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250 Cards in this Set
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1. Operating procedures, techniques, etc., which could result in damage to equipment if not carefully followed is a________.
Ref: TO 1C-130 E/H/K-1 Pg: viii, vii, xv A. Warning B. Caution C. Note D. None of the above |
B
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2. 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:
Ref: TO 1C-130 E/H/K-1-1 Pg: 1B-3,1B-3,1B-4 Chap: 1B Para: NOTE A. Overtemp B. Overspeed C. Pitchlock D. Stall/flameout |
D
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3. The hydromechanical fuel control senses ________ , and varies fuel flow accordingly.
Ref: TO 1C-130 E/H/K-1 Pg: 1B-4,1B-4,1B-5 Chap: 1B A. Turbine inlet temperature 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 |
C
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4. 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.
Ref: TO 1C-130 E/H/K-1 Pg: 1B-6,1B-6,1B-6 Chap: 1B A. 5 to 15 B. 3 ½ to 22 C. 3 to 7 D. 5 to 24 ½ |
B
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5. The Temperature Datum Control Valve switches lock a fuel correction only when they are positioned at LOCKED/LKD while the:
Ref: TO 1C-130 E/H/K-1 Pg: 1B-9,1B-9,1B-10 Chap: 1B Para: NOTE 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 |
D
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6. The engine low oil quantity warning light illuminates when an oil tank quantity level drops to approximately:
Ref: TO 1C-130 E/H/K-1 Pg: 1B-11,1B-12,1B-15 Chap: 1B A. 4 quarts B. 4 gallons C. 6 quarts D. 6 gallons |
B
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7. 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.
Ref: TO 1C-130 E/H/K-1 Pg: 1B-13,1B-12,1B-18 Chap: 1B A. 4 quarts B. 2 quarts C. 4 gallons D. 2 gallons |
B
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8. Early stage thermocouple decay may be difficult to identify, due to:
Ref: TO 1C-130 E/H/K-1 Pg: 1B-16,1B-16,1B-21 Chap: 1B Para: NOTE A. Limited changes in turbine inlet temperature, torque, or fuel flow B. Changes in turbine inlet temperature and fuel flow with little torque change C. Turbine inlet temperature change with only small decrease in torque and fuel flow D. No change in turbine inlet temperature and minimal increase in fuel flow and torque |
D
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9. During the landing approach, ________before the throttles are retarded should give more equal power distribution on all engines.
Ref: TO 1C-130 E/H/K-1 Pg: 1B-18,1B-18,1B-23 Chap: 1B A. Placing the TD valve in AUTO B. Locking the TD valve C. Selecting null D. Deenergizing the TD valve |
B
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10. In case of power failure, the crossfeed valves:
Ref: TO 1C-130 E/H/K-1 Pg: 1D-4,1D-3,1D-4 Chap: 1D A. Hold the last deenergized position B. Hold the last energized position C. Are failsafe closed D. Are failsafe open |
B
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11. 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.
Ref: TO 1C-130 E/H/K-1 Pg: 1D-6,1D-6,1D-7 Chap: 1D A. 8.5 B. 15 C. 23 D. 28 |
A
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12. When operating with less than 6,000 pounds of total fuel in the main fuel tanks:
Ref: TO 1C-130 E/H/K-1 Pg: 1D-11,1D-9,1D-10 Chap: 1D Para: CAUTION 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 |
D
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13. The 28 volt external DC source should have a capacity of ________ amperes.
Ref: TO 1C-130 E/H/K-1 Pg: 1F-3, 1F-3, 1F-3 Chap: 1F Para: NOTE A. 100 B. 200 C. 300 D. 400 |
D
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14. The battery is disconnected from all DC buses except the _______ when external DC power is being used.
Ref: TO 1C-130 E/H/K-1 Pg: 1F-3,1F-3,1F-3 Chap: 1F A. Battery bus B. Isolated bus C. Essential bus D. Battery and Isolated buses |
A
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15. The engine hydraulic pump pressure warning light will illuminate whenever the pump output pressure drops below approximately 1,000 PSI or:
Ref: TO 1C-130 E/H/K-1 Pg: 1G-2,1G-2,1G-2 Chap: 1G 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 |
C
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16. 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.
Ref: TO 1C-130 E/H/K-1 Pg: 1G-7,1G-7,1G-8 Chap: 1G Para: WARNING A. Number 1 B. Number 2 C. 3N (neutral) D. 6N (neutral) |
D
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17. Prior to raising the ramp, ensure that:
Ref: TO 1C-130 E/H/K-1 Pg: 1G-7,1G-7,1G-8 Chap: 1G Para: CAUTION 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 |
D
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18. 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:
Ref: TO 1C-130 E/H/K-1 Pg: 1G-13,1G-12,1G-14 Chap: 1G Para: NOTE A. All of the landing gear B. The other two gear only C. The faulty gear position indicator D. None of the above |
B
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19. 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.
Ref: TO 1C-130 E/H/K-1 Pg: 1G-17,1G-16,1G-19 Chap: 1G Para: WARNING A. 15 B. 45 C. 60 D. 65 |
D
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20. Elevator trim tab travel is controlled by limit switches set at ________ degrees nose down and ________ degrees nose up.
Ref: TO 1C-130 E/H/K-1 Pg: 1H-5,1H-5,1H-5 Chap: 1H Para: NOTE A. 6/25 B. 8/27 C. 10/30 D. 5/15 |
A
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21. The landing gear warning horn cannot be silenced until the landing gear is down and locked or the flap lever is retracted above ________ %.
Ref: TO 1C-130 E/H/K-1 Pg: 1H-6,1H-6,1H-6 Chap: 1H Para: NOTE A. 50 B. 60 C. 70 D. 80 |
C
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22. When the flight station air conditioning is on, the bleed air pressure indicator reads ________ than the actual pressure in the cross wing manifold.
Ref: TO 1C-130 E/H/K-1 Pg: 1J-2,1J-2,1J-2 Chap: 1J Para: NOTE A. 3 PSI lower B. 3 PSI higher C. 6 PSI lower D. 6 PSI higher |
C
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23. 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.
Ref: TO 1C-130 E/H/K-1 Pg: 1J-10,1J-11,1J-12 Chap: 1J Para: NOTE A. 3.1 B. 0.6 C. 1.5 D. 0.5 |
D
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24. When the leading edge temperature reaches approximately ________ the overheat warning light for that area is energized and the light illuminates.
Ref: TO 1C-130 E/H/K-1 Pg: 1K-1,1K-2,1K-2 Chap: 1K A. 180 degrees C B. 200 degrees F C. 190 degrees C D. 215 degrees F |
B
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25. In any airplane configuration that could limit the normal climb capability of the airplane (such as engine out, ramp door open, etc) or operational situation where an RA maneuver is prohibited, the TCAS should be placed in:
Ref: TO 1C-130 E/H/K-1 Pg: 1M-11,1M-8,1M-11 Chap: 1M Para: WARNING A. NORM mode B. STBY mode C. TA ONLY D. Either A or C |
D
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26. 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.
Ref: TO 1C-130 E/H/K-1 Pg: 1R-7,1R-6,1R-8 Chap: 1R Para: NOTE A. C B. P C. CO D. LD |
B
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27. The electrical control system of the ramp and door is inactivated when the:
Ref: TO 1C-130 E/H/K-1 Pg: 1S-25,1S-22,1S-24 Chap: 1S Para: Caution 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 |
C
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28. 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.
Ref: TO 1C-130 E/H/K-1 Pg: 1S-26,1S-21,1S-25 Chap: 1S Para: Caution A. Closed B. Open C. With the guard closed D. Safetied |
D
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29. When 100 percent oxygen is being supplied, _________ oxygen is consumed per person as altitude ________.
Ref: TO 1C-130 E/H/K-1 Pg: 1T-1,1T-2,1T-1 Chap: 1T Para: Note A. More/increases B. Less/increases C. Less/decreases D. Altitude has no effect on oxygen consumption |
B
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30. The AERP system ________ protect the user against ammonia fumes or carbon monoxide gas and _______ be used without an oxygen source in an oxygen deficient atmosphere.
Ref: TO 1C-130 E/H/K-1 Pg: 1T-6,1T-5,1T-6 Chap: 1T Para: Warning A. Will, shall B. Will not, shall C. Will not, shall not D. Will, shall not |
C
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31. Do not enter/exit from the ________ side of the nose wheel well due to possible hazard of venting liquid oxygen.
Ref: TO 1C-130 E/H/K-1 Pg: 1T-7,1T-6,1T-7 Chap: 1T Para: Warning A. Forward B. Aft C. Left D. Right |
D
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32. The CVR is operational anytime the ________ bus is powered by any source other than external power.
Ref: TO 1C-130 E/H/K-1 Pg: 1U-7,1U-7,1U-12 Chap: 1U A. Essential DC B. Essential AC C. Main AC D. Battery |
D
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33. The high pressure of the Halon fire extinguisher can spread a class ________ fire.
Ref: TO 1C-130 E/H/K-1 Pg: 1V-1,1V-1,1V-1 Chap: 1V Para: Caution A. A B. B C. C D. All the above |
A
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34. With the escape ladder installed, it is impossible to exit the airplane from the center overhead escape hatch using the ________ side of the ladder.
Ref: TO 1C-130 E/H/K-1 Pg: 1V-3,1V-3,1V-4 Chap: 1V Para: Warning A. Right B. Left C. Aft D. Forward |
B
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35. In emergencies, MIL-L-7808 and MIL-L-23699 may be mixed. The amount of emergency oil added should not exceed ________ tank capacity.
