AS 311 - Exam 2 Prep

70 flashcards · Other · by Nicholas Enoul

What is one purpose of the radial support struts and tail cone in the exhaust section? Answers: A. Change radial airflow into axial airflow after the exhaust exits the turbine section. B. Increase the exhaust velocity to maximize net thrust. C. Increase the static pressure to maximize pressure thrust. D. Change axial airflow into radial airflow after the exhaust exits the turbine section.
A. Change radial airflow into axial airflow after the exhaust exits the turbine section.
What is the shape and purpose of the duct formed between the tail cone and the exhaust cone in a subsonic airplane? Answers: A. Convergent duct. Increase velocity in the exhaust gas to maximize pressure thrust. B. Divergent duct. Increase velocity in the exhaust gas to help prevent radial airflow after the exhaust exits the turbine section. C. Divergent duct. Increases static pressure in the exhaust gas to help prevent radial airflow after the exhaust exits the turbine section. D. Convergent du…
C. Divergent duct. Increases static pressure in the exhaust gas to help prevent radial airflow after the exhaust exits the turbine section. NOTE: Even though the textbook states that the outer diameter is what determines what a convergent/divergent shape is (either decreasing/increasing in outer diameter), this class DOES NOT want you to think of it this way. You have to include the inner diameter when considering the shape!!! See the explanation below. An attempt at an explanation: It may seem…
What is the purpose of a choked nozzle in a subsonic airplane? A. Decrease exhaust gas velocity and increase static pressure to maximize pressure thrust B. Increase the exhaust gas velocity above M 1.0 and decrease exhaust gas pressure below ambient pressure C. Increase the exhaust gas velocity to M 1.0, create a shockwave at the exhaust nozzle, and increase exhaust pressure to ambient pressure D. Increase the exhaust gas velocity above M 1.0, create shockwaves inside the exhaust cone, and decr…
C. Increase the exhaust gas velocity to M 1.0, create a shockwave at the exhaust nozzle, and increase exhaust pressure to ambient pressure
What is the purpose of a convergent-divergent exhaust section in this supersonic airplane? A. Increase the static pressure above ambient in the convergent section and then decrease the pressure below ambient in the divergent section B. Decrease the exhaust velocity to M 1.0 in the convergent section and decrease the exhaust velocity below M 1.0 in the divergent section C. Increase the exhaust velocity to M 1.0 in the convergent section and accelerate the exhaust above M 1.0 in the divergent sec…
C. Increase the exhaust velocity to M 1.0 in the convergent section and accelerate the exhaust above M 1.0 in the divergent section Note: Even though the convergent section **does** form a shockwave, the key thing to look for is the decrease/increase in exhaust velocity.
What is (are) the primary source(s) of aircraft noise? A. Only compressor fan B. Only landing gear and flaps C. Turbulent airflow, compressor fan, jet blast, landing gear, and flaps D. Only compressor noise and jet blast
C. Turbulent airflow, compressor fan, jet blast, landing gear, and flaps
What shape (most likely) is the exhaust on this aircraft? A. Divergent B. Neither convergent nor divergent C. Convergent-divergent D. Convergent
A. Divergent Note: On most (if not all helicopters I have seen), the duct has to be divergent so as to not create more thrust. This sounds a bit weird, but think of how a helicopter has to hover or go backwards. Having a rear-facing jet blasting exhaust would not help the helo do these maneuvers. TL;DR: Helicopter = Divergent Duct
What is true of the static pressure in this convergent-divergent exhaust section? A. Static pressure remains constant in the convergent and divergent sections B. Static pressure increases in both the convergent and divergent sections and ends up greater than ambient C. Static pressure decreases in the convergent section and then increases above ambient in the divergent section D. Static pressure increases (due to a choked nozzle) in the convergent section and then decreases to ambient in the di…
D. Static pressure increases (due to a choked nozzle) in the convergent section and then decreases to ambient in the divergent section NOTE: This seems a bit weird, but the key thing to look for is decreases to ambient. It doesn't go higher than ambient pressure, but matches it. I'll verify this with the Prof. ASAP though.
