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cv-22 > Volume 3 > Flashcards

Volume 3 Flashcards

1
Q

What section of the H–60 is designed to give a smooth airflow induction for cooling major
aircraft systems and subsystem components?

A

Main rotor pylon

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2
Q

The H–60 stabilator vibration absorber is attached to the

A

right stabilator attachment fitting.

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3
Q

The roll vibration absorbers on the H–60 are installed under the

A

main landing gear drag beam support fairings.

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4
Q

Following installation, the H–60 vibration absorber that requires a tuning weight adjustment
using the 8500 Balancer/Analyzer and functional check flight is the

A

cabin

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5
Q

The attachment point for the tail wheel assembly on the H–60 tail landing gear is the

A

fork assembly

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6
Q

What allows for thermal expansion when the brakes on an H–60 are OFF?

A

Master cylinder.

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7
Q

Before servicing an H–60 landing gear strut with nitrogen, you must ensure there

A

are no hydraulic fluid leaks

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8
Q

To avoid placing undue stress on the brake assembly when servicing the upper stage of the
shock strut, you need to

A

release the parking brake

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9
Q

Before you apply external electrical power to perform an operational check of an H–60’s
brake system, you must first check the clearance around the

A

stabilator.

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10
Q

To operationally check the H–60 hydraulic system during ground operations, you use the

A

backup hydraulic system

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11
Q 
When the No. 1 hydraulic system on an H–60 fails, the pressure switch that will send a
signal to the logic module is located in the
A

transfer module.

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12
Q

The utility module on the H–60 connects hydraulic pressure to the

A

second stage of the tail rotor (TR) servo.

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13
Q 
The H–60 thermal relief valve protects the pilot-assist servo module from thermal
expansion of the hydraulic fluid
A

during storage

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14
Q

When pressed, the H–60 servo jam simulation button causes the

A

No. 1 or No. 2 PRI SERVO PRESS caution capsule to illuminate

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15
Q

What type of hydraulic leakage is defined as “Fluid leakage is such that hydraulic reservoir
levels may be dangerously lowered or depleted during normal operation, or a fire hazard may be
created, or the air worthiness of the helicopter may be otherwise affected”?

A

Excessive

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16
Q

The capacity of the cargo hook on the H–60 is

A

8000 pounds

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17
Q

The explosive cartridge (squib) on the H–60 cargo hook is used to

A

release the load during an emergency.

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18
Q

When the explosive squib is fired, the H–60 CARGO HOOK OPEN light will extinguish
when

A

a new squib is installed.

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19
Q

The release mode that is not applicable to the H–60 cargo hook is

A

standard

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20
Q

The hydraulic fluid for the H–60 rescue hoist is cooled by

A

a continuously running heat exchanger fan

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21
Q

To avoid injury and prevent cable fouling when raising or lowering the rescue hoist cable
on an H–60, you should use

A

leather gloves and maintain tension on the cable.

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22
Q

What is the most likely cause of a birdcaged rescue hoist cable on an H–60?

A

Hook bearing not rotating freely

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23
Q

On the H–60, the valve type used to mix engine or auxiliary power unit bleed-air with the
ambient air to obtain the desired temperature is

A

bleed-air mixing

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24
Q

H–60 fire detector sensors react to

A

blue and red light.

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25
Q

The windshield anti-ice system heating elements on the H–60 will heat the windshield
surface to a temperature of

A

70 – 115F.

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26
Q

When you place an H–60’s WINDSHIELD ANTI-ICE COPILOT switch to the ON
position, you should feel heat on the copilot’s windshield in approximately

A

5 minutes

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27
Q

The type of self-sealing valves installed in the H–60 fuel lines to contain the fuel in case of
a helicopter crash or malfunction is

A

breakaway

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28
Q

The H–60 fuel system pump that primes all fuel lines (if prime is lost) and acts as an
auxiliary power unit (APU) boost for APU starts and operation is

A

prime boost.

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29
Q

The submerged fuel boost system on the H–60 operates in conjunction with the

A

engine-driven boost pump.

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30
Q

When the H–60 fuel boost pump is OFF, loss of engine fuel line prime is prevented by a

A

check valve on the submerged fuel boost pump

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31
Q

Flow of fuel in the H–60 fuel system is directed by the fuel

A

management package.

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32
Q

The amount of useable fuel the H–60 internal auxiliary fuel tank will hold if it is single
point refueled is

A

170 gallons.