Ref: TO 1C-130 E/H/K-1 Pg: 1Z-4,1Z-2,1Z-4 Chap: 1Z Para: Delta 2 A. One-third B. Two-thirds C. One-half D. Three-quarters |
C
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36. During the BEFORE EXTERIOR INSPECTION and before any electrical power is applied to the airplane, the engineer will:
Ref: TO 1C-130 E/H/K-1 Pg: 2-5,2-4, 2-5 Chap: 2 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 |
D
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37. While accomplishing the POWER ON INSPECTION, if a light in the overheat test panel fails to illuminate during testing, bleed air systems:
Ref: TO 1C-130 E/H/K-1 Pg: 2-15,2-13,2-14 Chap: 2 Para: Caution 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 |
B
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38. 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.
Ref: TO 1C-130 E/H/K-1 Pg: 2-19,2-20,2-21 Chap: 2 Para: Note A. Asymmetric flaps B. Flap brake engagement C. Hydraulic leaks D. Fuel leaks |
C
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39. Do not ________ or open the ground test valve if ramp hydraulic actuators are preloaded or cargo loading operations are in progress.
Ref: TO 1C-130 E/H/K-1 Pg: 2-18,2-19,2-20 Chap: 2 Para: Warning A. Apply hydraulic pressure B. Check hydraulic pressure C. Service hydraulic reservoirs D. Deplete hydraulic pressure |
D
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40. Depletion of the emergency brake hydraulic system pressure with the brake select switch in normal is an indication of a(n) ________ failure.
Ref: TO 1C-130 E/H/K-1 Pg: 2-23,2-27,2-24 Chap: 2 Para: Caution A. Normal brake selector valve B. Anti-skid valve C. Emergency brake selector valve D. Ground test valve |
C
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41. During EXTERIOR INSPECTION, if not previously checked by maintenance, a work stand/ladder will be required to check:
Ref: TO 1C-130 E/H/K-1 Pg: 2-30,2-33,2-30 Chap: 2 A. Engine inlets B. Exhaust areas C. External tank caps D. All of the above |
D
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42. Normally, the quick don oxygen mask system is the _______ use equipment.
Ref: TO 1C-130 E/H/K-1 Pg: 2-44,2-43,2-45 Chap: 2 Para: Note A. Preferred B. Alternate C. Primary D. Emergency |
C
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43. After moving the condition lever to ground stop, do not move the lever from this position until ________.
Ref: TO 1C-130 E/H/K-1 Pg: 2-48,2-48,2-48 Chap: 2 Para: Caution A. Fuel stops dripping from the drain mast B. Cleared by the loadmaster C. RPM decreases below 16% D. Engine rotation has stopped |
D
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44. 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 turbine inlet temperature limits are not exceeded, time to stabilize on speed is ________ seconds.
Ref: TO 1C-130 E/H/K-1 Pg: 2-48,2-48,2-48 Chap: 2 Para: Note A. 70 B. 60 C. 55 D. 45 |
A
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45. The throttles must not be moved out of the ________ detent during engine starting.
Ref: TO 1C-130 E/H/K-1 Pg: 2-47,2-47,2-48 Chap: 2 Para: Caution A. GROUND IDLE B. FLIGHT IDLE C. AIR START D. RUN |
A
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46. If there is no positive indication of oil pressure on the engine and reduction gear by _________ % RPM, immediately discontinue the start.
Ref: TO 1C-130 E/H/K-1 Pg: 2-49,2-49,2-50 Chap: 2 Para: Caution A. 30 B. 35 C. 40 D. 60 |
B
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47. A positive hydraulic pressure indication must be noted by the time the engine is _______. Normal operating pressure should be indicated within ________ after on speed.
Ref: TO 1C-130 E/H/K-1 Pg: 2-49,2-50,2-50 Chap: 2 Para: Note A. On speed / 30 seconds B. 60% / 60 seconds C. On speed / 45 seconds D. 35% / 50 seconds |
A
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48. If start turbine inlet temperature is less than _________degrees C, record in AFTO Form 781. Maintenance action is required prior to flight.
Ref: TO 1C-130 E/H/K-1 Pg: 2-50,2-50,2-51 Chap: 2 Para: Warning A. 780 B. 820 C. 720 D. 965 |
C
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49. If auxiliary feather motor operation is not indicated for a propeller:
Ref: TO 1C-130 E/H/K-1 Pg: 2-53,2-54,2-54 Chap: 2 Para: Warning 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 |
C
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50. 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.
Ref: TO 1C-130 E/H/K-1 Pg: 2-56,2-57,2-58 Chap: 2 Para: Caution A. 830 B. 965 C. 850 D. 865 |
C
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51. If a stop, sudden or severe braking application has occurred during turns:
Ref: TO 1C-130 E/H/K-1 Pg: 2-57,2-58,2-59 Chap: 2 Para: Caution A. Taxi the airplane forward approximately 5 feet B. Record in Form 781A C. Tow airplane out of turn D. No action required |
B
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52. The use of brakes during reverse taxiing should be ________ to prevent the airplane from setting on the tail.
Ref: TO 1C-130 E/H/K-1 Pg: 2-58,2-59,2-59 Chap: 2 Para: Caution A. Accomplished B. Avoided C. Considered D. Coordinated by both pilots |
B
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53. 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.
Ref: TO 1C-130 E/H/K-1 Pg: 2-59,2-60,2-61 Chap: 2 Para: Caution A. Five B. Four C. Three D. Two |
A
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54. With engines running, never operate the propeller anti-icing or de-icing system for more than ________ cycles while the airplane is on the ground.
Ref: TO 1C-130 E/H/K-1 Pg: 2-59,2-61,2-61 Chap: 2 Para: Caution A. Five B. Four C. Three D. Two |
D
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55. If the BLADE DE-ICING ammeter falls below________, do not fly into icing conditions.
Ref: TO 1C-130 E/H/K-1 Pg: 2-60,2-62,2-62 Chap: 2 Para: Warning A. 65 volts B. 90 amperes C. 65 amperes D. 90 volts |
C
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56. Observe engine torque and turbine inlet temperature when placing each ________ switch in the ON position when accomplishing the Before Takeoff checklist.
Ref: TO 1C-130 E/H/K-1 Pg: 2-65,2-67,2-67 Chap: 2 Para: Note A. ENGINE INLET AIR DUCT ANTI-ICING B. PROPELLER ICE CONTROL C. NESA D. PITOT HEAT |
A
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57. Main tank boost pump switches ________ be turned off in-flight unless directed by a specific procedure in the flight manual.
Ref: TO 1C-130 E/H/K-1 Pg: 2-65,2-68,2-67 Chap: 2 Para: Warning A. May B. Should C. Will D. Will not |
D
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58. Above crossover, if the engine instruments are not similar in ________, with throttles aligned, a propulsion system malfunction may exist.
Ref: TO 1C-130 E/H/K-1 Pg: 2-67,2-71,2-69 Chap: 2 Para: Warning A. RPM, fuel flow, or torque B. RPM, turbine inlet temperature, or torque C. Fuel flow, turbine inlet temperature, or oil pressure D. Fuel flow, turbine inlet temperature, or torque |
D
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59. If indicated torque exceeds 19,600 inch pounds:
Ref: TO 1C-130 E/H/K-1 Pg: 2-67,2-71,2-70 Chap: 2 Para: Caution A. Return the airplane to maintenance and document the highest torque value observed B. Continue the mission and document the highest torque value observed C. An entry in the FORM 781A is required noting the highest torque value observed and describing the runway and/or flight conditions D. Perform an emergency engine shutdown |
C
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60. Never place the throttles in the TAKEOFF position without monitoring the ________, since it is possible to exceed the maximum allowable torque.
Ref: TO 1C-130 E/H/K-1 Pg: 2-67,2-71,2-70 Chap: 2 Para: Caution A. Turbine inlet temperature indicators B. Torque meters C. Fuel flow D. RPM gages |
B
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61. The minimum flap retraction speed for a maximum effort takeoff is:
Ref: TO 1C-130 E/H/K-1 Pg: 2-69,2-73,2-72 Chap: 2 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 |
C
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62. For GCAS ESCAPE MANEUVERS; Crewmembers will back up the pilot who is performing the escape maneuver. The __________ and ____________ will confirm escape maneuver is being properly flown.
Ref: TO 1C-130 E/H/K-1 Pg: 2-71,2-75,2-74 Chap: 2 Para: Warning A. Flight Engineer, navigator B. Navigator, pilot monitoring C. Pilot monitoring, loadmaster D. Engineer, pilot monitoring |
D
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63. For GCAS ESCAPE during IMC Departure/Approach. Immediately and simultaneously rotate the airplane to at least 7° pitch-up, roll wings level and add maximum power to alter the airplanes flight path until _______________.
Ref: TO 1C-130E/H/K-1 Pg: 2-71, 2-75, 2-74 Chap: 2 Para 1.a. A. The warning has ceased and adequate terrain clearance is verified B. MSA is reached C. ATC gives a new clearance D. The stall margin is reached |
A
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64. 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.
Ref: TO 1C-130 E/H/K-1 Pg: 2-77,2-81,2-79 Chap: 2 Para: Note A. 20 B. 15 C. 10 D. 5 |
D
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65. Higher than normal ________ system pressure may be encountered in-flight.
Ref: TO 1C-130 E/H/K-1 Pg: 2-80,2-85,2-83 Chap: 2 Para: Note A. Normal brake B. Emergency brake C. Utility D. Booster |
B
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66. At high airspeeds, abrupt movement of the throttles into the ground range could result in:
Ref: TO 1C-130 E/H/K-1 Pg: 2-81,2-86,2-84 Chap: 2 Para: Warning A. Pitchlock B. Power-loss/bog-down C. None of the above D. All of the above |
A
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67. The two common types of wind shear phenomena found on final approach are:
Ref: TO 1C-130 E/H/K-1 Pg: 2-82,2-87,2-85 Chap: 2 A. Decreasing headwind, increasing headwind B. Upward vector, downward vector C. Microburst, Thunderstorms D. Cold Fronts, Warm Fronts |
A
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68. If severe wind shear is encountered on final and a recovery is flown, the navigator/engineer will monitor and call out ___________________.
