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WAPS Testing > 2A353 Volume 3 > Flashcards

2A353 Volume 3 Flashcards

1
Q

The F-16s emergency power unit provides a self-contained back up source of

A

Aircraft electrical and hydraulic power

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2
Q

How long Can the F-16 emergency power unit operate in the monopropellant mode

A

10 minutes

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3
Q

The f-16s emergency power units operation in the bleed air mode is intended to be

A

Use for ground functional test

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4
Q

What is the main electrical component of the F-16s emergency power unit system

A

Speed controller

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5
Q

All metal parts of the 16s hydrazine fuel tank are constructed of

A

Stainless steel

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6
Q

At what pressure does the F-16s emergency power unit nitrogen valve regulate nitrogen pressure

A

400+ or -20 pounds per square inch

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7
Q

The F-16s emergency generator supplies power to the

A

Essential buses

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8
Q

The 16s liquid oxygen fill valve is a combination fill, build up, and

A

Vent valve

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9
Q

The 16s liquid oxygen fill valve is always in the buildup position except

A

During servicing

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10
Q

The 16s liquid oxygen system heat exchanger is mounted

A

Under the right console in each carpet

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11
Q

What serves as a central interface for the upper and lower oxygen supply hoses, vest hose, and emergency oxygen hose on the 16s modified with pressure breathing for gravity system

A

Integrated terminal block

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12
Q

What indication does the F-16 pilot receive from the OXY flow indicator when oxygen is flowing within the system

A

Blinking

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13
Q

A path from the liquid oxygen probes to the quantity indicator on the 16 is provided by

A

Coaxial cables

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14
Q

The 16 OXY LOW Warning light illuminates

A

At a LOX quantity level of less than .5 Liters

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15
Q

What system malfunction causes the 16s liquid oxygen quantity indicator to rotate counterclockwise

A

Short to ground in the high-voltage side of the circuit

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16
Q

On the 16 the voids in clearances between the center conductor and the outer tube of the fire detection set sensing element are filled with

A

A temperature sensitive salt mixture

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17
Q

The fire detection set sensing element on the F-16 have an alarm temperature of

A

765°F

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18
Q

What symbol does the F-16 heads up display project when a fire condition is detected

A

WARN

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19
Q

How long does pure halon flow to the fuel tanks before the F-16s Fuel inerting shut off valve closes: 15 seconds, 20 seconds, 25 minutes, 30 minutes

A

20 seconds

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20
Q

How many separate fluid chambers are in the F-16s hydraulic system a reservoir: One, two, three, or four?

A

Two

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21
Q

The fluid quantity gauge on the 16s hydraulic system A reservoir displays what quantity of measure

A

Percent of full fluid level

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22
Q

Which valve on the F-16 releases excessive hydraulic pressure due to thermal expansion into system return

A

Reservoir service manifold relief

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23
Q

The delivery rating of one of the F-16 accessory drive gearbox mounted hydraulic pumps is

A

42.5 GPM at 3100 psi

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24
Q

The F-16s hydraulic system A pressure filter manifold is located

A

In the right main landing gear wheelwell

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25
Q

What prevents fluid loss when the filter bowl and element are removed from the F-16s hydraulic system A pressure manifold

A

Internal shut off valve

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26
Q

The 16s flight control accumulators are

A

Piston type

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27
Q

Which valve in the 16s hydraulic system A ensures emergency power unit pump flow is not supplied to the ground test stand if connected during EPU operation

A

Ground test manifold pressure check

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28
Q

Hydraulic fluid for operation of the 16 speedbrake is supplied by hydraulic

A

A system only

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29
Q

Which valves in the F-16 hydraulic system B prevent fluid flow from one jet fuel starter brake accumulator to the other

A

JFS pressure check valves

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30
Q

The F-16s jet fuel starter motor anti-cavitation check valve prevents motor cavitation by directing the flow to the motor inlet whenever return pressure

A

Exceeds inlet pressure

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31
Q

F-16’s Jet fuel starter/brake integral externally powered, manually operated hydraulic pump draws hydraulic fluid from the: b system pressure filter manifold, b system return filter manifold, a system return filter manifold, or B system reservoir

A

B system return filter manifold

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32
Q

The hydraulic pressure transmitters on the F-16 Are located

A

In the left and right main landing gear wheel wells

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33
Q

The F-16s hydraulic pressure indicator consists of a direct reading dial with graduations from zero to: 3000 PSI, 4000 PSI, 5000 psi, or 6000 PSI

A

4000 PSI

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34
Q

On the F-16 the hydraulic power required for normal operation during main landing gear retraction is supplied by: A,B,Both, Either?

