Volume Three F16's

Front 1

the emergency power unit provides a self contained backup source of

Back 1

aircraft electrical and hydraulic power

Front 2

how long can emergency power unit operate in the monopropellent mode

Back 2

ten minutes

Front 3

the epu operation in the bleed air mode is intennded to be

Back 3

used for ground functional test

Front 4

what is the main electrical component of the epu system

Back 4

speed controller

Front 5

all metal parts of the hydrazine fuel tank are constructed of

Back 5

stainless steel

Front 6

at what pressure does the epu nitrogen valve regulate nitrogen pressure

Back 6

400 plus or minus 20 psi

Front 7

the emergency generator supplies power to the

Back 7

essential buses

Front 8

the liquid oxygen fill valve is a combination fill, buildup and

Back 8

vent valve

Front 9

the liquid oxygen fill valve is always in the buildup position except

Back 9

during servicing

Front 10

the liquid oxygen system heat exchanger is mounted

Back 10

under the right console in each cockpit

Front 11

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

Back 11

intergrated terminal block

Front 12

what indicatoin does the pilot receive from the oxy flow indicator when oxygen is flowing within the system

Back 12

blinking

Front 13

a path from the liquid oxygen probes to the quantity indicator on the jet is provided by

Back 13

coaxial cables

Front 14

the oxy low warning light illuminates

Back 14

at a lox quantity level of less then 0.5 leters

Front 15

the voids and clearances between the center conductor and the outer tube of the fire detection set sensing elements are filled with

Back 15

a temperature sensitive salt mixture

Front 16

the fire detection set sensing elements on the jet have an alarm temperature of

Back 16

765 degrees f

Front 17

what symbol does the head up display project when a fire condition is detected

Back 17

WARN

Front 18

how long does pure halon flow to the fuel tanks before the fuel inerting shutoff valve closes

Back 18

20 seconds

Front 19

how many separate fluid cambers are in the hydraulic system a reservoir

Back 19

two

Front 20

the fluid quantity gage on the hydraulic system a reservoir displays what quantity of measure

Back 20

percent of full fluid level

Front 21

which valve relieves excessive hydraulic pressure due to thermal expansion in to system return

Back 21

reservoir service manifold relief

Front 22

the delievery rating of one of the adg mounted hydraulic pumps is

Back 22

42.5 gpm at 3100 psi

Front 23

the hydraulic system a pressure filter manifold is located

Back 23

in the right mlg wheel well

Front 24

what prevents fluid loss when the filter bowl and element are removed from the hydrauilc system a pressure manifold

Back 24

internal shutoff valve

Front 25

what type of accumulators are the flight control accumulators

Back 25

piston type

Front 26

which valve in the hydraulic system a ensures epu pump flow is not supplied to the ground test stand if connected during epu operation

Back 26

ground test manifold pressure check

Front 27

hydraulic fluid for operation of the speed brakes is supplied by hydraulic

Back 27

system a only

Front 28

which valves in the hydraulic system b prevent fluid flow from one jet fuel starter/ brake accumulator to the other

Back 28

jfs pressure check

Front 29

the jet fuel starter motor anticavitation check valve prevents motor cavitation by directing flow to the motor inlet whenever return pressure

Back 29

exceeds inlet pressure

Front 30

the jfs/brake integral externally powered manually operated hydraulic pump draws hydraulic fluid from the

Back 30

b system return filter manifold

Front 31

the hydraulic pressure transmitters on the jet are located

Back 31

in the right and left mlg wheel wells

Front 32

the hydrauilc pressure indicator consists of a direct reading dial with graduations from 0-

Back 32

4000

Front 33

on the 16 the hydraulic power required for normal operatoin during main landing gear retraction is supplied by what system

Back 33

hyd system b only

Front 34

what landing gear component free falls into the extended position

Back 34

main landing gear

Front 35

which main landing gear component houses the downlock mechanism.

Back 35

drag brace

Front 36

the main landing gear downlock mechanism holds the drag brace on center with an actuator

Back 36

spring

Front 37

on each main landing gear shock strut the air valve faces

Back 37

outboard and the uplock roller faces foward

Front 38

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

Back 38

self contained trunnion pins

Front 39

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

Back 39

sequence valves

Front 40

how is the landing gear handle locked in the up position

Back 40

mechanicaly

Front 41

the landing gear selector valve is a

Back 41

two position valve with a pneumatically operated bypass

Front 42

the landing gear hydraulic isolation valve isolates the landing gear portion of hydraulic system b from the rest of the system to reduce hydraulic system

Back 42

combat vuneralbility

Front 43

what landing gear component prevents extend hydraulic pressure from reaching the nose landing gear retract actuator until the nlg door is open

Back 43

nlg mechanical sequence valve

Front 44

which components of the brake assembly are keyed on their outside diameters to the wheel

Back 44

rotating discs

Front 45

the brake control unit receives electrical signals

Back 45

from the brake pedal position transducers and anti skid control unit

Front 46

what warns the pilot of an anti skid system failure

Back 46

caution light

Front 47

prebraking of the main wheels is provided to

Back 47

eliminate gyroscopic movements applied to the mlg during retraction

Front 48

the solenoid operated parking valve ports hydrauilc pressure from system b or

Back 48

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

Front 49

the arresting hook is controlled how

Back 49

electronically controlled and pneumatically actuated

Front 50

what arresting hook component provides a means of locking and releasing the arresting hook

Back 50

arresting hook uplock roller

Front 51

what does the arresting hook caution light indicate

Back 51

arresting hook is not up and locked

Front 52

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

Back 52

32 degrees left or right

Front 53

which comp. of the nosewheel steering system transforms the pilots steering commands to electrical signals that drive the hydraulic linear actuator

Back 53

command potentiometer

Front 54

which comp. of the nosewheel steering system routes signals to the steering control box indicating the position of the hydraulic linear actuator

Back 54

feedback potentiometer

Front 55

the hydrualic linear actuator receives hydraulic pressure from

Back 55

hyd. system b only

Front 56

all contol surface actuators the lef pdu and the isa's utilize power from

Back 56

hydraulic systems a and b

Front 57

which does not have quadrupel redundancy input signals into the flight control computer

Back 57

autopilot

Front 58

which flight control component contains microprocessor circuitry that provides a nonvolatile memory storage capability

Back 58

flight control computer