C-130H Flight Engineer MQF 01Sep19 Flashcards
Operating procedures, techniques, etc., which could result in damage to equipment if not carefully followed is a __________.
a. Warning
b. Caution
c. Note
d. None of the above
Operating procedures, techniques, etc., which could result in damage to equipment if not carefully followed is a __________.
b. Caution
Normal operation of the NTS system does not commit the propeller to feather. However, a malfunctioning NTS system may completely feather the propeller or cause the engine to
a. Overtemp
b. Overspeed
c. Pitchlock
d. Stall/flameout
Normal operation of the NTS system does not commit the propeller to feather. However, a malfunctioning NTS system may completely feather the propeller or cause the engine to
d. Stall/flameout
The hydromechanical fuel control senses ________ , and varies fuel flow accordingly.
a. TIT and throttle position
b. Temperature, pressure altitude, fuel flow, and RPM
c. Engine inlet air temperature and pressure, RPM, and throttle position
d. Fuel manifold pressure, temperature, and pressure altitude
The hydromechanical fuel control senses ________ , and varies fuel flow accordingly.
c. Engine inlet air temperature and pressure, RPM, and throttle position
In most cases degradation of an individual thermocouple assembly would affect each circuit equally. The indicating signal will be lower (________ ° C) than the actual temperature experienced by each thermocouple sensing element.
a. 5 to 15
b. 3 ½ to 22
c. 3 to 7
d. 5 to 24 ½
In most cases degradation of an individual thermocouple assembly would affect each circuit equally. The indicating signal will be lower (________ ° C) than the actual temperature experienced by each thermocouple sensing element.
b. 3 ½ to 22
The Temperature Datum Control Valve switches lock a fuel correction only when they are positioned at LOCKED/LKD while the:
a. Throttle is in the temperature controlling range
b. ELECTRONIC FUEL CORRECTION lights are out
c. Airplane is within 5,000 feet of field elevation
d. Throttle is in the temperature controlling range and the fuel correction lights are out
The Temperature Datum Control Valve switches lock a fuel correction only when they are positioned at LOCKED/LKD while the:
d. Throttle is in the temperature controlling range and the fuel correction lights are out
The NTS system operates when negative torque applied to the reduction gear exceeds a predetermined value of _____________ inch-pounds.
a. 1260 (±600)
b. -1260 (±600)
c. 600 (±1200)
d. -600 (±1200)
The NTS system operates when negative torque applied to the reduction gear exceeds a predetermined value of -1,260 (±600) inch-pounds.
b. -1260 (±600)
The PROPELLER LOW OIL WARNING light and the PROP LOW OIL QUANTITY
light will illuminate when the oil quantity for any propeller drops approximately ________ below normal in the pressurized sump.
a. 4 quarts
b. 2 quarts
c. 4 gallons
d. 2 gallons
The PROPELLER LOW OIL WARNING light and the PROP LOW OIL QUANTITY
light will illuminate when the oil quantity for any propeller drops approximately ________ below normal in the pressurized sump.
b. 2 quarts
Early stage thermocouple decay may be difficult to identify, due to:
a. Limited changes in TIT, torque, or fuel flow
b. Changes in TIT and fuel flow with little torque change
c. TIT change with only small decrease in torque and fuel flow
d. No change in TIT and minimal increase in fuel flow and torque
Early stage thermocouple decay may be difficult to identify, due to:
d. No change in TIT and minimal increase in fuel flow and torque
During the landing approach, ________before the throttles are retarded should give more equal power distribution on all engines.
a. Placing the TD valve in AUTO
b. Locking the TD valve
c. Selecting null
d. Deenergizing the TD valve
During the landing approach, ________before the throttles are retarded should give more equal power distribution on all engines.
b. Locking the TD valve
In case of power failure, the crossfeed valves:
a. Hold the last deenergized position
b. Hold the last energized position
c. Are failsafe closed
d. Are failsafe open
In case of power failure, the crossfeed valves:
b. Hold the last energized position
The fuel low pressure warning light is turned on when fuel supply pressure at the point where fuel enters the engine pump falls below approximately ________ PSI.
a. 8.5
a. 15
c. 23
d. 28
The fuel low pressure warning light is turned on when fuel supply pressure at the point where fuel enters the engine pump falls below approximately ________ PSI.
a. 8.5
When operating with less than 6,000 pounds of total fuel in the main fuel tanks:
a. Place the crossfeed valve switches to OPEN for all tanks containing fuel
b. Place the boost pump switches to ON for all tanks containing fuel
c. Place the crossfeed separation valve switch to OPEN
d. All the above
When operating with less than 6,000 pounds of total fuel in the main fuel tanks:
d. All the above
The 28 volt external DC source should have a capacity of ________ amperes.
