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
2
Q
How long Can the F-16 emergency power unit operate in the monopropellant mode
A
10 minutes
3
Q
The f-16s emergency power units operation in the bleed air mode is intended to be
A
Use for ground functional test
4
Q
What is the main electrical component of the F-16s emergency power unit system
A
Speed controller
5
Q
All metal parts of the 16s hydrazine fuel tank are constructed of
A
Stainless steel
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
7
Q
The F-16s emergency generator supplies power to the
A
Essential buses
8
Q
The 16s liquid oxygen fill valve is a combination fill, build up, and
A
Vent valve
9
Q
The 16s liquid oxygen fill valve is always in the buildup position except
A
During servicing
10
Q
The 16s liquid oxygen system heat exchanger is mounted
A
Under the right console in each carpet
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
12
Q
What indication does the F-16 pilot receive from the OXY flow indicator when oxygen is flowing within the system
A
Blinking
13
Q
A path from the liquid oxygen probes to the quantity indicator on the 16 is provided by
A
Coaxial cables
14
Q
The 16 OXY LOW Warning light illuminates
A
At a LOX quantity level of less than .5 Liters
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
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
17
Q
The fire detection set sensing element on the F-16 have an alarm temperature of
A
765°F
18
Q
What symbol does the F-16 heads up display project when a fire condition is detected
A
WARN
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
20
Q
How many separate fluid chambers are in the F-16s hydraulic system a reservoir: One, two, three, or four?
A
Two
21
Q
The fluid quantity gauge on the 16s hydraulic system A reservoir displays what quantity of measure
A
Percent of full fluid level
22
Q
Which valve on the F-16 releases excessive hydraulic pressure due to thermal expansion into system return
A
Reservoir service manifold relief
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
24
Q
The F-16s hydraulic system A pressure filter manifold is located
A
In the right main landing gear wheelwell
25
What prevents fluid loss when the filter bowl and element are removed from the F-16s hydraulic system A pressure manifold
Internal shut off valve
26
The 16s flight control accumulators are
Piston type
27
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
Ground test manifold pressure check
28
Hydraulic fluid for operation of the 16 speedbrake is supplied by hydraulic
A system only
29
Which valves in the F-16 hydraulic system B prevent fluid flow from one jet fuel starter brake accumulator to the other
JFS pressure check valves
30
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
Exceeds inlet pressure
31
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
B system return filter manifold
32
The hydraulic pressure transmitters on the F-16 Are located
In the left and right main landing gear wheel wells
33
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
4000 PSI
34
On the F-16 the hydraulic power required for normal operation during main landing gear retraction is supplied by: A,B,Both, Either?
Hydraulic system B only
35
What F-16 landing gear component free falls into extended Position
Main landing gear
36
Which F-16 main landing gear component houses the down lock mechanism
Drag brace
37
The F-16 Main landing gear down lock mechanism holds the drag brace on center with an actuator
Spring
38
On each 16 main landing gear shock strut, the air valve faces
Outboard and the block roller lugs face forward
39
The 16 nose landing gear shock strut is connected to the aircraft by
Self-contained trunnion pins
40
What 16 components control landing gear and door operations to prevent interference during extension and retraction
Sequence valves
41
How is the 16 landing gear handle locked in the up position
Mechanically
42
The 16 landing gear selector valve is a
Two position valve with a pneumatically operated bypass
43
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
Combat vulnerability
44
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?
NLG mechanical sequence valve
45
Which components of the F-16s brake assembly are keyed on the outside diameters to the wheel
Rotating disks
46
The 16s brake control unit receives electrical signals
From the brake pedal position transducers and antiskid control unit
47
What warns the F-16 pilot of an antiskid system failure
Caution light
48
Prebaking of the 16 main wheels is provided to
Eliminate gyroscopic moments applied to the main landing gear during retraction
49
F-16 solenoid operated parking valve ports hydraulic pressure from system B or
One brake accumulator to one set of brake pistons in each wheel brake assembly
50
F-16 arresting hook is
Electrically controlled and pneumatically actuated
51
What F-16 arresting hook component provides a means of locking and releasing the arresting hook
Arresting hook up lock roller
52
What does the F-16 arresting hook caution light indicate
Arresting hook is not up and locked
53
F-16s nosewheel steering subsystem provides turning capability for the aircraft while it is on the ground allowing the aircraft to turn
32° left or right
54
Which component of the 16s nosewheel steering system transforms the pilots steering commands to electrical signals that drive the hydraulic linear actuator
Command potentiometer
55
Which component of the F-16s nosewheel steering system routes signals to the steering control box indicating the position of the hydraulic linear actuator
Feedback potentiometer
56
F-16s hydraulic linear actuator receives hydraulic pressure from
Hydraulic system B only
57
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
Hydraulic systems A And B
58
Which does not have quadruple redundancy input signals into the F-16 flight control computer
Autopilot
59
Which F-16 flight control component contains microprocessor circuitry that provides a non-volatile memory storage capability
Flight control computer
60
What provides the 16's flight controls with artificial feel
Beams and coil springs within sidestick controller transducers
61
Which F-16 flight control system electronic malfunction light remains on until malfunction is cleared, regardless of the caution light reset action taken
P, R, and Y
62
Which F-16 flight control component receives signals from the angle of attack transmitters
Electronic component assembly
63
How many pressure sensors does the F-16 pneumatic sensor assembly contain