Ref: TO 1C-130E/H/K-1, Pg: 2-83, 2-89, 2-86 Para: Wind Shear Recovery A. Engine instruments and airspeed B. Terrain clearance and traffic deconfliction C. Radar Altimeter D. Sink rate (VVI/VSI) and airspeed as appropriate |
C
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69. The only sound response when severe wind shear is encountered during an approach is an immediate decision to _______________
Ref: TO 1C-130E/H/K-1 Pg: 2-84, 2-89, 2-87 Para: Warning 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 |
A
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70. During landing, at the first indication of directional control difficulties during reversing, immediately:
Ref: TO 1C-130 E/H/K-1 Pg: 2-86,2-90,2-88 Chap: 2 Para: Warning 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 |
B
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71. The nose gear must be on the ground prior to _________.
Ref: TO 1C-130 E/H/K-1 Pg: 2-87,2-91,2-90 Chap: 2 Para: Warning A. Entering ground range B. Reversing C. Coming out of flight idle D. Going to ground stop |
B
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72. When moving the flaps at low airspeed, an asymmetrical flap may go undetected until near or above ___________.
Ref: TO 1C-130 E/H/K-1 Pg: 2-88, 2-93, 2-91 Chap: 2 Para: Warning A. Rotation speed B. VMCG C. VMCA D. Takeoff speed |
D
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73. If a go-around is accomplished, retracting flaps from 100 to 50 percent will:
Ref: TO 1C-130 E/H/K-1 Pg: 2-90,2-95,2-94 Chap: 2 Para: Warning A. Decrease sink rate B. Increase sink rate C. Decrease stall speed D. Increase stall speed |
D
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74. The flight engineer should monitor engine instruments during shutdown for:
Ref: TO 1C-130 E/H/K-1 Pg: 2-96,2-101,2-100 Chap: 2 Para: Note A. Turbine inlet temperature and RPM decrease and NTS lights B. Zero fuel flow and turbine inlet temperature and RPM decrease C. Zero fuel flow and turbine inlet temperature and torque decrease D. Zero fuel flow and turbine inlet temperature decrease and NTS lights |
B
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75. If NTS advisory lights do not illuminate when shutting down engines from low-speed ground idle:
Ref: TO 1C-130 E/H/K-1 Pg: 2-96,2-102,2-100 Chap: 2 Para: Note 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 |
B
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76. Regardless of specific emergency encountered:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-2,3A-3,3A-2 Chap: 3A A. Maintain airplane control B. Analyze the situation C. Take coordinated corrective action D. All the above |
D
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77. 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)
Ref: TO 1C-130 E/H/K-1 Pg: 3A-4,3A-4,3A-4 Chap: 3 Para: Warning 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 |
C
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78. If on crossfeed during the ENGINE SHUTDOWN PROCEDURE, ________ before shutting off the fuel boost pump and closing the crossfeed valve for the affected engine.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-6,3A-5,3A-6 Chap: 3 Para: Note 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 |
C
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79. If cabin pressure increases at an excessive rate and cannot be reduced by normal means then:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-8,3A-9,3A-9 Chap: 3 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 |
D
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80. 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:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-9,3A-8,3A-8 Chap: 3 Para: Caution A. Overheated tires B. Overheated brakes C. A failed GTC control valve D. A failed cargo compartment control valve |
B
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81. The correct procedure for high turbine inlet temperature on the ground is:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-10,3A-10,3A-10 Chap: 3 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 |
C
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82. If a tailpipe fire occurs in-flight, follow the ENGINE SHUTDOWN PROCEDURE. If the fire persists:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-10,3A-10,3A-10 Chap: 3 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 |
C
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83. If a turbine overheat occurs in-flight:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-10,3A-10,3A-10 Chap: 3 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 |
A
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84. During GROUND EVACUATION; if pyrotechnics are loaded on the airplane, evacuate a minimum of ______ feet from the airplane.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-11,3A-11,3A-11 Chap: 3 Para: Warning A. 300 B. 400 C. 500 D. 600 |
D
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85. If parking brake handle does not properly retract and requires additional force to fully seat:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-14,3A-14,3A-13 Chap: 3 Para: Note A. Maintenance action required prior to flight B. Turn anti-skid off C. No action required D. Document in Form 781 |
D
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86. 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:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-15,3A-14,3A-14 Chap: 3 Para: Warning A. FLIGHT IDLE B. GROUND IDLE C. TAKEOFF D. REVERSE |
A
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87. For malfunctions which result in asymmetric thrust, the airplane will attempt to ________ the malfunctioning power plant during airplane acceleration.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-15,3A-15,3A-14 Chap: 3 Para: Note A. Turn away from B. Turn toward C. Remain on runway centerline instead of turning into D. Accelerate to Vmcg before turning toward |
B
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88. For a takeoff continued after engine failure, flap retraction should be accomplished in ______ percent increments with airspeed increasing approximately ________ knots between retraction increments.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-16,3A-16,3A-15 Chap: 3 Para: Note A. 5, 5 B. 5, 10 C. 10, 5 D. 10, 10 |
C
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89. In all combinations of two engine failures, monitor ________ to keep it within the range of available output.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-16,3A-16,3A-15 Chap: 3 A. Hydraulic system pressures B. Pressurization system C. Emergency brake system D. Generator loading |
D
|
|
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90. Two-engine operation above ________ pounds gross weight or at high density altitude is marginal.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-17,3A-16,3A-16 Chap: 3 Para: Warning A. 110,000 B. 115,000 C. 120,000 D. 125,000 |
C
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91. 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 E/H/K-1 Pg: 3A-21,3A-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 |
B
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92. During pitchlocked propeller operation, the engine should be shutdown when:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-24,3A-24,3A-23 Chap: 3 A. Reaching 150 KTAS B. 96% RPM cannot be maintained with the throttles C. Reaching a suitable landing area D. All of the above |
D
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93. If a propeller fails to feather in flight, it is critical to restore oil to the ________ of the windmilling propeller as soon as possible.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-24,3A-24,3A-24 Chap: 3 Para: Caution A. Engine section B. Turbine section C. Reduction gearbox D. All the above |
C
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94. For PROPELLER BRAKE FAILURE; if the propeller does counter-rotate, and the procedures are ineffective:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-25,3A-25,3A-25 Chap: 3 Para: Caution 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 |
B
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95. If throttle control cable failure is suspected, do not move the throttle prior to engine shutdown. To do so could cause:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-25,3A-25,3A-25 Chap: 3 Para: Warning 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 |
D
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96. Any time an IGNITION CONTROL circuit breaker is pulled on an inboard engine, the ________ for that engine is inoperative.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-27,3A-26,3A-26 Chap: 3 Para: Note A. Propeller de-icing system B. Propeller anti-icing system C. Engine inlet anti-icing system D. Ice detection system |
D
|
|
|
97. A sheared shaft on the speed sensitive control with the throttle above 65 degrees travel may be indicated by:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-27,3A-27,3A-27 Chap: 3 A. Momentary illumination of the SECONDARY FUEL PUMP PRESSURE light B. ELECTRONIC FUEL CORRECTION light C. Turbine inlet temperature will not exceed start limiting temperature of 830 degrees C D. All the above |
D
|
|
|
98. In case of loss of oil pressure:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-28,3A-27,3A-28 Chap: 3 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 |
B
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|
99. A negative G condition may allow air to enter the engine oil supply line resulting in a loss of oil pressure approximately ________ later due to oil pump cavitation.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-28,3A-27,3A-28 Chap: 3 Para: Note A. 30 to 60 seconds B. 45 to 90 seconds C. 30 to 90 seconds D. 45 to 60 seconds |
C
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|
|
100. If a Tachometer Generator Failure occurs on the engine selected as the master engine, first:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-28,3A-27,3A-28 Chap: 3 A. Place the propeller governor control switch to MECH GOV B. Place the synchrophaser master switch to OFF/other master C. Resync the propellers D. Follow the engine shutdown procedures |
B
|
|
|
101. When operating in tank-to-engine position with an inoperative fuel boost pump, avoid:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-29,3A-29,3A-29 Chap: 3 Para: Note A. Rapid acceleration or nose high attitudes B. Rapid deceleration or nose high attitudes C. Rapid acceleration or nose low attitudes D. Rapid deceleration or nose low attitude |
C
|
|
|
102. Do not select ________ unless the crossfeed system is pressurized by operating fuel boost pumps in other tanks.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-29,3A-28,3A-29 Chap: 3 Para: Warning A. Crossfeed B. Tank to engine C. DUMP D. Crossfeed Bypass |
A
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103. After confirmed fuel pump failure, fuel boost pump circuit breakers may be reset and the pump operated only:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-29,3A-28,3A-29 Chap: 3 Para: Warning A. To prevent having to stop to refuel on a higher headquarters mission with the pilot's approval B. To prevent fuel starvation when a landing cannot be accomplished within the range of available fuel C. If rapid acceleration or nose low attitudes are anticipated D. To avoid enroute stops |
B
|
|
|
104. Prior to performing any procedure which involves removing all AC power:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-33,3A-32,3A-33 Chap: 3 Para: Warning A. Obtain pilot permission to proceed B. Open the oil cooler flaps C. Configure the fuel system for tank to engine operation D. Turn on the UHF radio manual control head |
C
|
|
|
105. Failure of the reverse current relay connecting the essential and isolated DC bus will be indicated by:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-37,3A-36,3A-37 Chap: 3 A. A battery voltmeter indication of 27 volts or less B. Illumination of the essential DC bus off light C. Illumination of all DC bus off lights D. Illumination of the ISOL DC ON BATT/BAT DSCH light and/or a battery voltmeter indication of 24 volts or less |
D
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|
|
106. If flammable fumes are present, electrical equipment not required to complete the FUSELAGE FIRE/SMOKE AND FUME ELEMINATION procedure should:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-45,3A-44,3A-43 Chap: 3 Para: Warning A. Be turned off B. Be disconnected C. Not be turned on or off until the fumes are eliminated D. Be turned on |
C
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|
|
107. Smoke developed in the cargo compartment ________ move forward into the flight
station. The hatch ________ be opened to effectively eliminate smoke and fumes during all elimination emergencies. Ref: TO 1C-130 E/H/K-1 Pg: 3A-48,3A-47,3A-45 Chap: 3A Para: Warning A. Could possibly/should B. Will/must C. Could/will D. May not/may |
B
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|
108. If an in-flight door warning occurs and it cannot be determined what caused the door light to illuminate, the flight ________ at the discretion of the pilot (below the point where the light illuminates and with all personnel secured with safety belts).