a. 100
b. 200
c. 300
d. 400
The 28 volt external DC source should have a capacity of ________ amperes.
d. 400
The battery is disconnected from all DC buses except the _______ when external DC power is being used.
a. Battery bus
b. Isolated bus
c. Essential bus
d. Battery and Isolated buses
The battery is disconnected from all DC buses except the _______ when external DC power is being used.
a. Battery bus
The engine hydraulic pump pressure warning light will illuminate whenever the pump output pressure drops below approximately 1,000 PSI or:
a. The circuit breaker opens
b. Essential DC control power is lost
c. Engine pump switch is placed in the OFF position
d. Essential AC power is lost
The engine hydraulic pump pressure warning light will illuminate whenever the pump output pressure drops below approximately 1,000 PSI or:
c. Engine pump switch is placed in the OFF position
The ADS control panel ramp and door control switch must be set to OFF, and the ramp manual control knob, above the ramp control panel, must be set at the ________ position before operating the pump switch on the ramp control panel.
a. Number 1
b. Number 2
c. 3N (neutral)
d. 6N (neutral)
The ADS control panel ramp and door control switch must be set to OFF, and the ramp manual control knob, above the ramp control panel, must be set at the ________ position before operating the pump switch on the ramp control panel.
d. 6N (neutral)
Prior to raising the ramp, ensure that:
a. Locks are retracted and manual control knob is 3N (neutral)
b. The ramp seal area and personnel are clear
c. Locks are retracted and personnel are clear
d. All ramp locks are retracted and the ramp seal area is clear
Prior to raising the ramp, ensure that:
d. All ramp locks are retracted and the ramp seal area is clear
If an individual landing gear position indicator becomes inoperative because of a faulty grounding circuit, the warning horn and warning light will indicate the position of:
a. All of the landing gear
b. The other two gear only
c. The faulty gear position indicator
d. None of the above
If an individual landing gear position indicator becomes inoperative because of a faulty grounding circuit, the warning horn and warning light will indicate the position of:
b. The other two gear only
After any full anti-skid braking operation above 130,000 pounds (aborted takeoff, engine-out/flaps-up landing, etc.), the approximate ground cooling time is ________ minutes.
a. 15
b. 45
c. 60
d. 65
After any full anti-skid braking operation above 130,000 pounds (aborted takeoff, engine-out/flaps-up landing, etc.), the approximate ground cooling time is ________ minutes.
d. 65
Elevator trim tab travel is controlled by limit switches set at ________ degrees nose down and ________ degrees nose up.
a. 6/25
b. 8/27
c. 10/30
d. 5/15
Elevator trim tab travel is controlled by limit switches set at ________ degrees nose down and ________ degrees nose up.
a. 6/25
The landing gear warning horn cannot be silenced until the landing gear is down and locked or the flap lever is retracted above ________ %.
a. 50
b. 60
c. 70
d. 80
The landing gear warning horn cannot be silenced until the landing gear is down and locked or the flap lever is retracted above ________ %.
c. 70
When the flight station air conditioning is on, the bleed air pressure indicator reads ________ than the actual pressure in the cross wing manifold.
a. 3 PSI lower
b. 3 PSI higher
c. 6 PSI lower
d. 6 PSI higher
When the flight station air conditioning is on, the bleed air pressure indicator reads ________ than the actual pressure in the cross wing manifold.
c. 6 PSI lower
Cabin differential pressure will be zero for landing. If the differential pressure is less than ________ Hg, no discomfort will be experienced if the air conditioning master switch is turned to a nonpressure position.
a. 3.1
b. 0.6
c. 1.5
d. 0.5
Cabin differential pressure will be zero for landing. If the differential pressure is less than ________ Hg, no discomfort will be experienced if the air conditioning master switch is turned to a nonpressure position.
d. 0.5
When the leading edge temperature reaches approximately ________ the overheat warning light for that area is energized and the light illuminates.
a. 180 degrees C
b. 200 degrees F
c. 190 degrees C
d. 215 degrees F
When the leading edge temperature reaches approximately ________ the overheat warning light for that area is energized and the light illuminates.
b. 200 degrees F
Four low speed ground idle buttons located on the flight control pedestal may be pushed in to reduce engine RPM to approximately __ at any time the throttles are in the range between 9-30°.
a. 92 %
b. 65%
c. 94%
d. 72%
Four low speed ground idle buttons located on the flight control pedestal may be pushed in to reduce engine RPM to approximately __ at any time the throttles are in the range between 9-30°.