Eight
64
The 16s flaperons extended as flaps when the
Aircraft is in the takeoff or landing configuration
65
F-16s aileron rudder interconnect gain is a variable function of
Angle of attack and Mach number
66
While the F-16 is in landing configuration, each speedbrake surface only opens to
43°
67
How many mechanical rotary actuators are located on each 16 wing leading edge
Four
68
Upon landing, the 16s leading-edge flaps are automatically position to
2° up
69
The internal fuel storage system on the F-16 consists of
Seven fuel tanks
70
Each of the external wing tanks on the F-16 holds
370 gallons of fuel
71
How many fuselage fuel tank drain valves are on the F-16
Seven
72
Which 16 fuel tanks equally provide fuel to the engine on-demand
Forward and aft reservoir
73
Into which fuel tanks does the F-16 external centerline transfer fuel
Left and right internal wing
74
What provides the refuel receptacle with an emergency disconnect feature during F-16 aerial refueling
Pressure relief valve
75
The fuel scavenge pumps on the F-16 move the residual fuel to the
Forward reservoir
76
The fuel scavenge pumps on the 16 receive their power from
Fuel bled off the boost pumps
77
The 16s fuel flow proportioner is powered by
Hydraulic system A
78
At what pressure does the F-16 fuel flow proportioner operate
19 psi
79
A thermal valve on the 16s fuel system heat exchanger outlet prevents the fuel temperature from exceeding
200°F
80
The vent and pressurization valve for the 16s External fuel tank is located on the inside of the
Vent Tank
81
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
Negative pressure relief valve
82
The ground air service connector For F-16 fuel tank pressurization is located
In the right main landing gear wheelwell
83
What provides a redundant means of relieving excess pressure should be F-16s fuel system internal vent and pressurization valve fail
Remote-sensing relief valve
84
Which switch provides a way of testing the F-16s fuel temperature subsystem
Fuel hot test switch on the ground test panel
85
The dual pointer markers on the 16th fuel quantity indicator are labeled
FR and AL
86
On the F-16 Flammable vapor air mixtures for JP-8 are possible at all temperatures above
100°F
87
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
Internal nonvented areas
88
On an F-16, which fuel leak conditions do not require immediate repair
Conditions one and two
89
On the F-16, the F 100 Pratt & Whitney 220 engine compressor contains
Three stages of low-pressure compression and 10 stages of high-pressure compression
90
On the 16, one benefit of the modular construction of the Pratt & Whitney 220 engine is the Ease of removal and replacement of
Faulty engine sections
91
If the 16's Pratt & Whitney 220's digital electronic engine control fails, engine control transfers to
Secondary mode of operation
92
After initial ignition, the main ignition spark on the 220 engine is suppressed by
Combustion chamber pressure
93
On the F-16, what is the position of the F110 GE 100 anti-ice valve when Electrical power is removed
Open
94
On the F-16 with a GE 100 engine, which condition causes the F-16s engine warning light to illuminate
Engine revolutions per minute of 59%
95
The capacity of an F-16s oil tank with the GE 100 engine is
3.0 gallons
96
How many mounting pads provide for the attachment of the F-117's airframe mounted accessory drive to the airframe
Three
97
The oil level in which F-117 component can be checked by pressing a check switch
Auxiliary power unit
98
During activation of the F-117's emergency power unit, automatic operation of the auxiliary generator is controlled by
The altitude pressure switch
99
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?
Left main landing gear wheel well
100
The F-117's oxygen system low level switch senses when the liquid quantity in the system decreases to
0.5 L
101
The responder portion of each fire detector element on the F-117 contains two
Pressure operated switches
102
What is the alarm temperature of the over heat sensing elements located in the F-117's engine compartment
400°F
103
To prevent ignition of fuel vapor, the Fuel inerting system on the F-117 uses
Halon
104
The F-117 Halon reservoir relief valve is designed to crack open at
600 psi
105
Hydraulic power system number one on the F-117 is divided into subsystems 1A and 1B by
Reservoir number one
106
During F-117 landing gear retraction, how long is hydraulic pressure maintained in the main and nose gear actuators
Until all door latches are fully locked
107
Emergency extension of the F-117's landing gear is achieved through the use of
A cable operated release system
108
On the F-117 nosewheel steering caution light illuminates to indicate
NWS has been disengaged
109
Braking force on the F-117 is transmitted to each main landing gear wheel by
For rotating disks
110
After any left or right deflection the Tailhook on the F-117 is returned to the center position by the
Swivel fitting
111
The Tailhook air bottle on the F-117 is charged by
The pressurized air start system
112
Which F-117 flight control computer input signal is received by way of a single channel
Autopilot
113
Which of the four F-117 nose mounted probe assemblies is slightly smaller than the other three
Channel C
114
How many flight control integrated servoactuators are on the F-117
Six
115
How many controlling servovalves are contained in each F-117 integrated servo actuator
Three
116
What two types of flight control movements are controlled by the F-117's elevons
Pitch and roll
117
What F-117 component contains test control switches and alphanumeric message display that tells maintenance personnel to perform certain flight control test operations
Flight control system panel
118
Normally the left feed tank on the F-117 supplies fuel to the
Left engine
119
The fuel boost pumps on F-117 operate
Anytime AC power is supplied to the aircraft
120
The F-117 fuel low-level sensing thermistors are mounted
Directly above the other in each feed tank
121
On the F-117 aircraft pressurized air from the air pressure regulator is introduced directly into the
Vent box
122
On the F-117 how many turbine stages drive the fan rotor on the F404 GE F1 D2 engine
One
123
On the F-117 aircraft what are mounted on the F404 GE F1D2 fan stator at the five and 8 o'clock positions
Two fan speed (N1) transmitters
124
On the F-117 the electronic processor unit for the structural tracking and engine monitoring system is powered by
28 VDC
