provides VOR, ILS, localizer and GPS capability.
False. The VHF system provides VOR, ILS, localizer, and glideslope capability
Primary navigation display is provided by which component of the Electronic Flight Instrument System (EFIS)?
EHSI
Which standby flight instruments will operate without electrical power?
The standby altimeter, airspeed indicator, the ball in the turn and bank indicator, and the magnetic compass
What component of the ejection seat provides sufficient altitude for parachute deployment?
Rocket motor
Secondary aircraft electrical power is provided by what component?
24 volt battery
Which aircraft system provides automatic temperature and pressure control?
ECS
Control of the transponder is provided by which component?
RMU
True or false?Once the engine is started, and the ignition switch is in the ON position, igniters are automatically
energized and de-energized by the PMU.
False. the igniters are energized by the ignition exciters
The PMU is located ______.
underneath the engine, in the accessory compartment
The PMU performs what functions?
maintains operating limits
processes power requests
determines available power
The PMU STATUS annunciator illuminates after landing when the PMU ______.
needs maintenance
If oil pressure remains between 15 and 40 psi at IDLE power for more than 5 seconds, ______ will be illuminated
both the amber and red OIL PX annunciators
The phase shift torque probe monitors __.
propeller speed
The PIU ______.
regulates oil pressure to the pitch change mechanism
The PMU ______.
keeps the engine and propeller within operating limits
The phase shift torque probe is located ______.
in the reduction gearbox
The EDM is located ______.
in the left avionics bay
In the event of abnormal engine operation, the primary engine data displays will warn the pilot by
changing color
The engine/systems/NACWS displays provide ______.
oil temperature, oil pressure, hydraulic pressure, NACWS traffic alerts, DC volts and DC amps
When testing the integrity of the fire warning system, you will know the system is working properly if ______ and the aural tone sounds.
the FIRE and MASTER WARN annunciators illuminate
The primary engine data display system ______.
provides each cockpit with a visual indication of engine operations
The primary engine data display provides ______.
torque, ITT, N1, NP, and IOAT
Given indications of abnormal start, what should you do?
Begin abort start procedure
What are the indications of a hot start?
High/rapidly rising ITT, lower, N1, lower NP
What are the indications of a hung start?
Slow rising ITT, lower N1, lower, NP
What are the indications of PMU failure?
Power step change, PMU FAIL annunciator, MASTER WARN light, aural tone
What are the indications of uncommanded propeller feather?
Rapid loss of power, high torque, lower NP, possible PMU FAIL/PMU STATUS annunciators, engine/airframe vibration, engine noise
What are some sensory indications of engine fire in-flight?
smoke or flames, smell oil burning, hear unusual sounds, feel engine vibration or roughness
The power turbine is driven by ______.
Expanding gases
What does FEVER stand for?
Fluctuating oil or hyd pressure, & oil temp
Excessive turbine temp
Visual indications (smoke)
Erratic engine operation
Roughness or vibration
What are the three engine sections?
Accessory compartment, gas generation section, and power turbine section
What functions are performed by the PMU?
Maintain operating limits, process power requests, control engine and propeller, provide near linear power response.
What is the purpose of the PIU?
Regulate oil pressure to the pitch change mechanism
What are some possible causes of engine failure in-flight?
FEVER, FIRE annunciator, MASTER WARNING light, aural tone
What are some possible causes of uncommanded power loss?
Engine rollback due to PMU scheduling, Oil/engine/fuel system contamination
What are some possible indications of engine fire in-flight that may be seen on the engine displays?
High ITT; Fluctuating: oil temperature and pressure, hydraulic pressure
Circuit breakers labeled FWD AVI and AFT AVI control front and rear cockpit avionics buses and are located on the front cockpit ______.
battery bus and generator bus circuit breaker panels
A circuit breaker labeled AFT BAT on the front cockpit battery bus circuit breaker panel controls the ______.
rear cockpit battery bus
Light output from the instruments, control panels, and displays can be adjusted by using dimming controls located on the ______ in each cockpit.
trim control panel
The engine-driven high-pressure fuel pump is fed from the ______.
engine-driven low pressure fuel pump
The motive flow line routes fuel to which of the following pumps?
Primary jet pump and transfer jet pumps
The collector tank is equipped with two fuel pumps for engine feed operations. Which one is used AFTER engine start?
Primary jet pump
During negative-G flight, the flip-flop valve activates, providing the engine access to fuel located in the ______.
collector tank
True or false. Once the engine is running and motive flow has been activated, the boost pump is automatically turned off by the low pressure switch.
true
The fuel system incorporates an auto balance system which maintains the fuel load in each wing tank to within ______ pounds of the other wing.
20
What is the aircraft limitation for negative-G flight?
15 sec
Which of the following maintains fuel balance by shutting off fuel flow to the light wing tank?
Transfer (solenoid) valve
The primary and transfer jet pumps are operated by ______.
venturi flow
Fuel is routed from the engine-driven fuel pump to the primary jet pump through which line?
motive flow line
The left and right fuel quantity arrows on the AEDD turn yellow when indicated fuel quantity in the respective tank is below ______.
150 lbs
During normal operation, while the bus tie is closed, which electrical buses does the generator supply?
Both generator and battery buses are powered by the generator
Power for aircraft avionics is supplied by which bus?
Both generator and battery buses supply power to avionics and radios.
Control of battery power is transferable between cockpits using what?
the battery switch.
True or false? The auxiliary battery will activate automatically upon failure of the primary battery
False. It must be activated by the auxiliary battery switch
The primary jet pump and transfer jet pumps are operated by what means?
by venturi flow generated by fuel flowing in the motive flow line.