A

Hydraulic system B only

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35
Q

What F-16 landing gear component free falls into extended Position

A

Main landing gear

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36
Q

Which F-16 main landing gear component houses the down lock mechanism

A

Drag brace

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37
Q

The F-16 Main landing gear down lock mechanism holds the drag brace on center with an actuator

A

Spring

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38
Q

On each 16 main landing gear shock strut, the air valve faces

A

Outboard and the block roller lugs face forward

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39
Q

The 16 nose landing gear shock strut is connected to the aircraft by

A

Self-contained trunnion pins

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40
Q

What 16 components control landing gear and door operations to prevent interference during extension and retraction

A

Sequence valves

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41
Q

How is the 16 landing gear handle locked in the up position

A

Mechanically

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42
Q

The 16 landing gear selector valve is a

A

Two position valve with a pneumatically operated bypass

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43
Q

F-16s landing gear hydraulic isolation valve isolates the landing gear portion of hydraulic system B from the rest of the system to reduce hydraulic system

A

Combat vulnerability

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44
Q

What F-16 landing gear component prevents extend hydraulic pressure from reaching the nose landing gear Retract actuator until the NLG door is open: Nose landing gear down lock switch, nose landing gear door sequence valve, landing gear selector valve, or nose landing gear mechanical sequence valve?

A

NLG mechanical sequence valve

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45
Q

Which components of the F-16s brake assembly are keyed on the outside diameters to the wheel

A

Rotating disks

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46
Q

The 16s brake control unit receives electrical signals

A

From the brake pedal position transducers and antiskid control unit

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47
Q

What warns the F-16 pilot of an antiskid system failure

A

Caution light

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48
Q

Prebaking of the 16 main wheels is provided to

A

Eliminate gyroscopic moments applied to the main landing gear during retraction

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49
Q

F-16 solenoid operated parking valve ports hydraulic pressure from system B or

A

One brake accumulator to one set of brake pistons in each wheel brake assembly

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50
Q

F-16 arresting hook is

A

Electrically controlled and pneumatically actuated

51
Q

What F-16 arresting hook component provides a means of locking and releasing the arresting hook

A

Arresting hook up lock roller

52
Q

What does the F-16 arresting hook caution light indicate

A

Arresting hook is not up and locked

53
Q

F-16s nosewheel steering subsystem provides turning capability for the aircraft while it is on the ground allowing the aircraft to turn

A

32° left or right

54
Q

Which component of the 16s nosewheel steering system transforms the pilots steering commands to electrical signals that drive the hydraulic linear actuator

A

Command potentiometer

55
Q

Which component of the F-16s nosewheel steering system routes signals to the steering control box indicating the position of the hydraulic linear actuator

A

Feedback potentiometer

56
Q

F-16s hydraulic linear actuator receives hydraulic pressure from

A

Hydraulic system B only

57
Q

All F-16 control surface actuators, the Leading edge flap power drive unit, and the integrated servo actuators utilize power from: B only, A only, both, or A except when emergency hydraulic pump is operating

A

Hydraulic systems A And B

58
Q

Which does not have quadruple redundancy input signals into the F-16 flight control computer

A

Autopilot

59
Q

Which F-16 flight control component contains microprocessor circuitry that provides a non-volatile memory storage capability

A

Flight control computer

60
Q

What provides the 16’s flight controls with artificial feel

A

Beams and coil springs within sidestick controller transducers

61
Q

Which F-16 flight control system electronic malfunction light remains on until malfunction is cleared, regardless of the caution light reset action taken

A

P, R, and Y

62
Q

Which F-16 flight control component receives signals from the angle of attack transmitters

A

Electronic component assembly

63
Q

How many pressure sensors does the F-16 pneumatic sensor assembly contain

A

Eight

64
Q

The 16s flaperons extended as flaps when the

A

Aircraft is in the takeoff or landing configuration

65
Q

F-16s aileron rudder interconnect gain is a variable function of

A

Angle of attack and Mach number

66
Q

While the F-16 is in landing configuration, each speedbrake surface only opens to

A

43°

67
Q

How many mechanical rotary actuators are located on each 16 wing leading edge

A

Four

68
Q

Upon landing, the 16s leading-edge flaps are automatically position to

A

2° up

69
Q

The internal fuel storage system on the F-16 consists of

A

Seven fuel tanks

70
Q

Each of the external wing tanks on the F-16 holds

A

370 gallons of fuel

71
Q

How many fuselage fuel tank drain valves are on the F-16

A

Seven

72
Q

Which 16 fuel tanks equally provide fuel to the engine on-demand

A

Forward and aft reservoir

73
Q

Into which fuel tanks does the F-16 external centerline transfer fuel

A

Left and right internal wing

74
Q

What provides the refuel receptacle with an emergency disconnect feature during F-16 aerial refueling

A

Pressure relief valve

75
Q

The fuel scavenge pumps on the F-16 move the residual fuel to the

A

Forward reservoir

76
Q

The fuel scavenge pumps on the 16 receive their power from

A

Fuel bled off the boost pumps

77
Q

The 16s fuel flow proportioner is powered by

A

Hydraulic system A

78
Q

At what pressure does the F-16 fuel flow proportioner operate

A

19 psi

79
Q

A thermal valve on the 16s fuel system heat exchanger outlet prevents the fuel temperature from exceeding

A

200°F

80
Q

The vent and pressurization valve for the 16s External fuel tank is located on the inside of the

A

Vent Tank

81
Q

Which F-16 fuel system valve provides a redundant means of allowing air into the vent tank thus guarding against instances of negative pressure within the fuel tanks