d. 72%
Ensure that the secure voice system mode switch is in the ________ position to provide normal operation (plain text) of the UHF radio when secure voice is not to be used.
a. C
b. P
c. CO
d. LD
Ensure that the secure voice system mode switch is in the ________ position to provide normal operation (plain text) of the UHF radio when secure voice is not to be used.
b. P
The electrical control system of the ramp and door is inactivated when the:
a. The door is not up and locked
b. The CDS switches are in the ARM position
c. Anchor line support arms are not in the UP position
d. Anchor line support arms are not in the down position
The electrical control system of the ramp and door is inactivated when the:
c. Anchor line support arms are not in the UP position
The LAPES/CDS switches must remain _________ in the NORMAL/OFF (guarded) position except when required to be in ARM for operational check or mission requirements.
a. Closed
b. Open
c. With the guard closed
d. Safetied
The LAPES/CDS switches must remain _________ in the NORMAL/OFF (guarded) position except when required to be in ARM for operational check or mission requirements.
d. Safetied
When 100 percent oxygen is being supplied, _________ oxygen is consumed per person as altitude ________.
a. More/increases
b. Less/increases
c. Less/decreases
d. Altitude has no effect on oxygen consumption
When 100 percent oxygen is being supplied, _________ oxygen is consumed per person as altitude ________.
b. Less/increases
The normal hydraulic pressure range is based on the following conditions: 100 percent RPM, all flight controls in neutral, suction boost pumps ON, and no system actuation. Pressure as low as \_\_\_\_\_\_\_ PSI may be experienced in low speed ground idle and is acceptable as long as the normal limits are attained as specified above. A. 2,200 B. 2,250 C. 2,550 D. 2,750
The normal hydraulic pressure range is based on the following conditions: 100 percent RPM, all flight controls in neutral, suction boost pumps ON, and no system actuation. Pressure as low as _______ PSI may be experienced in low speed ground idle and is acceptable as long as the normal limits are attained as specified above.
C. 2,550
Do not enter/exit from the ________ side of the nose wheel well due to possible hazard of venting liquid oxygen.
a. Forward
b. Aft
c. Left
d. Right
Do not enter/exit from the ________ side of the nose wheel well due to possible hazard of venting liquid oxygen.
d. Right
The CVR is operational anytime the ________ bus is powered by any source other than external power.
a. Essential DC
b. Essential AC
c. Main AC
d. Battery
The CVR is operational anytime the ________ bus is powered by any source other than external power.
b. Essential AC
While visually inspecting the Halon fire extinguisher pressure gage, the needle should be in the green zone, _______ PSIG.
a. 125 +-50
b. 175+-50
c. 100+-50
d. 75+-50
While visually inspecting the Halon fire extinguisher pressure gage, the needle should be in the green zone, _______ PSIG.
a. 125 +-50
With the escape ladder installed, it is impossible to exit the airplane from the center overhead escape hatch using the ________ side of the ladder.
a. Right
b. Left
c. Aft
d. Forward
With the escape ladder installed, it is impossible to exit the airplane from the center overhead escape hatch using the ________ side of the ladder.
b. Left
In emergencies, MIL-L-7808 and MIL-L-23699 may be mixed. The amount of emergency oil added should not exceed \_\_\_\_\_\_\_\_\_\_ tank capacity. A. One-third B. Two-thirds C. One-half D. Three-quarters
In emergencies, MIL-L-7808 and MIL-L-23699 may be mixed. The amount of emergency oil added should not exceed __________ tank capacity.
C. One-half
During the BEFORE EXTERIOR INSPECTION and before any electrical power is applied to the airplane, the engineer will:
a. Ensure that all locking pins are removed from doors and hatches
b. Check the form 781
c. Ensure that all aircraft switches and circuit breakers are in their normal shutdown position
d. All of the above
During the BEFORE EXTERIOR INSPECTION and before any electrical power is applied to the airplane, the engineer will:
d. All of the above
While accomplishing the POWER ON INSPECTION, if a light in the overheat test panel fails to illuminate during testing, bleed air systems:
a. Should be pressurized after clearance from the ground
b. Should not be pressurized until proper inspection and repairs have been made
c. May be checked after entry has been recorded in the form 781
d. Will be checked, using caution and at a reduced pressure
While accomplishing the POWER ON INSPECTION, if a light in the overheat test panel fails to illuminate during testing, bleed air systems:
b. Should not be pressurized until proper inspection and repairs have been made
During the POWER ON INSPECTION, movement of the flaps is essential at this time to enable detection of ________ or malfunctions during the walk-around inspection.
