ENGINEERING

Question 1

ou are level at your cruise altitude of FL310 at a speed of Mach .83. ATC tells you to maintain a speed of no greater than Mach .80. You pull the thrust levers back and the engines decelerate. The engine are decelerated because:

The turbine power exceeds the compressor power required to maintain Mach .83.
The turbine power is less than the compressor power required to maintain Mach .83.
The power extracted by the turbine will equal the power required to operate the compressor.
The amount of ram air available to the compressor section diminishes.

Answer 1

The turbine power is less than the compressor power required to maintain Mach .83.

Question 2

High fuel flow during engine start can be an indication of what?

A tailwind.
Introducing fuel into the engine before the compressor is up to proper speed.
Engine fuel pump malfunction.
Fuel control malfunction.

Answer 2

Fuel control malfunction.

Question 3

During an engine start you notice that the N2 is lower than normal and the EGT is higher than usually seen, but not excessive or approaching the start limits. What problem, if any, is the engine experiencing?

A hot start.
Start is normal.
A possible hung start.
Weak igniters in the combustor section.

Answer 3

A possible hung start.

Question 4

WHEN SPOILERS ARE FULLY EXTENDED AS A SPEED BRAKE, BOTH SIDES REMAIN IN THE EXTENDED SPEED BRAKE POSITION, AND THEREFORE, THE SPOILERS DO NOT PROVIDE ANY ROLL CONTROL. WHAT TYPE OF SPOILER SYSTEM DOES THIS BEST DESCRIBE?

SEQUENTIAL
NON-SEQUENTIAL
DIFFERENTIAL
NON-DIFFERENTIAL

Answer 4

NON-DIFFERENTIAL

Question 5

When wing fuel tanks on certain heavy aircraft, such as the MD-11, get below a certain fuel quantity, VMO/MMO is reduced. The primary reason for this is because:

The weight of the fuel in the wing fuel tanks that has been burned off is no longer available to provide added structural stability required at higher true airspeeds.
The weight of the fuel in the wing fuel tanks that has been burned off is no longer available to provide added structural stability required at higher indicated airspeeds.
Without the added weight of the fuel on the wing, the angle of attack increases, making the aircraft more susceptible to Mach tuck at higher airspeeds.
Without the added weight of the fuel on the wing, the angle of attack increases, making the aircraft more susceptible to wing twist at higher airspeeds

Answer 5

The weight of the fuel in the wing fuel tanks that has been burned off is no longer available to provide added structural stability required at higher indicated airspeeds.

Question 6

Activation of the trailing edge flaps automatically deploys:

The slats, which are driven out of the leading edge and downward, extending the camber of the wing.
The slats, which are driven out of the leading edge and downward, extending the chord of the wing.
The leading edge flaps, which are driven out of the leading edge and downward, extending the camber of the wing.
The leading edge flaps, which are driven out of the leading edge and downward, extending the chord of the wing.

Answer 6

The leading edge flaps, which are driven out of the leading edge and downward, extending the camber of the wing.

Question 7

Which hydraulic operation normally uses a double-acting, unbalanced linear actuator?

Brakes.
Landing gear.
Autopilot servo.
Rudder actuators.

Answer 7

Landing gear.

Question 8

DURING ENGINE START YOU NOTICE THAT THE N2 IS NOT SPOOLING UP AS FAST AS YOU NORMALLY MIGHT SEE IT. YOU ARE AT AN AIRPORT THAT IS 5600 FT MSL ON A VERY HOT DAY WITH A SLIGHT WIND FROM BEHIND. GIVEN THE SITUATION, WHAT POSSIBLE START ANOMALY WOULD YOU WANT TO BE ON THE LOOKOUT FOR

HOT START
HUNG START
NO START ANOMALY EXISTS IN THIS SCENARIO
NO START

Answer 8

HUNG START

Question 9

The speed brake control can deploy all spoiler and speed brake surfaces fully when operated.

Often, these surfaces deploy on the ground automatically when engine thrust reversers are retracted.
Often, these surfaces deploy on the ground automatically when engine thrust reversers are activated.
Often, these surfaces deploy on the ground automatically when brakes are activated.
Often, these surfaces deploy on the ground automatically when brakes are retracted.

Answer 9

Often, these surfaces deploy on the ground automatically when engine thrust reversers are activated.

Question 10

Mixing aviation gasoline with jet fuel will affect a turbine power plant by forming on the:

Fan blades.
Inlet guide vanes.
Compressor blades.
Turbine blades.