A

Negative pressure relief valve

82
Q

The ground air service connector For F-16 fuel tank pressurization is located

A

In the right main landing gear wheelwell

83
Q

What provides a redundant means of relieving excess pressure should be F-16s fuel system internal vent and pressurization valve fail

A

Remote-sensing relief valve

84
Q

Which switch provides a way of testing the F-16s fuel temperature subsystem

A

Fuel hot test switch on the ground test panel

85
Q

The dual pointer markers on the 16th fuel quantity indicator are labeled

A

FR and AL

86
Q

On the F-16 Flammable vapor air mixtures for JP-8 are possible at all temperatures above

A

100°F

87
Q

On the F 16, areas that are normally adjacent to fuel tanks or fuel lines and have no means of air circulation even though they are drained are considered

A

Internal nonvented areas

88
Q

On an F-16, which fuel leak conditions do not require immediate repair

A

Conditions one and two

89
Q

On the F-16, the F 100 Pratt & Whitney 220 engine compressor contains

A

Three stages of low-pressure compression and 10 stages of high-pressure compression

90
Q

On the 16, one benefit of the modular construction of the Pratt & Whitney 220 engine is the Ease of removal and replacement of

A

Faulty engine sections

91
Q

If the 16’s Pratt & Whitney 220’s digital electronic engine control fails, engine control transfers to

A

Secondary mode of operation

92
Q

After initial ignition, the main ignition spark on the 220 engine is suppressed by

A

Combustion chamber pressure

93
Q

On the F-16, what is the position of the F110 GE 100 anti-ice valve when Electrical power is removed

A

Open

94
Q

On the F-16 with a GE 100 engine, which condition causes the F-16s engine warning light to illuminate

A

Engine revolutions per minute of 59%

95
Q

The capacity of an F-16s oil tank with the GE 100 engine is

A

3.0 gallons

96
Q

How many mounting pads provide for the attachment of the F-117’s airframe mounted accessory drive to the airframe

A

Three

97
Q

The oil level in which F-117 component can be checked by pressing a check switch

A

Auxiliary power unit

98
Q

During activation of the F-117’s emergency power unit, automatic operation of the auxiliary generator is controlled by

A

The altitude pressure switch

99
Q

The F-117’s emergency power unit can be manually operated from the control switches in the: Left main landing gear wheelwell, right main landing gear wheelwell, right weapons bay, or left weapons bay?

A

Left main landing gear wheel well

100
Q

The F-117’s oxygen system low level switch senses when the liquid quantity in the system decreases to

A

0.5 L

101
Q

The responder portion of each fire detector element on the F-117 contains two

A

Pressure operated switches

102
Q

What is the alarm temperature of the over heat sensing elements located in the F-117’s engine compartment

A

400°F

103
Q

To prevent ignition of fuel vapor, the Fuel inerting system on the F-117 uses

A

Halon

104
Q

The F-117 Halon reservoir relief valve is designed to crack open at

A

600 psi

105
Q

Hydraulic power system number one on the F-117 is divided into subsystems 1A and 1B by

A

Reservoir number one

106
Q

During F-117 landing gear retraction, how long is hydraulic pressure maintained in the main and nose gear actuators

A

Until all door latches are fully locked

107
Q

Emergency extension of the F-117’s landing gear is achieved through the use of

A

A cable operated release system

108
Q

On the F-117 nosewheel steering caution light illuminates to indicate

A

NWS has been disengaged

109
Q

Braking force on the F-117 is transmitted to each main landing gear wheel by

A

For rotating disks

110
Q

After any left or right deflection the Tailhook on the F-117 is returned to the center position by the

A

Swivel fitting

111
Q

The Tailhook air bottle on the F-117 is charged by

A

The pressurized air start system

112
Q

Which F-117 flight control computer input signal is received by way of a single channel

A

Autopilot

113
Q

Which of the four F-117 nose mounted probe assemblies is slightly smaller than the other three

A

Channel C

114
Q

How many flight control integrated servoactuators are on the F-117

A

Six

115
Q

How many controlling servovalves are contained in each F-117 integrated servo actuator

A

Three

116
Q

What two types of flight control movements are controlled by the F-117’s elevons

A

Pitch and roll

117
Q

What F-117 component contains test control switches and alphanumeric message display that tells maintenance personnel to perform certain flight control test operations

A

Flight control system panel

118
Q

Normally the left feed tank on the F-117 supplies fuel to the

A

Left engine

119
Q

The fuel boost pumps on F-117 operate

A

Anytime AC power is supplied to the aircraft

120
Q

The F-117 fuel low-level sensing thermistors are mounted

A

Directly above the other in each feed tank

121
Q

On the F-117 aircraft pressurized air from the air pressure regulator is introduced directly into the

A

Vent box

122
Q

On the F-117 how many turbine stages drive the fan rotor on the F404 GE F1 D2 engine

A

One

123
Q

On the F-117 aircraft what are mounted on the F404 GE F1D2 fan stator at the five and 8 o’clock positions

A

Two fan speed (N1) transmitters

124
Q

On the F-117 the electronic processor unit for the structural tracking and engine monitoring system is powered by

A

28 VDC

WAPS Testing (35 decks)

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