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E.F.M.S. > Lesson 1 > Flashcards

Lesson 1 Flashcards

1
Q

The thrust of a turbo jet is controlled by varying the [?] that is burnt in the [?] and in order to operate the safe temperature limits, the amount of fuel that is burnt must be governed by the [?] that is available at the time.

A

1.amount of fuel
2. combustion system
3. amount of air

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2
Q

The air supply is dependent upon the RPM of the compressor and the density of the air at its inlet, so under a constant set of atmospheric conditions, the RPM of the compressor is an indication of the [?].

A

engine thrust

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3
Q

The pilot has control of the fuel flow to the combustion system and ts able to select any compressor RPM, between ground idling and the maximum permissible which is required for [?] conditions, by the operation of a cockpit lever.

A

take-off

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4
Q

In the normal operational environment of an aircraft engine, atmospheric conditions can vary over a wide range of air temperatures and pressures resulting in [?] at the compressor inlet.

A

changes of air density

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5
Q

A [?] will cause a reduction in the amount of air delivered to the combustion system at a selected RPM, with a consequent increase in the combustion chamber temperature.

A

reduction in air density

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6
Q

If the fuel flow is not reduced, a [?] will occur accompanied with overheating of the combustion and turbine assemblies.

A

rise in compressor RPM

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7
Q

An [?] will result in an increase in the amount of air delivered to the combustion system at a selected RPM

A

increase in air density

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8
Q

Fuel flow is increased, a [?] in RPM will occur .

A

reduction

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9
Q

The density of the air gets progressively less as the altitude is increased, therefore less fuel will be required in order to maintain the
selected RPM.

A

ALTITUDE

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10
Q

The faster the aircraft flies then the faster the air is forced into the aircraft intake.

A

FORWARD SPEED

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11
Q

(?) plays an important part in the performance of a turbo-jet. Within certain limits the greater the ram
effect, the greater the air mass flow and more fuel can be burnt at the selected RPM, producing more thrust.

A

Ram Effect

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12
Q

(?) is to deliver to the combustion system, in a readily combustible form, the correct amount of fuel over
the whole operating range of the engine, as required by the pilot.

A

Purpose of the engine fuel system

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13
Q

2 TYPES OF FUEL TANK

A

A. Gravity feed fuel system
B. Booster Pump feed fuel system/ Pressure Type

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14
Q

Stores sufficient fuel for the aircraft’s designed flight duration.

A

Fuel Tanks

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15
Q

(?) the fuel passes through a main system strainer. This often has a drain function to remove sediment and water.

A

Shutoff Valve or Selector Valve

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16
Q

(?) also supplies fuel pressure while starting and is used to prevent vapor lock during flight at high altitude.

A

Electric Pump

17
Q

Some high-wing, high-performance, single-engine general aviation aircraft are equipped with a fuel system that features (?) rather than a carburetor.

A

fuel injection

18
Q

It combines gravity flow with the use of a fuel pump(s).

A

Teledyne Continental system

19
Q

Fuel pressurized by an (?) is metered as a function of engine rpm on the Teledyne-Continental system.

A

Engine-Driven Pump

20
Q

draws fuel through the selector valve. It forces the fuel through the strainer, making it available for the primer pump and the engine-driven fuel pump.

A

Electric Auxiliary Fuel Pump

21
Q

This pump is typically used for starting and as a backup should the engine-driven pump fail.

A

Electric Auxiliary Fuel Pump

22
Q

It is controlled by a switch in the cockpit and does not need to be operating to allow the engine-driven fuel pump access to the fuel.

A

Electric Auxiliary Fuel Pump

23
Q

Fuel injection systems spray (?) into the engine intake or directly into the cylinders.

A

pressurized fuel

24
Q

(?) intakes the pressurized fuel from the electrically driven pump or from the reservoir tanks if the electric pump is not operating.

A

Engine-Driven Fuel Pump/ EDP

25
Q

It supplies a higher-than needed volume of fuel under pressure to the fuel control.

A

Engine-Driven Fuel Pump/ EDP

26
Q

(?) meters the fuel according to engine rpm and mixture control inputs from the cockpit.

A

Fuel Control Unit/ FCU

27
Q

A simplified system on a high-wing, twin-engine aircraft that combines gravity feed with an electric fuel pump.

A

SMALL MULTIENGINE (RECIPROCATING) AIRCRAFT FUEL SYSTEMS

(HIGH-WING TWIN)

28
Q

This pump draws fuel from the selected tank and sends it under pressure to the inlet side of the fuel injection metering unit.

A

Electric Fuel Pump

29
Q

It features the main fuel tanks in the wing tips and auxiliary tanks in the wing structure.

A

SMALL MULTIENGINE (RECIPROCATING) AIRCRAFT FUEL SYSTEMS

(LOW-WING TWIN)

30
Q

Two selector valves are required on twin-engine aircraft, one for each engine. The right selector valve receives fuel from a main tank on either side of the aircraft and directs it to the right engine. The left selector valve also receives fuel from either main tank and directs it to the left engine. This allows fuel to (?) from one side of the aircraft to the opposite engine if desired.

A

crossfeed

31
Q

Ensures a constant supply of fuel at low pressure to the inlet of the engine driven HP Fuel Pump.

A

BOOST PUMP

32
Q

The most common type of auxiliary fuel pump used on aircraft, especially large and
high-performance aircraft, is the (?).

A

Centrifugal Pump

33
Q

It is electric motor driven and most frequently is submerged in the fuel tank or located just outside of the bottom of the tank with the inlet of the pump extending into the tank.

A

Centrifugal Pump

34
Q

If the pump is mounted outside the tank, (?) is typically installed so the pump can be removed without draining the fuel tank.

A

pump removal valve

35
Q

A (?) is a variable displacement pump. It takes in fuel at the center of an impeller
and expels it to the outside as the impeller turns.

A

centrifugal boost pump

36
Q

An (?) prevents fuel from flowing back through the pump.

A

Outlet Check Valve

37
Q

A (?) may be installed in the fuel feed system to allow the engine-driven pump to pull fuel from the tank if the boost pump is not operating.

A

Bypass Valve

38
Q

The (?) is used to supply the engine-driven fuel pump, back up the engine driven fuel pump, and transfer fuel from tank to tank if the aircraft is so designed.

A

Centrifugal Boost Pump

39
Q

Isolates the engine fuel system from the aircraft fuel system in the event of engine fire or for maintenance.

A

LOW PRESSURE COCK

E.F.M.S. (8 decks)

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