What is the name and purpose of the white device in the exhaust section of this engine? A. Exhaust cone struts. Change radial airflow into axial airflow. B. Divergent nozzle. Increases static pressure in tailpipe C. Multi-lobe exhaust mixer. Mix airflow from bypass and core airflow to decrease engine noise. D. Turbine exit vanes. Ensure optimal velocity and angle of exhaust gases in tailpipe.
C. Multi-lobe exhaust mixer. Mix airflow from bypass and core airflow to decrease engine noise.
Why are the aft edges of both the bypass shroud and exhaust cowl chevron-shaped? A. Increases static pressure in the exhaust gas B. Because it looks awesome. C. Encourages airstream mixing and reduces engine noise. D. Encourages shockwave formation to decrease exhaust velocity below M 1.0
C. Encourages airstream mixing and reduces engine noise.
What is the shape and purpose of this tailpipe if the airplane is flying at M 0.91? A. Convergent. Increase exhaust velocity to M 1.0 and create a shockwave at the exhaust nozzle which "chokes" the flow and increases static pressure in the tailpipe. B. Convergent. Increase exhaust velocity to M 1.0 which decreases static pressure to ambient and increases propulsive efficiency. C. Convergent-divergent. Increase exhaust velocity to greater than M 1.0 which increases net thrust. D. Convergent-dive…
A. Convergent. Increase exhaust velocity to M 1.0 and create a shockwave at the exhaust nozzle which "chokes" the flow and increases static pressure in the tailpipe.
What is the name (shape) and purpose of the portion of the tailpipe indicated by the red dot? A. Divergent. Increase static pressure to reduce turbulent exhaust flow. B. Divergent. Increase exhaust gas velocity in supersonic aircraft. C. Convergent. Increase exhaust gas velocity to M 1.0 to create a choked nozzle. D. Convergent. Decrease static pressure to ambient to increase propulsive efficiency.
A. Divergent. Increase static pressure to reduce turbulent exhaust flow.
What is the purpose of the struts that radiate outward from the exhaust cone? A. Convert radial exhaust gas motion into axial motion. B. Convert axial exhaust gas motion into radial motion C. Increase exhaust gas velocity D. Decrease exhaust gas velocity
A. Convert radial exhaust gas motion into axial motion.
An exhaust pipe that is only divergent (no convergence) is most likely found on what type of engine? A. Turboshaft B. Turboprop C. Turbofan D. Turbojet
A. Turboshaft NOTE: Divergent exhaust pipes are usually found in helicopters. Considering that helicopters use turboshafts, then this has to be the answer :D
What is the name (shape) and purpose of this exhaust nozzle? A. Convergent-divergent. Increase exhaust velocity above M 1.0 and decrease static pressure to ambient. B. Convergent-divergent. Decrease exhaust velocity to below M 1.0 and increase static pressure above ambient. C. Fixed geometry exhaust. Change into convergent shape during supersonic flight. D. Variable geometry exhaust. Change into convergent shape during supersonic flight.
A. Convergent-divergent. Increase exhaust velocity above M 1.0 and decrease static pressure to ambient. -- NOTES -- This is my guesswork as to why it's (A.), but here's my thought process. First of all, it can't be (D.), not because it isn't variable (it is a variable nozzle), but because it doesn't "change into convergent shape during supersonic flight." It would, in reality, change into a convergent-divergent shape during supersonic. The only time it should be convergent only is when the airc…
What type of noise is least desirable and travels the farthest distance? A. Low-frequency noise. B. High-frequency noise. C. Mid-frequency noise. D. Noise between 50-80 decibels.
A. Low-frequency noise.
What is the name and purpose of this engine exhaust feature? A. Multi-lobe exhaust mixer. Mix airflow from bypass and core airflow to decrease engine noise. B. Engine nacelle chevron. Mix airflow from bypass and core air to decrease engine noise. C. Afterburner. Increase thrust. D. Turbine exit guide vanes. Optimize airflow direction and velocity in the tailpipe.