a. Asymmetric flaps
b. Flap brake engagement
c. Hydraulic leaks
d. Fuel leaks
During the POWER ON INSPECTION, movement of the flaps is essential at this time to enable detection of ________ or malfunctions during the walk-around inspection.
c. Hydraulic leaks
Do not ________ or open the ground test valve if ramp hydraulic actuators are preloaded or cargo loading operations are in progress.
a. Apply hydraulic pressure
b. Check hydraulic pressure
c. Service hydraulic reservoirs
d. Deplete hydraulic pressure
Do not ________ or open the ground test valve if ramp hydraulic actuators are preloaded or cargo loading operations are in progress.
d. Deplete hydraulic pressure
Depletion of the emergency brake hydraulic system pressure with the brake select switch in normal is an indication of a(n) ________ failure.
a. Normal brake selector valve
b. Anti-skid valve
c. Emergency brake selector valve
d. Ground test valve
Depletion of the emergency brake hydraulic system pressure with the brake select switch in normal is an indication of a(n) ________ failure.
c. Emergency brake selector valve
During EXTERIOR INSPECTION, if not previously checked by maintenance, a work stand/ladder will be required to check:
a. Engine inlets
b. Exhaust areas
c. External tank caps
d. All of the above
During EXTERIOR INSPECTION, if not previously checked by maintenance, a work stand/ladder will be required to check:
d. All of the above
Normally, the quick don oxygen mask system is the _______ use equipment.
a. Preferred
b. Alternate
c. Primary
d. Emergency
Normally, the quick don oxygen mask system is the _______ use equipment.
c. Primary
After moving the condition lever to ground stop, do not move the lever from this position until ________.
a. Fuel stops dripping from the drain mast
b. Cleared by the loadmaster
c. RPM decreases below 16%
d. Engine rotation has stopped
After moving the condition lever to ground stop, do not move the lever from this position until ________.
d. Engine rotation has stopped
During low air density conditions (high temperature above approximately 28 degrees C/ high altitude), if the engine accelerates smoothly with no indication of stall and TIT limits are not exceeded, time to stabilize on speed is ________ seconds.
a. 70
b. 60
c. 55
d. 45
During low air density conditions (high temperature above approximately 28 degrees C/ high altitude), if the engine accelerates smoothly with no indication of stall and TIT limits are not exceeded, time to stabilize on speed is ________ seconds.
a. 70
The throttles must not be moved out of the ________ detent during engine starting.
a. GROUND IDLE
b. FLIGHT IDLE
c. AIR START
d. RUN
The throttles must not be moved out of the ________ detent during engine starting.
a. GROUND IDLE
If there is no positive indication of oil pressure on the engine and reduction gear by _________ % RPM, immediately discontinue the start.
a. 30
b. 35
c. 40
d. 60
If there is no positive indication of oil pressure on the engine and reduction gear by _________ % RPM, immediately discontinue the start.
b. 35
A positive hydraulic pressure indication must be noted by the time the engine is _______. Normal operating pressure should be indicated within ________ after on speed.
a. On speed/30 seconds
b. 60%/60 seconds
c. On speed/45 seconds
d. 35%50 seconds
A positive hydraulic pressure indication must be noted by the time the engine is _______. Normal operating pressure should be indicated within ________ after on speed.
a. On speed/30 seconds
If start TIT is less than _________degrees C, record in AFTO Form 781. Maintenance action is required prior to flight.
a. 780
b. 820
c. 720
d. 965
If start TIT is less than _________degrees C, record in AFTO Form 781. Maintenance action is required prior to flight.
c. 720
If auxiliary feather motor operation is not indicated for a propeller:
a. Record in form 781 and continue mission to a repair facility
b. Pull the circuit breaker for the affected motor
c. The malfunction will be corrected prior to flight
d. Fly in mechanical governing
If auxiliary feather motor operation is not indicated for a propeller:
c. The malfunction will be corrected prior to flight
When down-shifting from normal to low-speed ground idle, the engineer will monitor the engine instruments and be prepared to shut down the engine by placing the condition lever to GROUND STOP if the temperature exceeds ________ degrees C or a stall occurs.
a. 830
b. 965
c. 850
d. 865
When down-shifting from normal to low-speed ground idle, the engineer will monitor the engine instruments and be prepared to shut down the engine by placing the condition lever to GROUND STOP if the temperature exceeds ________ degrees C or a stall occurs.
c. 850
If a stop, sudden or severe braking application has occurred during turns:
a. Taxi the airplane forward approximately 5 feet
b. Record in Form 781A
c. Tow airplane out of turn
d. No action required
If a stop, sudden or severe braking application has occurred during turns:
b. Record in Form 781A
The use of brakes during reverse taxiing should be ________ to prevent the airplane from setting on the tail.