What is indicated if the M FUEL BAL annunciator is lighted?
The fuel balance switch on the right forward switch panel has been set to MAN/RESET
True or false? The weight of fuel in the collector tank is included in the total fuel weight on the
AEDD
True. Collector tank fuel is split between the left and right fuel quantity indications.
Which component prevents fuel from draining from the wing tank?
Float valve
If tank loads are out of balance, the auto balance system stops flow to which tank?
Motive flow is halted to the light tank.
The FUEL BAL annunciator will illuminate if the fuel weight difference between the left and right tanks exceeds what figure for more than two minutes?
30 pounds
The BOOST PUMP annunciator is cycling on and off. This could be an indication of what?
Low fuel pressure
Gravity refueling adds how many total pounds to the T-6A normal capacity?
100 lbs
Which annunciator illuminates if the autobalance system has failed or if the difference in weight between the left and right tanks exceeds 30 pounds for more than two minutes?
The FUEL BAL annunciator
Which flight control electromechanical trim system(s) utilize movement of the actual primary control
surface?
Alierons
A primary purpose of the TAD system is to ______.
assist the pilot in maintaining directional trim
The TAD computes input to the rudder trim system based on ______.
engine torque, airspeed, altitude, and pitch rate
In addition to the TRIM OFF annunciator, actuating the trim interrupt button will also illuminate the ______ annunciator light.
TAD OFF
Which statement best describes the purpose of the bobweight attached to the forward control stick?
Provides higher stick forces as G-loading increases, helps prevent overstressing the airframe
What is included in the rudder control system?
Centering springs
Cables
Bellcrank
The emergency package’s manifold contains which of the following?
2 emergency extension selector valves
What is the purpose of the pressure release valve in the emergency hydraulic system?
To automatically release pressure should it reach 3500 psi
When the EHYD PX LO annunciator illuminates, it means that emergency accumulator hydraulic pressure is below ______ ± 150 psi.
2400
A red light illuminated in the landing gear selector handle indicates that the PCL is approaching IDLE, with the gear handle up, or which of the following?
The landing gear doors are not closed.
The engine-driven pump pressurizes the hydraulic system to which of the following?
3000 +- 120 psi
What is true about the power package reservoir?
A piston helps to step-down pressure to protect the pump
The primary hydraulic system’s selector manifold contains which of the following?
Electrical selector valves
The emergency package receives its pressure from which of the following?
From the emergency accumulator
The amber EHYD PX LO annunciator light means which of the following?
Pressure in the emergency accumulator is below 2400 psi ± 150
The HYDR FL LO annunciator means which of the following?
Reservoir fluid level is below 1 Qt
When the power package slide valve closes, the hydraulic pump pressure is prevented from energizing any hydraulic components except for the ______.
nose wheel steering actuator
True or false. The nose wheel steering system separate from the selector manifold
True
True or false. Emergency flap operation IS NOT available when the auxiliary battery is the only source of electrical power.
True
The _____is (are) interconnected with the elevator trim tab actuator to automatically input pitch trim to compensate for pitch effects as it is operated.
speed brake
What are the aileron trailing edge traveling limits?
20º up
11º down
How are the ailerons mass balanced and what function does this perform?
Small weights placed along the leading edge at the point where the ailerons pivot. These weights ensure the center of gravity for each aileron is at the pivot point.
What are the indications the trim disconnect switch has been selected?
TRIM OFF and TAD OFF
How is electrical power provided to operate the aileron and elevator trim system?
Through a circuit breaker placarded AIL/EL TRIM located on the battery bus
If the gust lock is installed properly, how will the control surfaces appear when they are visually
inspected?
The ailerons and rudder will be in a neutral position and the elevator will be in a nose-down position.
What component is the source of pressure for the primary hydraulic system?
The engine driven pump
What is the purpose of the emergency hydraulic system?
It provides a one-time lowering of the landing gear, main gear inboard doors and flaps.
What are the normal operating ranges for the hydraulic system pressure and fluid quantity?
Pressure at 2880-3120 psi on the Engine/Systems/NACWS display
FULL AC or FULL AD displayed on the green indicating rod in the reservoir level window
Can the flaps be operated in the event the primary hydraulic system fails?
Yes, after the landing gear has been lowered.
What are the indications of abnormal primary flight control operations?
Uncommanded pitch, roll or yaw movements, sluggish response to control inputs
What is the corrective action to take in the case of runaway trim?
Perform checklist
What are some indications of unsafe landing gear?
Indicator lights
Lack of noticeable drag
Lack of noticeable noise
AOA indexer not active
Inability to turn on landing or taxi lights
Tendency to roll (main gear)
What indicator lights would illuminate with the main landing gear full down, the nose gear still fully retracted, and the PCL above IDLE?
Two green mains, two red mains, red gear handle light
When lowering flaps using the emergency system, what two conditions might result?
The flaps might extend only partially and they can take longer to extend
What are the indications of wheel brake failure?
Inability to maintain directional control
Inability to decelerate
“Spongy” or soft brake pedal
The aircraft pulls to one side
A “ground-adjustable” trim tab is found on ______.
Alierons
What does the red light in the landing gear selector handle indicate when illuminated?
The gear doors are not closed, or the PCL is approaching IDLE with the gear handle UP.
When completing a sharp turn, how should nose wheel steering be used?
Nose wheel steering should be turned off prior to the turn since the NWS will try to limit the nose wheel castor