A. Multi-lobe exhaust mixer. Mix airflow from bypass and core airflow to decrease engine noise.
What is the name of the openings and doors on the side of the engine cowl? A. Clamshell reverser B. Aerodynamic blockage reverser C. Mechanical Blockage Reverser D. Target Reverser
B. Aerodynamic blockage reverser NOTE: One thing to note is that even though this looks like it is mechanically blocking and diverting the air forwards, it is still an aerodynamic reverser because it is using the bypass air, not the exhaust jet! We can see that the exhaust cone is not being blocked, just the bypass air. TL;DR: Blocks bypass air = Aerodynamic Blocks whole exhaust/jet = mechanical
What is the name of the component on the aft end of the Citation X engine nacelle? A. Cascade reverser B. Clamshell reverser C. Divergent duct D. Aerodynamic blockage reverser
B. Clamshell reverser
How are thrust reversers deployed in the Cessna Citation Encore? A. Thrust reversers always deploy when the throttle setting is decreased B. Thrust reversers automatically deploy when the throttle is moved to idle C. Throttle is moved to idle then the "piggyback" levers are pulled up D. The thrust reverse lever is pushed forward
C. Throttle is moved to idle then the "piggyback" levers are pulled up Note: The key thing to look for is the piggy-back lever on the three images.
What is the name and purpose of the white grating in the side of the Pratt & Whitney PW2000 engine cowl? A. Cascade reverser. Uses bleed air to re-direct core (hot) exhaust air B. Cascade reverser. Mechanically re-directs bypass (cold) exhaust air C. Aerodynamic blockage reverser. Mechanically re-directs core (hot) exhaust air D. Target reverser. Mechanically re-directs bypass (cold) exhaust air
B. Cascade reverser. Mechanically re-directs bypass (cold) exhaust air Note: It has to be redirecting the cold bypass air as it is an aerodynamic cascade reverser. To confirm this, we can actually see the jet exhaust that protrudes out of the engine nacelle on the right.
At what speed (KIAS) during the landing roll should the pilot reduce reverse thrust to idle in the Cessna Citation Encore? **Enter only numbers** Hint: don't overthink it!
Answer: 60 Note: This may seem overly simple, but we can find the answer at the last paragraph of the image: "Thrust Reversers - REVERSER LEVERS TO IDLE REVERSE AT 60 KIAS"
What is the maximum allowable % N1 for reverse thrust in the Cessna Citation Encore given the following METAR? **Enter only numbers and decimal point** KMSO 021653Z 00000KT 10SM CLR 14/07 A3027 RMK AO2 SLP246 T01390067
Answer: 71.4 or 71.4% Note: The way we get to this answer is shockingly simple. Here are the steps in no particular order: 1). As we can see on the METAR, the temperature is 14°C (14/07). 2). We can also see that if the OAT is above -18°C, then we cannot exceed 71.4% --> "Do not exceed 71.4% N1 when OAT is at or above -18°C" As this exceeds 14°C exceeds the -18°C stipualted, we should thusly type out 71.4.
Why should the pilot decrease reverse thrust below a certain airspeed after landing? A. To avoid engine overspeed B. To avoid excessive exhaust pipe pressure C. To avoid FOD and possible compressor stall. D. To avoid insufficient exhaust pipe pressure
C. To avoid FOD and possible compressor stall. NOTE: I don't actually think we would need to have the image to give us the answer. But since we do have it, it can help us confirm this answer when we look at the last paragraph's last sentence: "Idle reverse thrust is capable of causing ingestion fo small grit at very low ground speed" This should at least help in confirming that it has something to do with FOD. The compressor stall component of the answer has to be memorized though.
What type of engine controls are pictured and is reverse thrust available? A. Turbofan. Yes, thrust reverse is available. B. Turboprop. Yes, thrust reverse is available. C. Turboshaft. Yes, thrust reverse is available. D. Turboprop. No, thrust reverse is not available.