a. Accomplished
b. Avoided
c. Considered
d. Coordinated by both pilots
The use of brakes during reverse taxiing should be ________ to prevent the airplane from setting on the tail.
b. Avoided
Do not hold the ice detector TEST switch in the No. 2 or No. 3 position longer than five seconds. The test cycle may be repeated once, but then wait ________ minutes for the ice detector to cool before performing this test again.
a. Five
b. Four
c. Three
d. Two
Do not hold the ice detector TEST switch in the No. 2 or No. 3 position longer than five seconds. The test cycle may be repeated once, but then wait ________ minutes for the ice detector to cool before performing this test again.
a. Five
With engines running, never operate the propeller anti-icing or de-icing system for more than ________ cycles while the airplane is on the ground.
a. Five
b. Four
c. Three
d. Two
With engines running, never operate the propeller anti-icing or de-icing system for more than ________ cycles while the airplane is on the ground.
d. Two
If the BLADE DE-ICING ammeter falls below________, do not fly into icing conditions.
a. 65 volts
b. 90 amperes
c. 65 amperes
d. 90 volts
If the BLADE DE-ICING ammeter falls below________, do not fly into icing conditions.
c. 65 amperes
Observe engine torque and TIT when placing each ________ switch in the ON position when accomplishing the Before Takeoff checklist.
a. ENGINE INLET AIR DUCT ANTI-ICING
b. PROPELLER ICE CONTROL
c. NESA
d. PITOT HEAT
Observe engine torque and TIT when placing each ________ switch in the ON position when accomplishing the Before Takeoff checklist.
a. ENGINE INLET AIR DUCT ANTI-ICING
Main tank boost pump switches ________ be turned off in-flight unless directed by a specific procedure in the flight manual.
a. May
b. Should
c. Will
d. Will not
Main tank boost pump switches ________ be turned off in-flight unless directed by a specific procedure in the flight manual.
d. Will not
Above crossover, if the engine instruments are not similar in ________, with throttles aligned, a propulsion system malfunction may exist.
a. RPM, fuel flow, or torque
b. RPM, TIT, or torque
c. Fuel flow, TIT, or oil pressure
d. Fuel flow, TIT, or torque
Above crossover, if the engine instruments are not similar in ________, with throttles aligned, a propulsion system malfunction may exist.
d. Fuel flow, TIT, or torque
On airplanes modified by TO 1C-130-2098, with brakes fully applied and engines at maximum power, forward movement may occur at a constant rate of ______ or less, and is acceptable.
a. 1 foot/second
b. 1 foot/minute
c. 5 foot/second
d. 5 foot/minute
On airplanes modified by TO 1C-130-2098, with brakes fully applied and engines at maximum power, forward movement may occur at a constant rate of ______ or less, and is acceptable.
a. 1 foot/second
Never place the throttles in the TAKEOFF position without monitoring the ________, since it is possible to exceed the maximum allowable torque.
a. TIT indicators
b. Torque meters
c. Fuel flow
d. RPM gages
Never place the throttles in the TAKEOFF position without monitoring the ________, since it is possible to exceed the maximum allowable torque.
b. Torque meters
The minimum flap retraction speed for a maximum effort takeoff is:
a. Obstacle clearance speed
b. Obstacle clearance speed plus 5 knots
c. Obstacle clearance speed plus 10 knots
d. Obstacle clearance speed plus 20 knots
The minimum flap retraction speed for a maximum effort takeoff is:
c. Obstacle clearance speed plus 10 knots
If performance is critical and a takeoff with brake creep is unacceptable, engine power may be checked symmetrically (e.g. outboard engines checked with inboards at ground idle, inboards checked with outboards at ground idle) before advancing all engines towards maximum power.
A. True
B. False
If performance is critical and a takeoff with brake creep is unacceptable, engine power may be checked symmetrically (e.g. outboard engines checked with inboards at ground idle, inboards checked with outboards at ground idle) before advancing all engines towards maximum power.