Answer 10

Turbine blades.

Question 11

Your ammeter pointer display a positive indication. What information does this provide to the pilot?

The charging rate of the battery.
The battery is fully charged.
More current is being drawn from the battery than is being replaced.
The amount of charging current demanded by the battery.

Answer 11

The charging rate of the battery.

Question 12

How are airplane AC generators rated?

Kilovolt-amps (KVA)
Kilowatts (KW)
Amps
Volts

Answer 12

Kilovolt-amps (KVA)

Question 13

The stators in the turbine section of a gas turbine engine:

Decreases temperature.
None of the above.
Increase the velocity of the gas flow.
Increases pressure.

Answer 13

Increase the velocity of the gas flow.

Question 14

The purpose of hydraulic accumulator is to:

Supply hydraulic fluid for normal operations under low demand.
Compensate for potential loss of pressure at high altitudes.
Maintain Fluid pressure and supply fluid under high demand.
Filter debris and remove air.

Answer 14

Supply hydraulic fluid for normal operations under low demand.

Question 15

Why are fixed orifice nozzles used in the lubrication system of turbine engines?

To keep pressure on the oil pump, thus preventing oil foaming.
To protect oil seals by preventing excessive pressure from entering the bearing cavities.
To keep pressure on the oil pump, thus preventing air lock.
To provide a relatively constant oil flow to the main bearings at all engine speeds.

Answer 15

To provide a relatively constant oil flow to the main bearings at all engine speeds.

Question 16

In a gas turbine engine the inlet, compressor, and diffuser sections are responsible for?

Building static energy of the airflow.
Transferring static energy into thrust.
Building potential energy of the airflow.
Transferring compressed airflow into kinetic energy.

Answer 16

Building potential energy of the airflow.

Question 17

How does “ram effect” affect performance of a turbine engine?

Increases temperature at the engine inlet, thus increasing performance.
Increases pressure at the engine inlet, thus decreasing performance.
Increases pressure at the engine inlet, thus increasing performance.
Decreasing air density at the engine inlet, thus decreasing performance.

Answer 17

Increases pressure at the engine inlet, thus increasing performance.

Question 18

Which of these items would not normally be fitted to the engine accessory system?

EGT/TIT
Engine driven fuel pump
N1
N2

Answer 18

EGT/TIT

Question 19

You are in level flight and encounter icing conditions, and you know that the pitot system heat is not working. What do you do?

Descend to a lower altitude and find a colder SAT
Descend to a lower altitude and find a warmer SAT.
Climb to a higher altitude; warmer than the current freezing level
Make no changes until you can ensure accurate airspeed inputs.

Answer 19

Climb to a higher altitude; warmer than the current freezing level
Correct
If you can find colder temperatures, the liquid water in the atmosphere will become frozen, making it less likely that freezing precipitation will clog the pitot tubes. Reference: Airplane Flying Handbook, Transition to Multiengine Airplanes.

Question 20

How do you tell the loads on the electrical bus?

Check the load meter.
Check the circuit breakers.
Look at the generator output.
Check the battery discharge rate.

Answer 20

Check the load meter.
Correct
Load meters will tell you to amperage load on a bus, usually in a fraction of the maximum load. Reference: Aviation Maintenance Technician Handbook – Airframe (Vol 2), Aircraft Electrical System.

Question 21

What instrument is primary for pitch in straight and level flight?

  Attitude indicator.
  Airspeed indicator.
  VSI.
  Altimeter.
Correct
The altimeter is the primary instrument for level flight. Reference: Instrument Flying Handbook, Airplane Attitude Instrument Flying Using Analog Instrumentation.

Answer 21

Altimeter.

Question 22

What types of electricity do most large aircraft generate from engine driven generation systems?

AC.
DC.
Variable frequency AC.
Variable frequency DC.

Answer 22

AC.
Correct
Large aircraft typically generate AC power from generators. These are called constant speed drives or integrated drive generators. Through gearing, they spin at a constant speed to produce 400hz power. Reference: Aviation Maintenance Technician Handbook – Airframe (Vol 2), Aircraft Electrical System.

Question 23

Why is fluid used in hydraulic systems over gas?

It is cheaper than generating extra engine power.
Gas in incompressible, which would overstress components.
Because fluid is not compressible like gas.
Gas is undependable at low temperatures.

Answer 23

Because fluid is not compressible like gas.
Correct
Since fluid is not compressible, the pressure of the fluid can be transferred directly to the actuator for the flight control surface. A gas is compressible, making the use of gas undependable for high-pressure surface movement applications. Reference: Pilot’s Handbook of Aeronautical Knowledge, Aircraft Systems.

