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Airframe A&P 2024 > Ch. 14 - Aircraft Fuel Systems > Flashcards

Ch. 14 - Aircraft Fuel Systems Flashcards

1
Q

If a piston engine aircraft is fueled with Avgas of an insufficient octane rating, there will be an increased danger of _____________

  • insufficient combustion.
  • vapor lock.
  • detonation.
A

detonation.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 4

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2
Q

The primary purpose of a fuel tank sump is to provide a _____________

  • place where water and dirt accumulations in the tank can collect and be drained.
  • positive system of maintaining the design minimum fuel supply for safe operation.
  • reserve supply of fuel to enable the aircraft to land safely in the event of fuel exhaustion.
A

place where water and dirt accumulations in the tank can collect and be drained.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 7

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3
Q

What precautions must be observed if a gravity feed fuel system is permitted to supply fuel to an engine from more than one tank at a time?

  • Each tank must have a valve in its outlet that automatically shuts off the line when the tank is empty.
  • The fuel outlet ports of each tank must have the same cross sectional area.
  • The tank airspaces must be interconnected.
A

The tank airspaces must be interconnected.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 9

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4
Q

Before fueling an aircraft by using the pressure fueling method, what important precaution should be observed?

  • The truck pump pressure must be adjusted for minimum filter pressure.
  • The aircraft’s electrical system must be on to indicate quantity gauge readings.
  • The truck pump pressure must be correct for that refueling system.
A

The truck pump pressure must be correct for that refueling system.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 14, 16

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5
Q

In all types of fuel systems, all fuel tanks must be vented _____________

  • to each other.
  • to a jettison system.
  • to the atmosphere.
A

to the atmosphere.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 9

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6
Q

Entrained water in aviation turbine fuel is a hazard because of its susceptibility to freezing as it passes through the filters. What are common methods of preventing this hazard?

  • Micromesh fuel strainers and fuel heater.
  • Anti-icing fuel additives and fuel heater.
  • High-velocity fuel pumps and fuel heater.
A

Anti-icing fuel additives and fuel heater.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 7, 50

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7
Q

The primary purpose of an aircraft’s fuel jettison system is to quickly achieve a _____________

  • lower landing weight.
  • reduced fire hazard.
  • balanced fuel load.
A

lower landing weight.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 2

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8
Q

Fuel jettisoning is usually accomplished _____________

  • by gravity flow into the outboard wing tanks and overboard through a common outlet in each wing.
  • through individual outlets for each tank.
  • through a common manifold and outlet in each wing.
A

through a common manifold and outlet in each wing.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 16

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9
Q

Carburetor icing may be eliminated by which of the following methods _____________

  • ethylene glycol spray and heated induction air.
  • electrically heating air intake, ethylene glycol spray, or alcohol spray.
  • heated induction air.
A

heated induction air.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 3-4

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10
Q

What is one disadvantage of using aromatic aviation fuels?

  • Results in low fuel volatility.
  • A fuel inter-cooler is required.
  • Deteriorates rubber parts.
A

Deteriorates rubber parts.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 4

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11
Q

What markings are placed on or near each appropriate fuel filler cover on aircraft?

  • The tank capacity.
  • The correct type of fuel to be used.
  • The words “Aviation Fuel”.
A

The correct type of fuel to be used.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 51, 53

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12
Q

Which of the following precautions is most important during refueling operations?

  • Fuel to be used must be appropriately identified.
  • All electrical switches must be in the OFF position.
  • All outside electrical sources must be disconnected from the aircraft.
A

Fuel to be used must be appropriately identified.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 6

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13
Q

Why are jet fuels more susceptible to water contamination than aviation gasoline?

  • Jet fuel is lighter than gasoline; therefore, water is more easily suspended.
  • Condensation is greater because of the higher volatility of jet fuels.
  • Jet fuel has a higher viscosity than gasoline.
A

Jet fuel has a higher viscosity than gasoline.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 7-9

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14
Q

The vapor pressure of aviation gasoline is _____________

  • lower than the vapor pressure of automotive gasoline.
  • approximately 20 PSI at 100°F.
  • higher than the vapor pressure of automotive gasoline.
A

lower than the vapor pressure of automotive gasoline.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 3

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15
Q

What is the maximum vapor pressure allowable for an aircraft fuel?