A. True
For GCAS ESCAPE during night/IMC En route. If required, rotate the airplane to maintain a maximum climb angle (flaps up: no less than 160 KIAS, flaps 50% or 100%: no slower than 130 KIAS).
a. 160/130
b. 150/120
c. flaps-up approach/obstacle clearance
d. max effort obstacle clearance/obstacle clearance
For GCAS ESCAPE during night/IMC En route. If required, rotate the airplane to maintain a maximum climb angle (flaps up: no less than 160 KIAS, flaps 50% or 100%: no slower than 130 KIAS).
a. 160/130
New TOLD will be required any time gross weight changes 5,000 pounds or more, outside temperature changes ________ degrees C or more, or pressure altitude changes 1,000 feet or more.
a. 20
b. 15
c. 10
d. 5
New TOLD will be required any time gross weight changes 5,000 pounds or more, outside temperature changes ________ degrees C or more, or pressure altitude changes 1,000 feet or more.
d. 5
Higher than normal ________ system pressure may be encountered in-flight.
a. Normal brake
b. Emergency brake
c. Utility
d. Booster
Higher than normal ________ system pressure may be encountered in-flight.
b. Emergency brake
At high airspeeds, abrupt movement of the throttles into the ground range could result in:
a. Pitchlock
b. Power-loss/bog-down
c. None of the above
d. All of the above
At high airspeeds, abrupt movement of the throttles into the ground range could result in:
a. Pitchlock
Do not downspeed the engines when taxi speed, wind, or a combination of the two exceeds 30 knots. Damage to the safety coupling could occur.
a. 20
b. 30
c. 40
d. 50
Do not downspeed the engines when taxi speed, wind, or a combination of the two exceeds 30 knots. Damage to the safety coupling could occur.
b. 30
If severe wind shear is encountered on final and a recovery is flown, the navigator/engineer will monitor and call out ___________________.
a. Engine instruments and airspeed
b. Terrain clearance and traffic deconfliction
c. Radar Altimeter
d. Sink rate (VVI/VSI) and airspeed as appropriate
If severe wind shear is encountered on final and a recovery is flown, the navigator/engineer will monitor and call out ___________________.
c. Radar Altimeter
The only sound response when severe wind shear is encountered during an approach is an immediate decision to _______________
a. Execute a go around
b. Depressurize the airplane and position the AIR COND master switch to AUX VENT
c. Notify the OG/CC
d. Check RPM for overspeed, underspeed, or fluctuation
The only sound response when severe wind shear is encountered during an approach is an immediate decision to _______________
a. Execute a go around
During landing, at the first indication of directional control difficulties during reversing, immediately:
a. Shut down the affected engine
b. Return all throttles to GROUND IDLE
c. Return all throttles to FLIGHT IDLE
d. Return throttle of affected engine to GROUND IDLE
During landing, at the first indication of directional control difficulties during reversing, immediately:
b. Return all throttles to GROUND IDLE
The nose gear must be on the ground prior to _________.
a. Entering ground range
b. Reversing
c. Coming out of flight idle
d. Going to ground stop
The nose gear must be on the ground prior to _________.
b. Reversing
When moving the flaps at low airspeed, an asymmetrical flap may go undetected until near or above ___________.
a. Rotation speed
b. VMCG
c. VMCA
d. Takeoff speed
When moving the flaps at low airspeed, an asymmetrical flap may go undetected until near or above ___________.
d. Takeoff speed
If a go-around is accomplished, retracting flaps from 100 to 50 percent will:
a. Decrease sink rate
b. Increase sink rate
c. Decrease stall speed
d. Increase stall speed
If a go-around is accomplished, retracting flaps from 100 to 50 percent will:
d. Increase stall speed
The flight engineer should monitor engine instruments during shutdown for:
a. TIT and RPM decrease and NTS lights
b. Zero fuel flow and TIT and RPM decrease
c. Zero fuel flow and TIT and torque decrease
d. Zero fuel flow and TIT decrease and NTS lights
The flight engineer should monitor engine instruments during shutdown for:
b. Zero fuel flow and TIT and RPM decrease
If NTS advisory lights do not illuminate when shutting down engines from low-speed ground idle:
a. Do nothing, this is normal
b. A recheck of the NTS system must be made before the next flight
c. Record in the AFTO 781
d. Restart the engine and shutdown in Normal Ground Idle
If NTS advisory lights do not illuminate when shutting down engines from low-speed ground idle:
b. A recheck of the NTS system must be made before the next flight
Regardless of specific emergency encountered:
a. Maintain airplane control
b. Analyze the situation
c. Take coordinated corrective action
d. All the above
Regardless of specific emergency encountered:
d. All the above
When pulling the condition lever to FEATHER, pull it all the way to the detent to assure that the propeller is fully feathered when the engine fuel is shut off. If the lever is left at a mid-position, and NTS is inoperative, a(n)
a. Immediate loss of controlled flight could be possible
b. Pitchlock of the propeller is possible
c. Engine decoupling is possible
d. Propeller overspeed is possible
When pulling the condition lever to FEATHER, pull it all the way to the detent to assure that the propeller is fully feathered when the engine fuel is shut off. If the lever is left at a mid-position, and NTS is inoperative, a(n)
c. Engine decoupling is possible
If on crossfeed during the ENGINE SHUTDOWN PROCEDURE, ________ before
shutting off the fuel boost pump and closing the crossfeed valve for the affected engine.