B. Turboprop. Yes, thrust reverse is available. NOTE: There are 3 main things we could look at for the answer: 1). There is a prop control lever located in the middle. Additionally, it says "feather" --> this must mean that it is a turboprop engine. 2). On the throttle control (left most set of levers) there is an "idle" then "ground fine" placard. What is almost always behind idle? Reversers hecc yea >:D 3). Additionally, the placard on the throttle also indicates that you would have to "lift"…
How does water injection thrust augmentation increase thrust? A. Provides increased compressor cooling B. Increases mass airflow C. Provides decreased air inlet density D. Provides increased combustor cooling and increased intake air density
D. Provides increased combustor cooling and increased intake air density NOTE: This is a bit loopy, but adding water into a system (cooling it) makes the air denser. This cooling also helps the combustor cool down, allowing for a bigger/hotter fireball without damaging the combustor. Or, my favorite way of processing the answer: Is it the longest answer? Yes? Then that's the answer!
What type of thrust augmentation system can be seen in this picture? A. Alcohol injection B. Thrust vectoring C. Water injection D. Afterburner
D. Afterburner HYPERBOLIC NOTE/TANGENT TIME: There are a lot of ways we can figure out this answer, but the first is figuring out if this has thrust vectoring or not. It does seem to have a variable geometry exhaust, but it is incredibly difficult to judge whether or not it helps the plane maneuver via vectoring. With how inlaid the VRB exhaust nozzle is, it seems that it is a shaky answer at best. However, this looks to be a military jet (single engine with airbrakes). Alongside the parts insi…
What is the name and purpose of the part of the afterburner thrust augmentation system pictured below? A. Water injectors. Provide increased air density in exhaust section. B. Alcohol injectors. Provide increased cooling for exhaust section. C. Flame holder. Provide increased mixing for fuel-air mixture. D. Turbine inlet swirl vanes. Provide increased mixing for fuel-air mixture in turbine section.
C. Flame holder. Provide increased mixing for fuel-air mixture. NOTE: What confused me the most were the small holes in the images. However, this concept (from what I remember of the lectures) can also be seen in combustor liners --> having small holes (or dimples) in the structure to center the flame. Therefore, and with the additional consideration of how the construction is right behind the jet nozzle, and even though it looks weird, it is a flame holder.
How does a water injection thrust augmentation system increase thrust? A. Increases mass airflow B. Decreases air density in the compressor C. Increases air density in the inlet and/or increases combustor cooling D. Increases compressor cooling
C. Increases air density in the inlet and/or increases combustor cooling
What type of thrust augmentation system is visible in the image? A. Exhaust exit guide vanes B. Water injection C. Alcohol injection D. Afterburner
D. Afterburner NOTE: Honestly, the way I figured this out was by outside thinking. This aircraft is most definitely a F/A-18, which means it has an afterburner.
What is the name and purpose of the rings and radial struts in the center of the exhaust section? A. Water/alcohol injection rings. Increase air density and mass airflow B. Flame holder. Provide optimum fuel-air mixing to increase fuel efficiency C. Exhaust duct stator vanes. Direct airflow out of the turbine section D. Exhaust exit guide vane. Ensure optimum airflow angle and velocity outside the tailpipe
B. Flame holder. Provide optimum fuel-air mixing to increase fuel efficiency Note: Honestly, I was only able to figure this out because this is an F/A-18 (which have afterburners). That, and how the question was worded, was how I figured this one out :/
How does an afterburner increase thrust? A. Injects and ignites fuel in the turbine section B. Injects additional fuel into the combustor to increase mass airflow C. Injects water or alcohol to increase air density D. Injects and ignites fuel in exhaust section
D. Injects and ignites fuel in exhaust section
What is the name and purpose of the pictured device? A. Cascade reverser. Redirect cold/bypass airflow B. Cascade reverser. Redirect core/hot exhaust C. Mechanical blockage reverser. Redirect core/hot exhaust D. Mechanical blockage reverser. Redirect cold/bypass airflow
A. Cascade reverser. Redirect cold/bypass airflow Note: As a cascade reverse is in the aerodynamic category, we have to remember that this category has nothing to do with hot/core air (which is what mechanical blockers do).