Question 24

What is trim?

Provides feedback on the yoke to prevent over control.
Moves in the opposite direction of the primary control to relieve control pressure.
Provides a tab by which the flight control is easier to move.
Allows bleed air to enter the engine anti-ice actuator.

Answer 24

Moves in the opposite direction of the primary control to relieve control pressure.
Correct
Trim tabs move in the opposite direction of the control surface, in essence flying the trailing edge into the correct position for a given airspeed. They are used primarily to relieve control forces. Reference: Pilot’s Handbook of Aeronautical Knowledge, Flight Controls.

Question 25

Why do we use EGT to determine engine performance?

EGT is a direct measurement of the power being produced by the engine
EGT is a direct measure of the amount of fuel being used.
EGT is the only way to measure the performance of a turbine engine.
The limiting factor of a gas turbine engine section is the turbine section.

Answer 25

The limiting factor of a gas turbine engine section is the turbine section.
Correct
The most limiting factor of a gas turbine engine is the temperature of the turbine section, which is indirectly measured by the temperature of the exhaust gases leaving the turbine through the exhaust. Reference: Pilot’s Handbook of Aeronautical Knowledge, Aircraft Systems.

Question 26

What is the voltage and frequency for aircraft AC electrical power?

120 VAC, 500 Hz.
115 VAC, 400 Hz.
28 VAC, 400 Hz.
24 VAC, 500 Hz.

Answer 26

115 VAC, 400 Hz.
Correct
Most AC powered aircraft have a power rating of 115V at 400 Hz frequency. Reference: Aviation Maintenance Technician Handbook – Airframe (Vol 2), Aircraft Electrical System.

Question 27

With a Pt2 probe iced over, what indications will you get?

A falsely high EPR.
A falsely low EPR.
EPR will read zero
EPR will be unaffected. Only N1 will read lower than normal.

Answer 27

A falsely high EPR.
Correct
The Pt2 probe is the probe that senses inlet pressure. When this tube is iced over, it will provide an artificially high ratio of inlet to outlet pressure to the EPR instrument, thus giving an indication that engine power is higher than it really is. Reference: Pilot’s Handbook of Aeronautical Knowledge, Aircraft Systems.

Question 28

During engine start, rising EGT and a slower than normal RPM increase is a sign of what?

Hung start.
No light start.
Hot start.
Failed compressor start.

Answer 28

Hot start.
Correct
A hot start occurs when EGT rises faster than the RPM can. The temperature in at the turbine can quickly exceed limits due to inadequate airflow or too much fuel. Reference: Airplane Flying Handbook, Transitioning to Jet Powered Airplanes.

Question 29

Define specific fuel consumption.

Fuel flow in gallons for a given airspeed.
Fuel flow in pounds for a given airspeed.
Fuel flow at a given cruise altitude.
Fuel flow in lbs. per hour at a given power setting.

Answer 29

Fuel flow in lbs. per hour at a given power setting.
Correct
Specific fuel consumption is the amount of fuel burned per hour per unit of thrust (lbs of fuel per hour/pounds of thrust). Reference: Aerodynamics for Naval Aviators, Turbojet Operating Characteristics.

Question 30

What limits turbine engines from developing compressor stalls?

Handling valves.
Turbine inlet guide vanes.
Variable turbine stators.
Compressor bleed valves.

Answer 30

Compressor bleed valves.Correct
Compressor bleed valves are installed to “spill” excess air away from the compressor. Excess air in the compressor, especially at low speeds, can cause a compressor stall. Reference: Pilot’s Handbook of Aeronautical Knowledge, Aircraft Systems.

Question 31

You get smoke in the cabin, and you fix the problem. How do you get rid of the smoke?

Decrease cabin pressure differential.
Increase cabin pressure differential.
Keep the cabin pressure differential the same.
Take no action. Smoke will eventually leave via the outflow valve.

Answer 31

Decrease cabin pressure differential.
YOU ARE PROBABLY RUNNING AT MAX DIFFERENTIAL SO IF YOU DECREASE THE CABIN ALTITUDE SO IT DECREASES THE CABIN DIFFERENTIAL YOU CAN GET SOME AIR CYCLED IN THE CABIN.

Correct
By decreasing cabin altitude, you open the outflow valve. This will remove smoke and fumes. Reference: Airplane Flying Handbook, Emergency Procedures.