a. Ensure all boost pump switches are OFF and tank to engine operation
b. Ensure all boost pump switches are ON
c. Ensure source of fuel to operate engines
d. Open bypass valve and cross-feed separation valve
If on crossfeed during the ENGINE SHUTDOWN PROCEDURE, ________ before
shutting off the fuel boost pump and closing the crossfeed valve for the affected engine.
c. Ensure source of fuel to operate engines
If cabin pressure increases at an excessive rate and cannot be reduced by normal means then:
a. Immediately shut off engine bleed air, one at a time, until the rate of pressure increase is at a safe value
b. Control pressure by using engine bleed air as necessary to vary the amount of conditioned air supplied for pressurization
c. If necessary for further control when descending, one of the air conditioning systems can be shut down to expedite depressurization of the airplane
d. All the above
If cabin pressure increases at an excessive rate and cannot be reduced by normal means then:
d. All the above
If either the left or right wheel well overheat light illuminates after takeoff and the condition persists after isolation procedures have been accomplished, it may be indicative of:
a. Overheated tires
b. Overheated brakes
c. Failed APU control valve
d. A failed cargo compartment control valve
If either the left or right wheel well overheat light illuminates after takeoff and the condition persists after isolation procedures have been accomplished, it may be indicative of:
b. Overheated brakes
- The correct procedure for high TIT on the ground is:
A. Move all throttles to GROUND IDLE and follow the Engine Shutdown Procedure
B. Place the affected engine condition lever to GROUND STOP
C. Retard the throttle toward GROUND IDLE, and place the temp datum control valve switch to the NULL position. If this fails to eliminate the over temperature condition, place condition lever to GROUND STOP
D. None of the above
- The correct procedure for high TIT on the ground is:
C. Retard the throttle toward GROUND IDLE, and place the temp datum control valve switch to the NULL position. If this fails to eliminate the over temperature condition, place condition lever to GROUND STOP
If a tailpipe fire occurs in-flight, follow the ENGINE SHUTDOWN PROCEDURE. If the fire persists:
a. Isolate the affected wing
b. Discharge the fire bottle on command of the pilot
c. The airplane should be accelerated as rapidly as possible, not exceeding maximum airspeed
d. All the above
If a tailpipe fire occurs in-flight, follow the ENGINE SHUTDOWN PROCEDURE. If the fire persists:
c. The airplane should be accelerated as rapidly as possible, not exceeding maximum airspeed
If a turbine overheat occurs in-flight:
A. Retard the throttle toward FLIGHT IDLE. If the condition persists, proceed with the ENGINE SHUTDOWN PROCEDURE
B. Retard the throttle toward FLIGHT IDLE, TD switch to NULL. If the warning light persists follow the ENGINE SHUTDOWN PROCEDURE
C. Place the affected engine TD switch to NULL. If the overheat is corrected place the TD switch to locked
D. Perform the ENGINE SHUTDOWN PROCEDURE
If a turbine overheat occurs in-flight:
A. Retard the throttle toward FLIGHT IDLE. If the condition persists, proceed with the ENGINE SHUTDOWN PROCEDURE
During GROUND EVACUATION; if pyrotechnics are loaded on the airplane, evacuate a minimum of ______ feet from the airplane.
a. 300
b. 400
c. 500
d. 600
During GROUND EVACUATION; if pyrotechnics are loaded on the airplane, evacuate a minimum of ______ feet from the airplane.
d. 600
If a main wheel well fire exists or hot brakes are suspected and conditions require personnel to be close to an overheated wheel or tire assembly, the approach should be from the ______ only.
a. quickest route
b. upwind direction
c. side
d. fore or aft
If a main wheel well fire exists or hot brakes are suspected and conditions require personnel to be close to an overheated wheel or tire assembly, the approach should be from the ______ only.
d. fore or aft
If aborting for a propeller malfunction or any other malfunction which could result in asymmetric power causing directional control problems when the throttles are placed in the ground range, shut down the affected engine while throttle is in:
a. FLIGHT IDLE
b. GROUND IDLE
c. TAKEOFF
d. REVERSE
If aborting for a propeller malfunction or any other malfunction which could result in asymmetric power causing directional control problems when the throttles are placed in the ground range, shut down the affected engine while throttle is in:
a. FLIGHT IDLE
For malfunctions which result in asymmetric thrust, the airplane will attempt to ________ the malfunctioning power plant during airplane acceleration.