Ref: TO 1C-130 E/H/K-1 Pg: 3A-50,3A-49,3A-48 Chap: 3 Para: Warning A. Must be terminated immediately B. May be continued with partial pressurization C. Must continue depressurized D. Must be flown below 10,000 feet |
B
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|
|
109. If the inner and outer panes of a flight deck windshield should crack in-flight, reduce the cabin pressure to ___________.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-51,3A-50,3A-49 Chap: 3 A. Zero B. 3.1 inches or less C. 5 inches or less D. 10 inches or less |
D
|
|
|
110. In the event that utility or boost hydraulic pressure in excess of 3,450 psi is indicated:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-52,3A-51,3A-51 Chap: 3 Para: Caution A. Shut off the #1 and #2 engine hydraulic pump switches B. Do not turn off the individual hydraulic pump switches C. Turn off all the utility system flight control booster switches D. Follow the engine shutdown procedures |
B
|
|
|
111. If elevator control should fail (hydraulic assistance is lost), achieve approximately level flight and ________ KIAS and land with 50% flaps recommended.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-54,3A-53,3A-53 Chap: 3 A. 130 B. 150 C. 170 D. 180 |
C
|
|
|
112. If movement of the flaps, after an outboard flap failure, must be attempted, return them in increments of ________ toward the position last selected before failure. During flap movement, check aileron control ________.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-55,3A-54,3A-54 Chap: 3 Para: Warning A. 5 degrees/constantly B. 5 percent/ after flap movement C. 10 degrees/as flaps are retracting D. 10 percent/constantly |
D
|
|
|
113. Protection against asymmetrical operation is provided only during ________ hydraulic flap operation.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-56,3A-55,3A-55 Chap: 3 Para: Warning A. Normal B. Emergency C. Manual D. All the above |
A
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|
114. ________ take-off with a known or suspected landing gear malfunction.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-59,3A-58,3A-58 Chap: 3 Para: Caution A. Pilot discretion allows a B. Do not attempt a C. If repair facilities are not available you may D. After the flight engineer inspects the gear, the pilot may |
B
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|
115. If the landing gear selector valve DOWN button requires holding to lower the gear, hydraulic pressure will not be available for:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-61,3A-59,3A-59 Chap: 3 Para: Caution A. Extension of the nose landing gear B. Nose wheel steering C. Normal extension of the main landing gear D. Normal brakes |
B
|
|
|
116. For Manual Gear Extension, make sure the ratchet on the hand crank is set for ______ rotation before placing it on the emergency extension stub shaft.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-62,3A-60,3A-62 Chap: 3 Para: Warning A. Down B. Up C. Neutral D. Any |
A
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|
|
117. The order of preference of bailout exits are:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-81,3A-76,3A-75 Chap: 3 A. Cargo door and ramp, paratroop doors and forward crew door B. The cargo door, paratroop doors and side escape hatch C. The cargo ramp, side escape hatch and forward crew door D. Forward crew door, paratroop doors and cargo door and ramp |
A
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118. When landing with two engines inoperative, a go-around is not recommended:
Ref: TO 1C-130 E/H/K-1 Pg: 3A-84,3A-79,3A-80 Chap: 3 Para: Warning A. If the flaps are up B. After the flaps are lowered C. Until the flaps are lowered D. Unless the flaps are set 50 percent |
B
|
|
|
119. When Ditching, the severity of fuselage structural damage or failure depends on sea conditions and aircraft ___________ upon touchdown.
TO 1C-130 E/H/K-1 Pg: 3A-88,3A-83,3A-84 Chap: 3 Para: Warning A. Configuration B. Gross weight C. Flap setting D. Speed/descent rate |
D
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|
|
120. If a decision is made by the pilot to ditch the airplane then a minimum of ________ pounds of fuel should remain at time of descent from altitude.
Ref: TO 1C-130 E/H/K-1 Pg: 3A-89,3A-84,3A-85 Chap: 3 A. 6,000 B. 3,000 C. 2,000 D. 1,500 |
C
|
|
|
121. Negative thrust from propeller(s) retarded to the FLIGHT IDLE position will produce _____ drag than a feathered or windmilling propeller and _________ air minimum control speeds for the condition.
Ref: TO 1C-130 E/H/K-1 Pg: 3B-5,3B-5,3B-5 Chap: 3 Para: Warning A. Less, decrease B. More, decrease C. More, increase D. Less, increase |
C
|
|
|
122. If NTS is not indicated during an airstart, interruption of the start cycle after light off by an attempt to feather before the engine has reached a stabilized speed may result in:
Ref: TO 1C-130 E/H/K-1 Pg: 3B-10,3B-10,3B-9 Chap: 3 Para: Caution A. A pitch locked propeller B. Flameout of the engine C. Decoupling and severe over speed D. Severe over speed |
C
|
|
|
123. Ensure INU power switch has been off for more than ________ seconds before turning SCNS power switch OFF.
Ref: TO 1C-130 E/H/K-1 Pg: 4A-23,4A-24,4A-19 Chap: 4 Para: Note A. 5 B. 10 C. 15 D. 20 |
B
|
|
|
124. When oil temperature exceeds ________ degrees C. for any time duration, an entry will be made in the Form 781 to include duration and temperature.
Ref: TO 1C-130 E/H/K-1 Pg: 5-2,5-2,5-2 Chap: 5 Para: Note A. 85 B. 95 C. 105 D. 100 |
D
|
|
|
125. Normal limits for AC voltage:
Ref: TO 1C-130 E/H/K-1 Pg: 5-2,5-4,5-7 Chap: 5 A. 110 to 120 Volts B. 115 to 125 Volts C. 115 to 130 Volts D. 110 to 125 Volts |
D
|
|
|
126. Power section oil pressure up to ________ PSI is allowable during start and warm-up.
Ref: TO 1C-130 E/H/K-1 Pg: 5-2,5-2,5-4 Chap: 5 A. 50 B. 60 C. 85 D. 100 |
D
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|
|
127. Normal limit for the cabin differential gage:
Ref: TO 1C-130 E/H/K-1 Pg: 5-3,5-3,5-5 Chap: 5 A. 1.2 to 15.8 In. Hg B. 1.2 to 15.9 In. Hg C. -1.2 to 15.8 In. Hg D. -1.2 to 15.9 In. Hg |
C
|
|
|
128. The external fuel tank fuel boost pump pressure limits are ________ PSI.
Ref: TO 1C-130 E/H/K-1 Pg: 5-3,5-3,5-5 Chap: 5 A. 28 to 45 B. 28 to 40 C. 15 to 24 D. 15 to 20 |
B
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129. The normal limits on the DC voltmeter are ________ volts.
Ref: TO 1C-130 E/H/K-1 Pg: 5-4,5-4,5-7 Chap: 5 A. 21-25 B. 21-35 C. 24-30 D. 25-30 |
D
|
|
|
130. In case of emergency, oxygen usage may be continued until:
Ref: TO 1C-130 E/H/K-1 Pg: 5-6,5-6,5-9 Chap: 5 Para: Note A. 10 liters remaining B. 5 liters remaining C. 2.5 liters remaining D. System is empty |
D
|
|
|
131. During propeller reversing check, if symmetrical torque differences are ________ inch pounds or more, record in AFTO Form 781.
Ref: TO 1C-130 E/H/K-1 Pg: 5-8,5-8,5-11 Chap: 5 A. 1,500 B. 2,000 C. 1,000 D. 900 |
C
|
|
|
132. Do not exceed ________ KIAS with the ramp (or ramp and cargo door) open regardless of whether the paratroop doors are open or closed or the position of the air deflectors.
Ref: TO 1C-130 E/H/K-1 Pg: 5-11,5-12,5-10 Chap: 5 A. 130 B. 145 C. 150 D. 180 |
C
|
|
|
133. Maximum airspeed with the paratroop doors open and locked is:
Ref: TO 1C-130 E/H/K-1 Pg: 5-12,5-12,5-10 Chap: 5 A. 250 KIAS B. 150 KIAS C. 185 KIAS D. 200 KIAS |
A
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134. With any flap extension, the maximum maneuver load factor is ________ G in unsymmetrical maneuvers.
Ref: TO 1C-130 E/H/K-1 Pg: 5-13,5-13,5-16 Chap: 5 Para: Caution A. 2.0 B. 1.5 C. 2.5 D. 1.0 |
B
|
|
|
135. Secondary fuel management will shorten the service life of the wings and should be avoided unless necessary for mission accomplishment. This becomes more critical when:
Ref: TO 1C-130 E/H/K-1 Pg: 5-15,5-15,5-18 Chap: 5 Para: Note A. Operating near the gross weight limit for an applicable maneuver B. When carrying more than approximately 10,000 lbs of cargo C. Operating near the gross weight for an applicable speed D. All of the above |
D
|
|
|
136. Maximum effort operations with airplane configuration (fuel, cargo, etc.) that necessitate 300 FPM rate-of-sink should be restricted to wartime operation only. To perform during peacetime will require ________ approval.