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33
Q

On the H–60, fuel will automatically transfer when

A

one main fuel tank is at 887 pounds and the other is at less than 1,000 pounds.

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34
Q

The centrifugal-type fuel transfer pumps on the H–60 helicopter are powered by

A

115 VAC.

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35
Q

When the H–60 refuel probe is extended, the fuel from the retract side of the probe flows to
the

A

No. 2 main fuel tank

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36
Q

The amount of fuel that should remain in the main tanks of an H–60 after the fuel dump
pumps shut off is

A

172 pounds.

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37
Q

The item used as the dielectric in the H–60 fuel quantify indicating system is

A

fuel.

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38
Q

If, on an H–60 fuel system, you want to remove 28 volts direct current (VDC) power, deenergize
the fuel warning conditioner relays, and cause the No. 1 and No. 2 FUEL LOW capsules
to illuminate, you would press the FUEL

A

IND TEST push-button on the miscellaneous switch panel.

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39
Q

In comparison to other aircraft systems, troubleshooting the fuel system is more difficult
because

A

the mechanical components are hard to access

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40
Q

The generator kilovolt amperage rating of the auxiliary power unit on the H–60 is

A

20/30

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41
Q

The type of protection that functions only during ground operation of the No. 1 and No. 2
generator control units on the H–60 is

A

underfrequency

42
Q

On the H–60, 115-VAC, B-phase power is connected to the alternating current (AC)
essential bus by the

A

XFR relay

43
Q

The No.1 and No.2 direct current (DC) power converters on the H–60 helicopter receive
power from

A

the alternating current (AC) primary buses

44
Q

To monitor the voltage capacity of the battery and generator, the H–60 flight engineer
console is equipped with a

A

battery-generator meter

45
Q

The H–60 direct current (DC) essential bus is connected to the battery bus by the

A

No. 2 DC essential bus relay

46
Q

To perform continuity and voltage checks on H–60 electrical systems, you would use

A

a multimeter.

47
Q

What electrical check would you use to determine the amount of resistance (ohms) in a
particular wire or component on an H–60?

A

Continuity.

48
Q

What electrical check would you use to check for a specified amount of alternating current
(AC) or direct current (DC) voltage in a particular wire or component on an H–60?

A

Voltage

49
Q

Before performing an H–60 electrical continuity check, you must remove all power from
the circuit you are checking. Failure to do this could result in damage to the

A

multimeter.

50
Q

What power source backs up the No. 1 and No. 2 generators on the H–60?

A

Auxiliary power unit (APU) generator.

51
Q

The pin filter adapters in the H–60 alternating current (AC) electrical system are designed to
filter

A

electromagnetic pulses

52
Q

The back panel of the H–60 central display unit (CDU) is equipped with

A

eight fuses.

53
Q

The H–60 instrument that is part of the global positioning system (GPS) is the

A

horizontal situation indicator (HSI).

54
Q

You externally zero the pointer on the H–60 vertical speed indicator by adjusting the screw
in the

A

lower left corner of the indicator

55
Q

The indicator range of the barometric altimeters on the H–60 is between

A

1,000 to 50,000 ft

56
Q

To check the H–60 central display unit (CDU) dimming feature, you would use

A

a flashlight.

57
Q

A main rotor (MR) blade on an H–60 is allowed to move about its axis for pitch changes by
the

A

elastomeric bearing

58
Q

When an H–60 damper and reservoir are fully serviced, the indicator will show full

A

gold.

59
Q

When the H–60 main rotor (MR) is rotating, centrifugal force will throw the droop stops out
and permit increased vertical movement of the blades when the rotation percentage MR speed
(Nr) is

A

70 to 75 percent.

60
Q

The tail rotor (TR) on the H–60 is canted upward

A

20 degrees

61
Q

The H–60 pilot is alerted to a de-ice system malfunction by a

A

FAIL flag on the ice-rate meter

62
Q

Vibration is best defined as the periodic back and forth movement of a component caused
by

A

unbalance or external forces

63
Q

Vibration frequency is the number of cycles completed in

A

a specified period of time.

64
Q

What readings do you use to find the location and amount of imbalance on an H–60?

A

Amplitude and phase angle measurements

65
Q

The most probable cause of a low-frequency vibration is

A

a damaged or out-of-balance main rotor (MR)

66
Q

What type of vibration frequency would an out-of-balance H–60 tail rotor drive shaft cause?