A. Turn away from
B. Turn toward
C. Remain on runway centerline instead of turning into
D. Accelerate to Vmcg before turning toward
For malfunctions which result in asymmetric thrust, the airplane will attempt to ________ the malfunctioning power plant during airplane acceleration.
B. Turn toward
For a takeoff continued after engine failure, flap retraction should be accomplished in ______ percent increments with airspeed increasing approximately ________ knots between retraction increments.
a. 5, 5
b. 5, 10
c. 10, 5
d. 10, 10
For a takeoff continued after engine failure, flap retraction should be accomplished in ______ percent increments with airspeed increasing approximately ________ knots between retraction increments.
c. 10, 5
In all combinations of two engine failures, monitor ________ to keep it within the range of available output.
a. Hydraulic system pressures
b. Pressurization system
c. Emergency brake system
d. Generator loading
In all combinations of two engine failures, monitor ________ to keep it within the range of available output.
d. Generator loading
Two-engine operation above ________ pounds gross weight or at high density altitude is marginal.
a. 110,000
b. 115,000
c. 120,000
d. 125,000
Two-engine operation above ________ pounds gross weight or at high density altitude is marginal.
c. 120,000
If a propeller malfunction occurs after refusal speed and there is no indication of fire, it is recommended that the engine be allowed to run until at least ________ is reached.
Ref: TO 1C-130 H/K-1 Pg: 3A-22, 3A-21 Chap: 3 Para: Note
a. One-engine inoperative air minimum control speed
b. Two-engine inoperative air minimum control speed
c. 400 feet AGL
d. 150 KTAS
If a propeller malfunction occurs after refusal speed and there is no indication of fire, it is recommended that the engine be allowed to run until at least ________ is reached.
Ref: TO 1C-130 H/K-1 Pg: 3A-22, 3A-21 Chap: 3 Para: Note
b. Two-engine inoperative air minimum control speed
During pitchlocked propeller operation, the engine should be shutdown when:
a. Reaching 150 KTAS
b. 96% RPM cannot be maintained with the throttles
c. Reaching a suitable landing area
d. All of the above
During pitchlocked propeller operation, the engine should be shutdown when:
d. All of the above
If a propeller fails to feather in flight, it is critical to restore oil to the ________ of the windmilling propeller as soon as possible.
a. Engine section
b. Turbine section
c. Reduction gearbox
d. All the above
If a propeller fails to feather in flight, it is critical to restore oil to the ________ of the windmilling propeller as soon as possible.
c. Reduction gearbox
For PROPELLER BRAKE FAILURE; if the propeller does counter-rotate, and the procedures are ineffective:
a. Land as soon as possible
b. Land as soon as practical
c. Continue the flight with caution
d. Record in 781, maintenance action required
For PROPELLER BRAKE FAILURE; if the propeller does counter-rotate, and the procedures are ineffective:
b. Land as soon as practical
If throttle control cable failure is suspected, do not move the throttle prior to engine shutdown. To do so could cause:
a. The engine to stall or flameout
b. The propeller to be inadvertently feathered
c. The pitchlock mechanism to disengage
d. The propeller to go into reverse pitch or to full power
If throttle control cable failure is suspected, do not move the throttle prior to engine shutdown. To do so could cause:
d. The propeller to go into reverse pitch or to full power
Any time an IGNITION CONTROL circuit breaker is pulled on an inboard engine, the ________ for that engine is inoperative.
a. Propeller de-icing system
b. Propeller anti-icing system
c. Engine inlet anti-icing system
d. Ice detection system
Any time an IGNITION CONTROL circuit breaker is pulled on an inboard engine, the ________ for that engine is inoperative.
d. Ice detection system
A sheared shaft on the speed sensitive control with the throttle above 65 degrees travel may be indicated by:
a. Momentary illumination of the SECONDARY FUEL PUMP PRESSURE light
b. ELECTRONIC FUEL CORRECTION light
c. TIT will not exceed start limiting temperature of 830 degrees C
d. All the above
A sheared shaft on the speed sensitive control with the throttle above 65 degrees travel may be indicated by:
d. All the above
In case of loss of oil pressure:
a. Check the oil pressure indicator fuse
b. Shut down the engine in accordance with the Engine Shutdown Procedure
c. Shut down the engine by using Cruise Engine Shutdown Procedure
d. Placed the AC Instrument and Engine Fuel Control inverter switch to the DC position
In case of loss of oil pressure:
b. Shut down the engine in accordance with the Engine Shutdown Procedure