Ref: TO 1C-130 E/H/K-1 Pg: 5-24,5-23,5-26 Chap: 5 Para: Caution A. Unit commander B. Operations Group commander C. Numbered Air Force D. Major Command |
D
|
|
|
137. Under stable conditions, allowable oil pressure fluctuation is _________ psi (_________ psi excursion) for the power section.
Ref: TO 1C-130 E/H/K-1 Pg: 5-42,5-38,5-41 Chap: 5 Para: Delta 1 A. 20 psi/40 psi B. +/- 10 psi/20 psi C. +/- 5 psi/20 psi D. +/- 10 psi/10 psi |
B
|
|
|
138. Normal speed ground idle RPM limits are ________ percent.
Ref: TO 1C-130 E/H/K-1 Pg: 5-42,5-37,5-41 Chap: 5 A. 96-106 B. 69-75.5 C. 94.5-100.5 D. 94-102 |
D
|
|
|
139. Reduction gearbox oil pressure is permitted to go below ________ PSIG when RPM is below 100% if 150 PSIG can be maintained at 100% RPM with oil temperature normal.
Ref: TO 1C-130 E/H/K-1 Pg: 5-42,5-37,5-41 Note 3 Chap: 5 A. 100 B. 130 C. 150 D. 50 |
C
|
|
|
140. If start *** is between 720-750 degrees C:
Ref: TO 1C-130 E/H/K-1 Pg: 5-43,5-39,5-42 Chap: 5 A. Record in Form 781and perform a temperature controlling check IAW section 1B B. Record in Form 781, perform a temperature controlling check IAW section 1B, and record crossover turbine inlet temperature C. Maintenance action is required D. All the above |
A
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141. If the feather override button fails to pop out within 6 seconds after the the propeller is feathered:
Ref: TO 1C-130 E/H/K-1 Pg: 5-44,5-40,5-43 Chap: 5 A. Pull the aux feather motor circuit breakers B. Pull it out manually to shut off the pump. Maintenance action is required prior to flight C. Record in 781A. Maintenance action is required after flight D. Reset the fire handle if pulled to restore oil to the engine |
B
|
|
|
142. Allowable propeller fluctuations are:
Ref: TO 1C-130 E/H/K-1 Pg: 5-44,5-40,5-43 Chap: 5 A. Plus/minus 1.0% either side of a stable RPM for a total of 2% B. Plus/minus 0.5% either side of a stable RPM for a total of 1% C. 2% maximum D. Propeller flux is not allowed |
B
|
|
|
143. Raising of the flaps is permissible during stall recovery to decrease drag and assist in the recovery.
Ref: TO 1C-130 E/H/K-1 Pg: 6-1,6-1,6-1 Chap: 6 Para: Warning A. True B. False |
B
|
|
|
144. Fin stall can occur at all speeds between stall speed and approximately ________ KIAS in all flap configurations with power________.
Ref: TO 1C-130 E/H/K-1 Pg: 6-2,6-2,6-2 Chap: 6 A. 170/OFF B. 185/ON C. 185/OFF D. 170/ON |
D
|
|
|
145. The recommended airspeed for penetration into thunderstorms is:
Ref: TO 1C-130 E/H/K-1 Pg: 7-3,7-2,7-3 Chap: 7 Para: NOTE A. 65 knots above power-off stall speed not to exceed 165 KIAS B. 65 knots above power-on stall speed not to exceed 165 KIAS C. 65 knots above power-off stall speed not to exceed 180 KIAS D. 65 knots above power-on stall speed not to exceed 180 KIAS |
C
|
|
|
146. Cold weather procedures are generally considered to be applicable when the temperature is ________ and below.
Ref: TO 1C-130 E/H/K-1 Pg: 7-3,7-5,7-4 Chap: 7 A. Below 15 degrees C B. 32 degrees F C. 0 degrees C D. Both B and C |
D
|
|
|
147. Starts in cold weather conditions may result in start turbine inlet temperature less than normal starting limits. If all engine starts are similar in turbine inlet temperature:
Ref: TO 1C-130 E/H/K-1 Pg: 7-6,7-8,7-7 Chap: 7 Para: Note A. Consider this a normal start, no further action is required B. Consider this a cold start, maintenance action is required C. Restart the engine using enrichment, note start turbine inlet temperature D. Restart the engine, note start turbine inlet temperature |
A
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148. ________ should be on during takeoff and climb if temperature is 32 degrees F or
lower and any visible moisture is present. Ref: TO 1C-130 E/H/K-1 Pg: 7-8,7-9,7-8 Chap: 7 Para: Caution A. Nacelle preheat B. Propeller and engine anti-icing and deicing C. Leading edge and empennage anti-icing D. B and C |
B
|
|
|
149. Takeoff run is ________ and rate of climb decreased in high temperatures.
Ref: TO 1C-130 E/H/K-1 Pg: 7-10,7-11,7-10 Chap: 7 A. The same B. Better C. Considerably increased D. Considerably decreased |
C
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150. In accordance with hot weather procedures, during descent (for landing) below ________ feet, manually open the oil cooler flaps and place the switches to the FIXED position.
Ref: TO 1C-130 E/H/K-1 Pg: 7-10,7-11,7-10 Chap: 7 A. 5,000 B. 10,000 C. 15,000 D. 20,000 |
C
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151. As soon as the airplane is parked during hot weather, chock wheels and ________ in order to avoid possible damage to brake components from excessive heat generated while taxiing.
Ref: TO 1C-130 E/H/K-1 Pg: 7-10,7-11,7-11 Chap: 7 A. Set the parking brake B. Release brakes C. Select emergency brakes D. Deplete brake pressure |
B
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152. In accordance with desert procedures; when propeller reversing is used during landing, start moving the throttles from MAXIMUM REVERSE to GROUND IDLE at approximately ________ KIAS and have the throttles at GROUND IDLE by the time 40 KIAS is reached.
Ref: TO 1C-130 E/H/K-1 Pg: 7-12,7-13,7-12 Chap: 7 A. 60 B. 80 C. 100 D. 115 |
A
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153. Take-Off factor combines the parameters of:
Ref: TO 1C-130E(H)1-1/H1-1 Generic Pg: 3-6,3-9 Chap: 3 A. Temperature, pressure altitude, and turbine inlet temperature B. Torque, field pressure altitude, runway temperature, turbine inlet temperature, and engine efficiency C. Pressure altitude, temperature, turbine inlet temperature, and runway available D. Runway temperature, field pressure altitude, torque, and bleed air requirements |
B
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154. When the crosswind component and_____________ fall within the caution area, the take-off or touchdown speed should be increased until the recommended area is reached or until the aircraft speed has been increased by 10 knots.
Ref: TO 1C-130E(H)1-1/H1-1 Generic Pg: 3-11,3-13 Chap: 3 A. Vmca B. Normal take-off or touch down speed C. Vmcg D. Refusal or normal take-off speed |
B
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155. When corrected refusal speed exceeds take-off speed, use _________.
Ref: TO 1C-130E(H)1-1/H1-1 Generic Pg: 3-16.2,3-18 Chap: 3 A. Vmcg B. Vmca C. Refusal speed D. Take-off speed for refusal speed |
D
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156. When computing climb-out performance, a headwind ________used for obstacle clearance, but the tailwind component ________ used to determine an effective obstacle distance.
Ref: TO 1C-130E(H)1-1/H1-1 Generic Pg: 3-18,3-20 Chap: 3 A. is / is not B. must / may C. is not / is D. may / must |
C
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157. The RCR factor ________ affect the 4-engine climbout, but ________ affect the 3-engine climbout.
Ref: TO 1C-130E(H)1-1/H1-1 Generic Pg: 3-19,3-21 Chap: 3 Para: Note A. does not / does B. does / does not C. may / will D. will / may |
A
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158. For normal take-off, rotation speed is _________ than take-off speed to be used.
Ref: TO 1C-130E(H)1-1/H1-1 Generic Pg: 3-22,3-24 Chap: 3 Para: Note A. 10 KIAS more B. 5 KIAS more C. 5 KIAS less D. 10 KIAS less |
C
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159. For Refusal Speed, in the event of an engine failure, the options available are based on ________.
Ref: TO 1C-130E(H)1-1/H1-1 Generic Pg: 3-35,3-36.1 Chap: 3 A. Vmcg, Vr, and Vcef B. Vr, Vcef, and Vmca C. Vcef, Vmca, and Vmcg D. Vmca, Vmcg, and Vcef |
A
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160. If headwinds of more than 70 knots are encountered, increasing the cruise TAS by _________ knots for every _________ knots above 70 knots headwind will result in operating the airplane near the maximum nautical miles per pound of fuel.
Ref: TO 1C-130E(H)1-1/H1-1 Generic Pg: 5-8,5-11 Chap: 5 A. 4/10 B. 6/12 C. 8/16 D. 10/20 |
A
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161. ________ is operation at the speed which results in the minimum fuel flow for the given configuration, altitude, temperature, and gross weight.
Ref: TO 1C-130E(H)1-1/H1-1 Generic Pg: 6A-1,6A-2 Chap: 6 A. Optimum endurance B. Low altitude search C. Maximum endurance D. 3-engine drift down speed |
C
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162. When landing with one or two engines inoperative, it is recommended that the in-flight ________ be compared to the ________ and the higher speed be used for approach.
Ref: TO 1C-130E(H)1-1/H1-1 Generic Pg: 8-3 Note,9-4 Note A. Applicable stall speed/touchdown speed B. Minimum control speed/recommended approach speed C. Recommended approach speed/applicable stall speed D. Minimum control speed/threshold speed |
B
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163. Take-off and immediate landing data for the departure airfield will be completed prior to ________. The destination landing data will be computed prior to the completion of ________.