A

Medium

67
Q

High-frequency vibrations on the H–60 helicopter normally come from

A

a damaged main module

68
Q

Longitudinal movement of the H–60 helicopter is accomplished by movement of the

A

cyclic control

69
Q

The H–60 cyclic stick feature that allows the pilot to slew the stabilator trailing edge up
without letting go of the stick is a(n)

A

manual slew-up switch.

70
Q

The H–60 flight control feature that will counteract the pitching movement resulting from
the vertical lift of the canted tail rotor (TR) is the

A

yaw to longitudinal mixing

71
Q 
On the H–60, the yaw stability augmentation system (SAS) command comes from an
alternating current (AC)-powered
A

yaw rate gyro.

72
Q

The statement that best describes flight control component proof torqueing is

A

b. after torqueing and installing a cotter pin on a flight control, reduce the torque to half of the
specified torque and then check to see whether the bolt head will turn.

73
Q

On an H–60, what screw threaded component’s procedures are identified by ** SC
**?

A

Safety Critical

74
Q

During an H–60 main rotor rig check, the item you use to inspect all safety critical parts is

A

a 10-power magnifying glass

75
Q

You are performing a tail rotor (TR) rig on an H–60. You are ready to make adjustments to
the TR cable tension. You make these adjustments at the turnbuckles located

A

in front of the tail cone.

76
Q

You are performing a tail rotor (TR) rig on an H–60. To do this properly you must have a
bias of

A

3 degrees

77
Q

You are troubleshooting the directional control pedals on an H–60 and the problem still
persists. Your next course of action will be to

A

perform a tail rotor rig check

78
Q 
The T700 engine module that extracts most of the energy from the exhaust gases for output
power is the
A

power turbine

79
Q

Which sumps are used for the emergency oil system on the T700 engine?

A

A and B only

80
Q

The internal bypass flow in the T700 fuel boost pump provides approximately

A

twice the maximum fuel-flow.

81
Q

The type of fuel pressure the T700 engine electrical filter bypass sensor senses is

A

differential.

82
Q

The T700 engine component that stops fuel-flow after sensing an overspeed condition is the

A

digital electrical control (DEC).

83
Q

The thermocouple harness on the T700 engine is a

A

one-piece assembly with seven non-removable probes

84
Q

The hydromechanical unit actuating system on the T700 engine will open the start bleed
valve when gas generator speed (Ng) goes below

A

87 percent.

85
Q

The scroll vanes of the T700 engine are anti-iced by

A

hot scavenge oil

86
Q

The H–60 auxiliary power unit (APU) component protected by a 10-micron inlet filter is the

A

fuel pump

87
Q

If you have a problem during H–60 auxiliary power unit (APU) start or operation, what
color will the electronic sequence unit’s (ESU) built-in test equipment (BITE) indicators change
to illustrate the problem?

A

Black to white.

88
Q 
If you find it is difficult to pull the input module free from the main module when removing
the input module from an H–60 power train, you can help break the input module loose using
A

bolts.

89
Q

On the H–60, filtered oil is provided to all main transmission bearings and gears by the

A

integral sump lubrication system

90
Q

If the main transmission on an H–60 suffers a total oil loss, it can operate at cruise for

A

30 minutes

91
Q

The main transmission on the H–60 is equipped with

A

two lubrication pumps operating in parallel

92
Q 
The pressure side of the H–60 main transmission lubrication pumps supplies oil in gallons
per minute (gpm) and pounds per square inch (psi) at a rate of
A

15 gpm at 50 – 55 psi

93
Q 
On the H–60, the oil between the main module and the passages to the input modules,
accessory modules, and generators is divided by the
A

main module manifold.

94
Q

The section of the tail drive shaft on an H–60 that contains interchangeable shafts is

A

II

95
Q

The H–60 tail gearbox changes the angle of drive by

A

105 degrees

96
Q

What is indicated if the red fire extinguisher thermal discharge indicator is missing?

A

One or both fire bottles have discharged

97
Q

What is the operational pressure range, in pounds per square inch (psi), of the tail wheel
tire?

A

115–125

98
Q

If elastomer extrusion is identified on an elastomeric bearing, the bearing should be
replaced

A

within the next 50 flight hours

99
Q

What TO should you consult for loading and offloading your helicopter on a transport
aircraft?

A

The –9 TO of the aircraft you are using for transport

100
Q

What aircraft can the H–60 be air shipped on?

A

C–17, C–5.

cv-22 (4 decks)

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