  • 7 PSI
  • 3 PSI
  • 5 PSI
A

7 PSI

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 3

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16
Q

On an aircraft with an integral fuel take, the out most bay of the tank, located near the tip of the wing is used primarily _____________

  • as an overflow tank.
  • for extended range.
  • to fill in flight as needed for the purpose of lateral weight and balance.
A

as an overflow tank.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 13

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17
Q

Why are integral fuel tanks used in many large aircraft?

  • To facilitate servicing.
  • To reduce weight.
  • To reduce fire hazards.
A

To reduce weight.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 18, 21

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18
Q

Normal fuel cross-feed system operation in multi-engine aircraft

  • reduces contamination and/or fire hazards during fueling or defueling operations.
  • provides a means to maintain a balanced fuel load condition.
  • calls for jettisoning of fuel overboard to correct lateral instability.
A

provides a means to maintain a balanced fuel load condition.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 12, 16

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19
Q

The purpose of the baffle plate in a fuel tank is to _____________

  • resist fuel surging within the fuel tank.
  • provide internal structural integrity.
  • provide an expansion space for the fuel.
A

resist fuel surging within the fuel tank.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 21

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20
Q

If a bladder type fuel tank is to be left empty for an extended period of time, the inside of the tank should be coated with a film of _____________

  • ethylene glycol.
  • engine oil.
  • linseed oil.
A

engine oil.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 21

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21
Q

Which type of fuel valve will likely contain a 2nd thermal relief valve?

  • Cone Valve
  • Gate Valve.
  • Poppet Valve
A

Gate Valve.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 26

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22
Q

Fuel system components must be bonded and grounded in order to _____________

  • retard galvanic corrosion.
  • drain off static charges.
  • prevent stray currents.
A

drain off static charges.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 23

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23
Q

When routing rigid fuel lines in the proximity of electrical wiring, it is considered best practice to _____________

  • route the fuel line and wiring in a common harness.
  • route the fuel line below the height of the wiring.
  • route the fuel line above the height of the wiring.
A

route the fuel line below the height of the wiring.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 23

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24
Q

Fuel boost pumps are operated _____________

  • automatically from fuel pressure.
  • primarily for fuel transfer.
  • to provide a positive flow of fuel to the engine.
A

to provide a positive flow of fuel to the engine.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 27

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25
Q

What type of fuel booster pump requires a pressure relief valve?

  • Centrifugal
  • Sliding Vane
  • Concentric
A

Sliding Vane

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 31

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26
Q

To prevent vapor lock in fuel lines at high altitude, some aircrafts are equipped with _____________

  • vapor separators.
  • booster pumps.
  • direct injection type carburetors.
A

booster pumps.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 27

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27
Q

What is used in many aircraft to prevent bubbles in the fuel after it leaves the tank when atmospheric pressure is lower than fuel vapor pressure?

  • Air Fuel Separators
  • Boost Pumps
  • Anti-foaming Additives
A

Boost Pumps

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 27

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28
Q

What is the primary purpose of the fuel cross-feed system?

  • It allows any tank to supply fuel to any engine.
  • It bypasses the engine shutoff valve if it fails.
  • It divides the fuel and sends it to the injectors.
A

It allows any tank to supply fuel to any engine.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 12, 16

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29
Q

Where are flapper valves typically located?

  • In fuel tank partitions.
  • Downstream of fuel filters.
  • Within vane type fuel pumps.
A

Downstream of fuel filters.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 29

30
Q

Flapper valves are used in fuel tanks to _____________

  • act as check valves.
  • reduce pressure.
  • prevent a negative pressure.
A

act as check valves.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 29

31
Q

Why are centrifugal type boost pumps used in fuel systems of aircraft operating at high altitude?