Ref: TO 1C-130E(H)1-1/H1-1 Generic Pg: 9-1 Note,10-1 Note A. COCKPIT/DESCENT checklist B. Stations time/BEFORE LANDING checklist C. LINEUP/BEFORE LANDING checklist D. Take-off/DESCENT checklist |
D
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164. Temperature and pressure altitude will be obtained from __________.
Ref: TO 1C-130E(H)1-1/H1-1 Generic Pg: 9-2,10-2 Chap: 9,10 A. ATIS B. Tower C. Weather briefing D. All of the above |
D
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165. Which of the following information is obtained from the FLIP?
Ref: TO 1C-130E(H)1-1/H1-1 Generic Pg: 9-2,10-2 Chap: 9,10 A. Obstacle height and distance, climb gradient, runway heading, component H/T B. Climb gradient, RCR, slope, and obstacle height and distance C. Runway heading/Length , obstacle height/distance, climb gradients, and slope D. Component H/T, RCR, Temperature, and field elevation |
C
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166. Unless otherwise directed, waiver authority for the contents of AFI 11-2C-130V3 is the __________ with mission execution authority.
Ref: AFI 11-2C-130 Vol 3 Pg: 20 Chap: 1 Para: 1.4.2. A. OG/CC B. SQ/DO C. MAJCOM/A3/DO D. AW/CC |
C
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167. __________ is the period of time starting at mission report time and ending immediately after the aircrew completes the final engine shutdown of the day.
Ref: AFI 11-2C-130 Vol 3 Pg: 31 Chap: 3 Para: 3.7.1. A. Flight Duty Period B. Crew Duty Day C. Crew Duty Time D. Flight Duty Day |
A
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168. Complete all mission-related events (i.e., FCF/ACF checks, transition events, or tactical events) during the first _____ hours of the FDP.
Ref: AFI 11-2C-130 Vol 3 Pg: 32 Chap: 3 Para: 3.7.1.5.2. A. 8 B. 10 C. 12 D. 14 |
C
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169. SQ/CCs shall not schedule an aircrew member to fly nor will an aircrew member perform aircrew duties:
Ref: AFI 11-2C-130 Vol 3 Pg: 33 Chap: 3 Para: 3.8. A. When the flight will exceed maximum flying time limitations of AFI 11-202V3. B. Within 12 hours of consuming alcoholic beverages or impaired by its after effects. C. When using nasal sprays to treat symptoms of head congestion existing before flight. D. All of the above |
D
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170. The ___________ is the final authority in determining the overall suitability of an aircraft for the mission.
Ref: AFI 11-2C-130 Vol 3 Pg: 43 Chap: 4 Para: 4.1 A. PIC B. co-pilot C. flight engineer D. SQ/DO |
A
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171. A PIC who accepts an aircraft with degraded equipment/systems is not committed to subsequent operations with the same degraded equipment.
Ref: AFI 11-2C-130 Vol 3 Pg: 43 Chap: 4 Para: 4.2. A. True B. False |
A
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172. Do not connect unauthorized equipment (laptop computers, video equipment, food preparation equipment, radios/tape players, CD players, etc.) to:
Ref: AFI 11-2C-130 Vol 3 Pg: 59 Chap: 5 Para: 5.9.1. A. the aircraft intercom/PA B. radio systems C. electrical system D. all of the above |
D
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173. Any crewmember seeing a deviation of _____ feet altitude or _____ knots in airspeed, or a potential terrain or obstruction problem, will immediately notify the PF.
Ref: AFI 11-2C-130 Vol 3 Pg: 60 Chap: 5 Para: 5.11.2.2. A. 50/5 B. 100/10 C. 200/10 D. 200/20 |
C
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174. The stabilization point for precision approaches is at _______ feet above Threshold Elevation (THRE). For all other approaches (except tactical approaches), the stabilization point is at ______ feet above THRE unless otherwise briefed by the PF.
Ref: AFI 11-2C-130 Vol 3 Pg: 62 Chap: 5 Para: 5.12. A. 500/300 B. 300/100 C. 500/100 D. 1000/300 |
D
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175. At the briefed stabilization point, the _____ will state the altitude (AGL) and announce “stable” or “go-around”.
Ref: AFI 11-2C-130 Vol 3 Pg: 63 Chap: 5 Para: 5.12.1.8. A. PF B. PM C. Navigator D. Any crewmember |
B
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176. It is imperative for aircrews to review the airfield environment. Identify key features such as:
Ref: AFI 11-2C-130V3 Pg: 63 Chap: 5 Para: 5.12.4. A. Approach light type B. Airfield lighting C. Geographic layout/configuration of runways, taxiways, ramps D. All of the above |
D
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177. In terminal areas, __________ (if able) will monitor the command radio unless directed otherwise.
Ref: AFI 11-2C-130 Vol 3 Pg: 63 Chap: 5 Para: 5.13.2.2. A. the navigator B. the crew chief C. all crewmembers D. PIC |
C
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178. With the exception of cruise flight, conversation below _________ will be limited to mission, departure, or approach essential items.
Ref: AFI 11-2C-130 Vol 3 Pg: 64 Chap: 5 Para: 5.14.3 A. 10,000 feet AGL B. 10,000 feet MSL C. 18,000 feet AGL D. 18,000 feet MSL |
D
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179. Any crewmember that observes both pilots heads-down at the same time (other than heads-down instrument flying) shall alert the PF without delay.
Ref: AFI 11-2C-130V3 Pg: 64 Chap: 5 Para:5.14.4. A. True B. False |
A
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180. This is a closed-loop system of communication designed to significantly reduce typical automation selection errors between the PF, PM, and the navigator.
Ref: AFI 11-2C-130V3 Pg: 65 Chap: 5 Para: 5.15.2. A. Crew Resource Management (CRM) B. Verbalize, Verify, and Monitor (VVM) C. Aviation Safety Action Program (ASAP) D. Human Error Redundency Efforts (HERE) |
B
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181. For peace-time do not use runways less than __________ feet.
Ref: AFI 11-2C-130 Vol 3 Pg: 65 Chap: 5 Para: 5.18.1 A. 3,000 B. 3,500 C. 5,000 D. 5,500 |
A
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182. All maximum effort operations must fall in the ___________ area of charts (corrected for RCR) unless otherwise approved by OG/CC.
Ref: AFI 11-2C-130 Vol 3 Pg: 67 Chap: 5 Para: 5.18.6. A. tactical B. recommended C. caution D. not recommended |
B
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183. Do not taxi an aircraft within _____ feet of obstructions without wing walkers monitoring the clearance between aircraft and obstructions. With wing walkers, avoid taxi obstructions by at least ____ feet.
Ref: AFI 11-2C-130 Vol 3 Pg: 68 Chap: 5 Para: 5.19.1. A. 10/25 B. 15/25 C. 25/10 D. 25/15 |
C
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184. __________ detecting the illumination of the radar altimeter Low Altitude Warning Light will immediately notify the pilot flying the aircraft.
Ref: AFI 11-2C-130 Vol 3 Pg: 72 Chap: 5 Para: 5.26.1 A. The pilot not flying B. The flight engineer C. Any crewmember D. The crew chief |
C
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185. Pilots will normally use __________ for takeoffs provided refusal speed (Vr) is equal to or greater than takeoff speed.
Ref: AFI 11-2C-130 Vol 3 Pg: 72 Chap: 5 Para: 5.28 A. max power B. reduced power C. max continuous power D. bleeds closed power |
B
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186. Crewmembers will carry __________ on all flights
Ref: AFI 11-2C-130 Vol 3 Pg: 75 Chap: 6 Para: 6.2.5. A. magazines B. two identification tags C. one identification tag D. three identification tags |
B
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187. Each crewmember must carry an operable flashlight for night flights.
Ref: AFI 11-2C-130 Vol 3 Pg: 76 Chap: 6 Para: 6.2.8. A. True B. False |
A
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188. Any crewmember that experiences NVG problems will:
Ref: AFI 11-2C-130 Vol 3 Pg: 82 Chap: 6 Para: 6.12.2.2. A. call "knock it off" B. inform the rest of the crew C. cease logging NVG time on the AFTO 781 D. report the problem immediately to life support |
B
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189. The __________ will provide the obstacle height, distance, and gradient information necessary for performance computations to the flight engineer.
Ref: AFI 11-2C-130 Vol 3 Pg: 85 Chap: 6 Para: 6.16. A. IFR Supplement B. Pilot In Command (PIC) C. Pilot Monitoring (PM) D. Navigator |
B
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190. When any doubt exists about which screen height to use, plan to cross the DER at _____ feet (minimum) unless you can ascertain a different screen height requirement from an appropriate authority.
Ref: AFI 11-2C-130 Vol 3 Pg: 86 Chap: 6 Para: 6.16.3.2. A. 16 B. 0 C. 35 D. 50 |
C
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191. Aircraft must be able to meet the published climb gradient for the departure runway with all engines operating. If no minimum climb gradient is published, _____ ft/nm to MSA will be used.
Ref: AFI 11-2C-130 Vol 3 Pg: 86 Chap: 6 Para: 6.16.3.3. A. 152 B. 200 C. 252 D. 48 |
B
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192. Flight into areas of forecast or reported __________ is prohibited.
Ref: AFI 11-2C-130 Vol 3 Pg: 89 Chap: 6 Para: 6.21.1. A. severe clear B. cold weather C. low per diem D. severe turbulence |
D
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193. Do not takeoff under conditions of freezing rain.
Ref: AFI 11-2C-130 Vol 3 Pg: 90 Chap: 6 Para: 6.21.2.1. A. True B. False |
A
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194. Do not fly directly above (within _____ feet) thunderstorms or cumulonimbus clouds.
Ref: AFI 11-2C-130 Vol 3 Pg: 90 Chap: 6 Para: 6.21.3. A. 1000 B. 1500 C. 2000 D. 2500 |
C
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195. Aircraft damage may occur up to _____ from any thunderstorms.