  • To permit cooling air to circulate around the motor.
  • To supply fuel under pressure to engine driven pumps.
  • Because they are positive displacement pumps.
A

To supply fuel under pressure to engine driven pumps.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 28

32
Q

The purpose of a diaphragm in a vane type fuel pump is to _____________

  • compensate fuel pressures to altitude changes.
  • vary fuel pressure according to throttle setting.
  • equalize fuel pressure at all speeds.
A

compensate fuel pressures to altitude changes.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 31

33
Q

Why is the main fuel strainer located at the lowest point in the fuel system?

  • It filters and traps all micro organisms that may be present in the fuel system.
  • It provides a drain for residual fuel.
  • It traps any small amount of water that may be present in the fuel system.
A

It traps any small amount of water that may be present in the fuel system.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 33

34
Q
  1. The function of a fuel heater is to protect the engine fuel system from ice formation.
  2. An aircraft fuel heater cannot be used to thaw ice in the fuel screen.
    Regarding the above statements,

  • Only No. 1 is true.
  • Both No. 1 and No. 2 are true.
  • Only No. 2 is true.
A

Only No. 1 is true.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 35

35
Q
  1. Gas turbine engine fuel systems are very susceptible to the formation of ice in the fuel filters.
  2. A fuel heater operates as a heat exchanger to warm the fuel.
    Regarding the above statements,

  • Only No. 1 is true.
  • Only No. 2 is true.
  • Both No. 1 and No. 2 are true.
A

Both No. 1 and No. 2 are true.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 35

36
Q

An electrical type fuel quantity indicating system consists of an indicator in the cockpit and a float _____________

  • in the tank that moves a connecting arm to the wiper on a variable resistor in the tank.
  • attached to a rod that moves up or down in a calibrated cylinder.
  • in the tank that operates with alternating current and uses constant resistance in a circuit to drive a ratiometer-type indicator.
A

in the tank that moves a connecting arm to the wiper on a variable resistor in the tank.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 37

37
Q

What is the purpose of a float-operated transmitter installed in a fuel tank?

  • It sends an electric signal to the fuel quantity indicator.
  • It senses the dielectric qualities of fuel and air in the tank.
  • It senses the total amount of fuel density.
A

It sends an electric signal to the fuel quantity indicator.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 37

38
Q

What type of remote reading fuel quantity indicating system has several probes installed in each fuel tank?

  • Float type
  • Flow meters
  • Capacitance
A

Capacitance

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 38

39
Q

One advantage of electrical and electronic fuel quantity indicating systems is that _____________

  • the indicators are calibrated in gallons, therefore, no conversion is necessary.
  • only one transmitter and one indicator are needed regardless of the number of tanks.
  • several fuel tank levels can be read on one indicator.
A

several fuel tank levels can be read on one indicator.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 38

40
Q

One advantage of electrical and electronic fuel quantity indicating systems is that the indicator _____________

  • can be located any distance from the tank(s).
  • always measures volume instead of mass.
  • has no movable devices.
A

can be located any distance from the tank(s).

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 37

41
Q

The electronic type fuel quantity indicating system consists of a bridge circuit _____________

  • an amplifier, and indicator, and a tank unit.
  • a tank, an amplifier, and an indicator.
  • a tank unit, a tank, and an amplifier.
A

an amplifier, and indicator, and a tank unit.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 38

42
Q

A probe or a series of probes is used in what kind of fuel quantity indicating system?

  • Capacitor
  • Synchro
  • Selsyn
A

Capacitor

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 38

43
Q

What is the dielectric (non-conducting material) in a capacitance type fuel quantity indicating system?

  • Outer shell of the capacitor.
  • Fuel in the tank.
  • Fuel and air in the tank.
A

Fuel and air in the tank.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 38

44
Q

A capacitance type fuel quantity indicating system measures fuel in _____________

  • pounds per hour.
  • pounds.
  • gallons.
A

pounds.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 39

45
Q

In a fuel pressure warning circuit, if insufficient fuel pressure occurs, _____________

  • electrical contacts will close.
  • electrical contacts will open.
  • a flapper valve will close.
A

electrical contacts will close.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 44

46
Q

A fuel totalizer is a component which indicates the _____________

  • total amount of fuel being consumed by all engines.
  • amount of fuel in any given tank.
  • amount of fuel in all tanks.
A

amount of fuel in all tanks.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 42

47
Q

A transmitter in a fuel pressure warning system serves what function _____________

  • transmits an electrical signal to fluid pressure.
  • transmits fluid pressure directly to the indicator.
  • converts fluid pressure to an electrical signal.
A

converts fluid pressure to an electrical signal.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 44

48
Q

What is indicated when a fuel valve in-transit light illuminates?

  • A fuel valve is currently in motion.
  • Insufficient fuel pressure exists past a fuel valve.
  • Fuel is successfully being transferred to its desired location.
A

A fuel valve is currently in motion.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 44

49
Q

What unit would be adjusted to change the fuel pressure warning limits _____________

  • fuel pressure relief valve.
  • fuel flow meter bypass valve.
  • pressure sensitive mechanism.
A

pressure sensitive mechanism.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 44

50
Q

Fuel leaks are usually classified as a stain, a seep, a heavy seep, or a running leak. As a general rule _____________

  • stains, seeps, and heavy seeps are not flight hazards.
  • all fuel leaks, regardless of location or severity, are considered a hazard to flight.
  • stains, seeps, and heavy seeps, (in addition to running leaks) are considered flight hazards when located in unvented areas of the aircraft.
A

stains, seeps, and heavy seeps, (in addition to running leaks) are considered flight hazards when located in unvented areas of the aircraft.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 45-46

51
Q

When inspecting a removable rigid fuel tank for leaks, what procedure should be followed?

  • Pressurize the tank with air and submerge in water to locate leaks.
  • Pressurize the tank with air and brush with soapy water.
  • Fill the tank with water and pressurize with air and brush with soapy water.
A

Pressurize the tank with air and brush with soapy water.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 47

52
Q

What is the recommended practice for cleaning a fuel tank before welding?

  • Steam clean the tank interior.
  • Flush the inside of the tank with clean cold water.
  • Purge the tank with ambient air.
A

Steam clean the tank interior.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 47

53
Q

What should be used to remove flux from an aluminum tank after welded repair?

  • Soft brush and warm water.
  • 5 percent solution of nitric or sulfuric acid.
  • Mild solution of soap and water.
A

5 percent solution of nitric or sulfuric acid.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 47

54
Q

The absence of particulate contamination of jet fuel in transport aircraft is best maintained by _____________

  • frequent filter replacements.
  • frequent sump drains.
  • attentive fuel temperature control.
A

frequent filter replacements.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 49

55
Q

Some turbine powered aircraft have a fuel temperature indicator located in the cockpit to _____________

  • monitor the fuel flow in the event that ice crystals form in the fuel system.
  • monitor the fuel temperature during high altitude flight.
  • ascertain the amount of fuel onboard the aircraft when ice starts to form in the fuel tanks.
A

monitor the fuel temperature during high altitude flight.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 43

56
Q

Pressure fueling of aircraft is usually accomplished through _____________

  • at least one single point connection.
  • individual fuel tank over wing and/or fuselage access points.
  • pressure connections on individual fuel tanks.
A

at least one single point connection.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 55

57
Q

Which of the following may be used for the repair of fuel leaks on most integral fuel tanks?

  • Resealing with proper sealing compound.
  • Brazing
  • Welding
A

Resealing with proper sealing compound.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 47-48

58
Q

What can be done to eliminate or minimize the microbial growth problem in an aircraft jet fuel tank?

  • Use antibacterial additive.
  • Keep the fuel tank topped off.
  • Add carbon dioxide as a purgative.
A

Use antibacterial additive.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 51

59
Q

What method is used on turbine powered aircraft to determine when the condition of the fuel is approaching the danger of forming ice crystals?

  • Fuel Temperature Indicator
  • Fuel Pressure Gauge
  • Fuel Pressure Warning
A

Fuel Temperature Indicator

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 43

60
Q

If an aircraft is fueled from a truck or storage tank which is known to be uncontaminated with dirt or water, periodic checks of the aircraft’s fuel tank sumps and system strainers?