Ref: AFI 11-2C-130 Vol 3 Pg: 91 Chap: 6 Para: 6.21.3.1.4 A. 5 NMs B. 10 NMs C. 20 NMs D. 50 NMs |
C
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196. Maintain at least _____ separation from heavy rain showers.
Ref: AFI 11-2C-130 Vol 3 Pg: 91 Chap: 6 Para: 6.21.3.3.2 A. 5 NMs B. 7 NMs C. 10 NMs D. 20 NMs |
A
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197. The aircraft dash one preflight inspection will remain valid until either:
Ref: AFI 11-2C-130 Vol 3 Pg: 93 Chap: 6 Para: 6.25.3.1 A. aircraft ground time exceeds 12 hours B. aircraft ground time exceeds 72 hours provided the aircraft is sealed, not flown, and documented entry control is maintained. C. another maintenance dash six preflight is performed D. all of the above |
D
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198. Under no circumstance will any crewmember act as the towing supervisor.
Ref: AFI 11-2C-130 Vol 3 Pg: 94 Chap: 6 Para: 6.25.6 A. True B. False |
A
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199. Crewmembers will fit and adjust LPUs for overwater flights and will wear them on overwater missions below _______ feet.
Ref: AFI 11-2C-130 Vol 3 Pg: 94 Chap: 6 Para: 6.27.3. A. 500 B. 1,000 C. 2,000 D. 5,000 |
C
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200. Non-Current and/or unqualified NVG aircrews may fly NVG departures in weather down to ______.
Ref: AFI 11-2C-130 Vol 3 Pg: 98 Chap: 6 Para: 6.33.1. A. 1200/1 B. 1500/3 C. 1200/2 D. 1300/2 |
B
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201. The C-130 is a category “C” aircraft. If approach speeds exceed _____ knots, the minimums for category “D” will be used.
Ref: AFI 11-2C-130 Vol 3 Pg: 101 Chap: 6 Para: 6.42.1 A. 130 B. 135 C. 140 D. 145 |
C
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202. If involved in a mishap or incident, after landing and terminating the emergency, pull the ___________ power circuit breaker.
Ref: AFI 11-2C-130 Vol 3 Pg: 109 Chap: 6 Para: 6.49 A. ignition control B. CVR and FDR C. start control D. all of the above |
B
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203. The maximum number of persons on the flight deck will be the minimum commensurate with the mission requirements. At no time will this exceed _____ (unless otherwise specified in a MAJCOM supplement).
Ref: AFI 11-2C-130 Vol 3 Pg: 111 Chap: 6 Para: 6.57.1 A. five B. seven C. eight D. ten |
B
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204. If departure is not possible, the aircrew must secure the aircraft to the best of their ability. In no case, will the entire crew leave the aircraft unattended. Crew rest will be subordinate to aircraft security when the airframe may be at risk.
Ref: AFI 11-2C-130 Vol 3 Pg: 113 Chap: 7 Para: 7.5.2.3 A. True B. False |
A
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205. Crews facing a hijacking threat will notify ground agencies by __________.
Ref: AFI 11-2C-130 Vol 3 Pg: 117 Chap: 7 Para: 7.11 A. Transmit an in-the-clear notification of hijacking to ATC B. Set transponder to code 7500 C. Transmit a radio message indicating transponder change to 7500. D. All of the above |
D
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206. When required to transfer a loaded weapon to another crew member, __________.
Ref: AFI 11-2C-130 Vol 3 Pg: 118 Chap: 7 Para: 7.13.7 A. use hand-to hand transfer B. hand the weapon butt first C. place the weapon on a flat surface D. it is not authorized for individuals to transfer weapons |
C
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207. The __________ is a tool to notify appropriate authorities of any mishap involving crewmembers or aircraft.
Ref: AFI 11-2C-130 Vol 3 Pg: 120 Chap: 8 Para: 8.4 A. AF IMT 457, USAF Hazard Report B. AMC IMT 97, AMC In-Flight Emergency and Unusual Occurrence Worksheet C. AMC IMT 54, Aircraft Commander's report on Services/Facilities D. AF IMT 651, Hazardous Air Traffic Report |
B
|
|
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208. This is used for the purchase of aviation fuel and ancillary ground services at commercial airports (and some military installations) worldwide.
Ref: AFI 11-2C-130 Vol 3 Pg: 124 Chap: 8 Para: 8.6 A. SF 44, Purchase Order-Invoice-Voucher B. DD Form 1898, Fuels Sales Slip C. AF IMT 664, Aircraft Fuels Documentation Log D. U.S. Government Aviation Into-Plane Reimbursement (AIR) card |
D
|
|
|
209. Initial qualification or re-qualification for pilots ____________ be conducted with passengers onboard.
Ref: AFI 11-2C-130 Vol 3 Pg: 127 Chap: 9 Para: 9.1.1 A. may B. will not C. may, under extenuating circumstances D. may, for currency |
B
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210. Minimum runway length for 50% flap flight idle touch-and-go landing is _____ feet. Minimum runway length for all other touch-and-go landings is _____ feet.
Ref: AFI 11-2C-130 Vol 3 Pg: 127 Chap: 9 Para: 9.2.2.2 A. 6,000/7,000 B. 7,000/8,000 C. 5,000/6,000 D. 5,000/7,000 |
C
|
|
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211. Touch and go landings are only authorized when the crosswind component corrected for RCR is within the ___________ zone for the landing crosswind chart.
Ref: AFI 11-2C-130 Vol 3 Pg: 127 Chap: 9 Para: 9.2.2.4. A. Caution B. Recommended C. Not recommended D. All of the Above |
B
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212. Do not conduct simulated aircraft systems emergency procedures training during any tactical training (operating in low level environment or during tactical approaches).
Ref: AFI 11-2C-130 Vol 3 Pg: 128 Chap: 9 Para: 9.4.1.2. A. True B. False |
A
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213. Maximum gross weight for a no-flap landing is _____ lbs.
Ref: AFI 11-2C-130 Vol 3 Pg: 131 Chap: 9 Para: 9.9.1.6. A. 130,000 B. 120,000 C. 110,000 D. 125,000 |
B
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214. When performing a Stop-and-Go landing, runway remaining for takeoff must be greater than or equal to __________.
Ref: AFI 11-2C-130 Vol 3 Pg: 131 Chap: 9 Para: 9.9.2.3 A. CFL B. 4 engine ground run C. 3 engine minimum field length D. MFLMETO |
A
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215. With actual or suspected vapor contamination, the aircraft must be purged for __________ using Smoke and Fume Elimination procedures to eliminate the vapor hazard.
Ref: AFI 11-2C-130 Vol 3 Pg: 143 Chap: 10 Para: 10.5.8. A. Thirty minutes B. Two hours C. One hour D. Forty-five minutes |
B
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216. When it is suspected or known that an aerospace vehicle or piece of equipment has been contaminated with a radiological, biological or chemical contaminant, a _________ will be entered and an annotation will be made in historical records for the lifecycle of the equipment.
Ref: AFI 11-2C-130 Vol 3 Pg: 143 Chap: 10 Para: 10.5.9. A. Red dash B. Red diagonal C. Red X D. None of the above |
C
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217. If a situation is encountered where the aircraft is on a Red X and qualified maintenance personnel are not available to clear it, the highest qualified flight engineer on scene may obtain authorization to sign off the Red X from the ___________, in accordance with TO 00-20-1.
Ref: AFI 11-2C-130 Vol 3 Pg: 166 Chap: 12 Para: 12.3. A. SQ/CC, SQ/DO, or maintenance officer B. Home station OG/CC C. SQ/CC or his designated representative D. Home station MXG/CC or designated representative |
D
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218. When crewmembers are required to refuel, the flight engineer will act as the __________.
Ref: AFI 11-2C-130 Vol 3 Pg: 166 Chap: 12 Para: 12.4.1.1 A. Refueling team supervisor B. Refueling panel operator C. Fire guard D. None of the above |
A
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219. Unless servicing JP-4, simultaneous servicing of fuel while loading passengers, cargo, performing maintenance, aircrew members performing inspections, or operating aircraft systems is considered to be a normal fuel servicing operation.
Ref: AFI 11-2C-130 Vol 3 Pg: 166 Chap: 12 Para 12.4.1. A. True B. False |
A
|
|
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220. During normal fuel servicing operations, simultaneous fuel and oxygen servicing is not authorized.
Ref: AFI 11-2C-130 Vol 3 Pg: 167 Chap: 12 Para: 12.4.1.10 A. True B. False |
A
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221. In addition to the procedures in __________ and ___________, the flight engineer will assist the pilot in maintaining the AFTO Form 781.
Ref: AFI 11-2C-130 Vol 3 Pg: 168 Chap: 12 Para: 12.7.2. A. T.O. 00-25-172/AFI 11-2C-130 Vol 3 B. T.O. 00-20-1/AFI 11-401 C. T.O. 00-25-172/AFI 11-402 D. T.O. 00-20-1/ AFI 11-2C-130 Vol 3 |
B
|
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222. When conducting flaps up landings, compute and post VMCA speeds for both configurations; flaps 50% and flaps up (normal boost). For example: VMCA, in ground effect, one engine inoperative - 105/122.
Ref: AFI 11-2C-130 Vol 3 Pg: 168 Chap: 12 Para: 12.8.2 A. True B. False |
A
|
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223. Minimum TOLD requirements for a termination landing are: Air Minimum Control Speeds, Obstacle Clearance Speed, 3 Engine Climb Speed, 100 & 50% Flap Landing Speeds and Distances, 0% Landing Approach Speed (Night or IMC), and __________.