  • Are still necessary due to the possibility of contamination from other sources.
  • Can be eliminated except for the strainer check before the first flight of the day and the fuel tank sump check during 100 hour or annual inspections.
  • Can be sharply reduced since contamination from other sources is relatively unlikely and of little consequence in modern aircraft fuel systems.
A

Are still necessary due to the possibility of contamination from other sources.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 55

61
Q

If it is necessary to enter an aircraft’s fuel tank, which procedure should be avoided _____________

  • conduct the defueling and tank purging operation in an air conditioned building.
  • continue purging the tank during the entire work period.
  • station an assistant outside the fuel tank access to perform rescue operations if required.
A

conduct the defueling and tank purging operation in an air conditioned building.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 56

62
Q

Aircraft defueling should be accomplished _____________

  • with the aircraft’s communication equipment on and in contact with the tower in case of fire.
  • in a hangar where activities can be controlled.
  • in the open air for good ventilation.
A

in the open air for good ventilation.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 56

63
Q

How may the anti-knock characteristics of a fuel be improved?

  • By adding a knock enhancer.
  • By adding a knock inhibitor.
  • By adding a fungicide agent.
A

By adding a knock inhibitor.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 9

64
Q

Which of the following problems would result in a high fuel pressure indication in the cockpit?

  • Vapor lock.
  • A clogged fuel injector.
  • A clogged fuel tank vent line.
A

A clogged fuel injector.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 40

65
Q
  1. A fuel pressure relief valve is required on an aircraft positive displacement fuel pump.
  2. A fuel pressure relief valve is required on an aircraft centrifugal fuel boost pump.
    Regarding the above statements,

  • Both No. 1 and No. 2 are true.
  • Only No. 2 is true.
  • Only No. 1 is true.
A

Only No. 1 is true.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 28, 45

66
Q

Low and mid-wing single reciprocating engine aircraft fuel systems typically consist of an _____________

  • engine driven pump and a primer.
  • electric fuel pump and an engine driven fuel pump.
  • electric fuel pump, an engine driven fuel pump, and a primer.
A

electric fuel pump, an engine driven fuel pump, and a primer.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 11

67
Q

Some high-wing, high-performance single engine reciprocating engine aircraft have fuel injection systems. In these systems the _____________

  • fuel control delivers fuel to the fuel reservoir tanks.
  • fuel control delivers fuel to the distributor manifold.
  • auxiliary pump must be on to deliver fuel to the fuel control.
A

fuel control delivers fuel to the distributor manifold.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 12-13

68
Q

A “wobble” pump is _____________

  • an electric primary fuel pump located inside the fuel tank.
  • a hand operated pump used as a fuel primer on older reciprocating aircraft.
  • used to return excess fuel to reservoir tanks on fuel injected aircraft.
A

a hand operated pump used as a fuel primer on older reciprocating aircraft.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 12-13

69
Q

The appearance of tan or brown tints on the surface of fuel or in filters is an indication that the fuel has been contaminated by _____________

  • surfactants.
  • microorganisms.
  • moisture.
A

surfactants.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 51

70
Q

Most aircraft fuel tanks contain baffling to _____________

  • guide impurities to the sump.
  • provide vent space for the fuel at all attitudes.
  • subdue the fuel from shifting during flight maneuvers.
A

subdue the fuel from shifting during flight maneuvers.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 18

71
Q

A fuel selector valve in a single engine or light twin aircraft is likely to be what type of valve?

  • Gate
  • Cone
  • Bypass
A

Cone

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 25

72
Q

At the core of a pulsating electric pump used as an auxiliary fuel pump in light reciprocating engine aircraft is a _____________

  • centrifugal impeller.
  • solenoid.
  • relay controlled rotating vane.
A

solenoid.

Ref: Airframe Handbook H-8083-31B-ATB, Chapter 14 Page 30

Airframe A&P 2024 (1 decks)

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