Ref: AFI 11-2C-130 Vol 3 Pg: 169 Chap: 12 Para: 12.8.3 A. Refusal Speed B. Ground Minimum Control Speed C. Torque D. 3 Eng Ft/NM |
D
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224. The AF IMT 4108 will be completed whenever the navigator completes the __________.
Ref: AFI 11-2C-130 Vol 3 Pg: 169 Chap: 12 Para: 12.9.2 A. AF IMT 4125, Range Control Chart B. AF IMT 4091, Mission Data C. AF IMT 4116, C-130 Flight Plan and Record D. AF IMT 4053, INS Flight Plan and Log |
C
|
|
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225. Authority to use the Hostile Environment Kit and Repair Procedures is granted by OG/CC/CD for Operations; this authority is documented on the:
Ref: AFI 11-2C-130 Vol 3 Pg: 173 Chap: 12 Para: 12.10.1 A. FRAG B. SPINS C. Air Tasking Order D. Both A and C |
D
|
|
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226. Air Force policy is to conserve aviation fuel when it does not adversely affect ________, ______________, or _______________.
Ref: AFI 11-2C-130 Vol 3 Pg: 207 Chap: 14 Para 14.2. A. Structural limitations, flight duty period (FDP), stall speed B. Aircraft gross weight, DV missions, flight safety C. Takeoff time, sortie completion, flight time D. Training, flight safety, operational readiness |
D
|
|
|
227. Aircrews will consider delaying engine start on all departures whenever practical to minimize fuel consumption.
Ref: AFI 11-2C-130 Vol 3 Pg: 207 Chap: 14 Para 14.2.5. A. True B. False |
A
|
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228. Day VMC En-Route. Fly no lower than ___________ (or __________ IAW paragraph 16.4.4.8) modified contour altitude above terrain using visual references and radar altimeter.
Ref: AFI 11-2C-130 Vol 3 Pg: 217 Chap: 16 Para: 16.4.1.2. A. 500 feet MSL, 300 feet AGL B. 300 feet AGL, 100 feet AGL C. 500 feet AGL, 300 feet AGL D. 500 feet MSL, 300 feet MSL |
C
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229. Night VMC En-Route (Non-NVGs). Fly no lower than an indicated altitude of ________-feet above the highest obstruction to flight (man-made obstacle, terrain feature, or spot elevation), or _____-feet plus one chart contour interval above the highest depicted terrain contour, whichever is highest, within the tactical corridor to include the aircraft turn radius over each point.
Ref: AFI 11-2C-130 Vol 3 Pg: 217 Chap: 16 Para: 16.4.1.3. A. 500/400 B. 400/300 C. 500/300 D. 1,000/500 |
A
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230. NVG Enroute. Fly no lower than an indicated altitude of _________feet abouve the highest spot terrain elevation, or __________ feet plus one chart contour interval above the highest depicted terrain contour, whichever is higher, within the tactical corridor.
Ref: AFI 11-2C-130 Vol 3 Pg: 217 Chap: 16 Para: 16.4.1.4. A. 400/300 B. 500/300 C. 500/400 D. 1,000/500 |
C
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231. If either the pilots' NVGs, SCNS, pressure altimeter, or radar altimeter fail, climb to MSA until resolving the problem. In addition, climb to MSA to resolve any T.O. 1C-130(x)/(x)-1 Section III procedures, commensurate with the tactical situation.
Ref: AFI 11-2C-130 Vol 3 Pg: 217 Chap: 16 Para: 16.4.1.4 A. True B. False |
A
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232. Plan MSA at an indicated altitude of _____-feet above the highest obstruction to flight (man-made obstacle, terrain feature, or spot elevation), or _____-feet plus one chart contour interval above the highest depicted terrain contour, whichever is highest, within _____ of route centerline to include the aircraft turn radius.
Ref: AFI 11-2C-130 Vol 3 Pg: 218 Chap: 16 Para: 16.4.1.5 A. 400/300/5 NMs B. 400/300/3 NMs C. 500/400/5 NMs D. 500/400/3 NMs |
C
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233. To compute ESA, add _____ feet (_____ feet in mountainous terrain) to the elevation of the highest obstruction to flight within _____ NMs either side of the planned route centerline. An ESA will be computed for the route and conspicuously annotated on the chart.
Ref: AFI 11-2C-130 Vol 3 Pg: 219 Chap: 16 Para: 16.4.1.7 A. 500/1,000/10 B. 1,000/2,000/22 C. 500/1,000/22 D. 1,000/2,000/10 |
B
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234. Airdrops will not be conducted below the following altitudes:
Ref: AFI 11-2C-130 Vol 3 Pg: 219 Chap: 16 Para: 16.4.2 A. Day VMC Drop Altitude B. Night VMC Drop Altitude C. IMC Drop Altitude D. All of the above |
D
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235. Low Altitude Approach maneuvers may be flown on continuation training and operational missions with passengers aboard. In all cases plan to roll out on final at __________ speed no lower than _____ ft _____.
Ref: AFI 11-2C-130 Vol 3 Pg: 224 Chap: 17 Para: 17.6 A. threshold/500/AGL B. approach/150/AGL C. threshold/500/MSL D. approach/150/MSL |
B
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236. EROs will not be conducted simultaneously through the __________ door and __________ door.
Ref: AFI 11-2C-130 Vol 3 Pg: 225 Chap: 17 Para: 17.8.1.[W] A. paratroop doors/cargo ramp and door/crew entrance door B. crew entrance door/any other airplane C. crew entrance door/paratroop doors/cargo ramp and door D. EROs won’t be conducted through any door |
C
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237. During ERO procedures, use __________ and __________ to enhance safety at night as the situation dictates.
Ref: AFI 11-2C-130 Vol 3 Pg: 225 Chap: 17 Para: 17.8.1.1.3 A. formation/taxi lights B. formation/strobe lights C. landing/taxi lights D. wing leading edge/taxi lights |
D
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238. When personnel on-load and off-load through the crew entrance door, station a crewmember (normally the loadmaster) on interphone with cord held taut at approximately ______-feet at an angle of _____ degrees from the aircraft axis.
Ref: AFI 11-2C-130 Vol 3 Pg: 226 Chap: 17 Para: 17.8.1.6 A. 20/45 B. 45/20 C. 50/45 D. 45/50 |
A
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239. Combat Off-load Method “A” Procedures. A taxiway or ramp at least ______ feet long is required, however, _____ feet is desired to provide a margin of safety.
Ref: AFI 11-2C-130 Vol 3 Pg: 227 Chap: 17 Para: 17.8.2.1.1[C] A. 300/500 B. 500/1000 C. 1000/1500 D. 1500/2000 |
B
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240. NVG Airland. Coordinated actions during the final segment of an NVG __________ and _________ are critical.
Ref: AFI 11-2C-130 Vol 3 Pg: 230 Chap: 17 Para: 17.12.1.2. A. takeoff/landing B. approach/departure C. approach/landing D. takeoff/departure |
C
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241. NVG Operations. For tactical VFR approaches, bank angle will not exceed _____ degrees and the aircraft will not descend below _____ AGL until rolled on final.
Ref: AFI 11-2C-130 Vol 3 Pg: 230 Chap: 17 Para: 17.12.1.3. A. 30/150 ‘ B. 45/150’ C. 30/300 ‘ D. 45/300’ |
B
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242. NVG Operations. IMC Approaches. The transfer of aircraft control for the landing will be no lower than _____.
Ref: AFI 11-2C-130 Vol 3 Pg: 230 Chap: 17 Para: 17.12.1.4 A. 300’ AGL B. 300’ MSL C. 500’ AGL D. 500’ MSL |
A
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243. Minimum taxi interval is _____ aircraft length with four engines operating and _____ aircraft lengths with two engines operating.
Ref: AFI 11-2C-130 Vol 3 Pg: 232 Chap: 18 Para: 18.4.1 A. one/two B. two/one C. three/four D. four/three |
A
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244. Formations. At no time will aircraft be operated within _____ feet of another aircraft.
Ref: AFI 11-2C-130 Vol 3 Pg: 232 Chap: 18 Para: 18.7.1. A. 300 B. 500 C. 1000 D. 1500 |
B
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245. When flying at night, potential for spatial disorientation increases with:
Ref: AFI 11-2C-130 Vol 3 Pg: 233 Chap: 18 Para: 18.10.2.5[W] A. Rapid changes in airspeed B. Bank angles C. Changing "G" loads D. All of the above |
D
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246. Do not perform touch-and-go landings during formation recoveries unless:
Ref: AFI 11-2C-130 Vol 3 Pg: 234 Chap: 18 Para: 18.14[W] A. you are lead aircraft B. if all aircraft are clear of the runway C. you are at least five miles in trail D. Never |
D
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247. After Slowdown, element leads will not exceed _____ degrees of bank.
Ref: AFI 11-2C-130 Vol 3 Pg: 235 Chap: 18 Para: 18.18.2 A. 5 B. 10 C. 15 D. 20 |
B
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248. Analyze pre-drop gross weight to determine if obstructions can be cleared with __________.
Ref: AFI 11-2C-130 Vol 3 Pg: 236 Chap: 18 Para: 18.18.3[W] A. one engine inoperative B. two engines inoperative C. three engine climb speed D. obstacle clearance speed |
A
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249. CDS Airdrops. It is not recommended to drop CDS at gross weights less than _____ pounds.
Ref: AFI 11-2C-130 Vol 3 Pg: 252 Chap: 19 Para: 19.29.1. A. 103,000 B. 104,000 C. 105,000 D. 109,000 |
B
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250. Towed Parachutist. The PIC must consider density altitude, aircraft weight, position in formation, or other factors deemed important in determining what flap setting between _____ and _____ percent should be used.
Ref: AFI 11-2C-130 Vol 3 Pg: 259 Chap: 19 Para: 19.39.4[W] A. 0/50 B. 14/50 C. 50/100 D. 0/100 |
C
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