What is the name and purpose of the pictured device? A. Mechanical blockage reverser. Redirects core/hot exhaust B. Cascade reverser. Redirects core/hot exhaust C. Cascade reverser. Redirects cold/bypass airflow D. Mechanical blockage reverser. Redirects cold/bypass airflow
A. Mechanical blockage reverser. Redirects core/hot exhaust
How are thrust reverser systems actuated? A. Only hydraulically B. Pneumatically or hydraulically C. Only pneumatically D. Only electrically
B. Pneumatically or hydraulically
What is the name and purpose of the two levers in the yellow circle? A. Afterburners levers. Increase thrust by pushing forward. B. Throttle levers. Change engine RPM by moving forward or aft. C. Piggyback levers. Actuate the thrust reversers by pulling up. D. Piggyback levers. Actuate the thrust reversers by pushing forward.
C. Piggyback levers. Actuate the thrust reversers by pulling up.
What type of airplane is pictured and is reverse thrust available? A. Turbofan. No, thrust reverse is not available. B. Turboshaft. Yes, thrust reverse is available. C. Turboprop. Yes, thrust reverse is available. D. Turboprop. No, thrust reverse is not available.
C. Turboprop. Yes, thrust reverse is available. Note: We can tell it is a turboprop because we see prop controls in the right. Afterward, we can also tell that it has a reverse according to the placards below the "POWER" levers.
What is beta mode in a turboprop airplane? A. Beta mode is not available in a turboprop airplane. B. When the propeller enters either minimum pitch or reverse pitch. C. Only when the propeller enters minimum pitch D. Only when the propeller enters reverse thrust. E. When the propellor just got into open beta for play testing.
B. When the propeller enters either minimum pitch or reverse pitch.
What is the general name and purpose of these three components? A. Bearing. Cause the engine shaft to rotate. B. Bearing. Absorb and transfer engine loads, allow engine shaft expansion, and support the rotating shafts. C. Seal. Allow the oil between engine components. D. Seal. Prevent oil flow between engine components.
B. Bearing. Absorb and transfer engine loads, allow engine shaft expansion, and support the rotating shafts.
What is the name of this component? A. Plain bearing B. Roller bearing C. Carbon seal D. Ball bearing
B. Roller bearing
What type(s) of load(s) (force) is/are parallel to the engine shaft? A. Radial and axial B. Axial C. Centrifugal D. Radial
B. Axial
What type(s) of load(s) (force) is/are perpendicular to the engine shaft? A. Thrust B. Radial C. Axial D. Radial and axial
B. Radial
Bearing A Bearing B Which type of bearing allows for axial expansion of the engine shaft? A. Bearing A...ball bearing B. Bearing B...ball bearing C. Bearing B...roller bearing D. Bearing A...roller bearing
C. Bearing B...roller bearing
What is the name and purpose of this component? A. Labyrinth seal. Reduce oil movement while allowing air movement B. Brush seal. Reduce oil movement while allowing air movement. C. Carbon bearing. Support engine shaft loads. D. Carbon seal. Reduce oil and air movement.
A. Labyrinth seal. Reduce oil movement while allowing air movement
Why do labyrinth seals allow air movement through the seal? A. Air flow through the seal helps pressurize the bearing. B. Air flow through the seal helps oil to escape into the scavenge system. C. Air flow is not allowed through a labyrinth seal. D. Air flow through the seal prevents oil from exiting the seal.
D. Air flow through the seal prevents oil from exiting the seal.
Seal A Seal B Which type of seal allows the least amount of air to pass through? 1). Seal A. Carbon seal 2). Seal B. Carbon seal 3). Seal A. Labyrinth seal 4). Seal B. Labyrinth seal
4). Seal B. Labyrinth seal
What type of seal is pictured and what are the benefits of this seal compared to a labyrinth seal? A. Brush seal. Increased airflow through the seal for increased pressurization. B. Carbon seal. Decreased airflow through the seal. C. Carbon seal. Increased airflow through the seal for increased pressurization D. Brush seal. Decreased air and oil leakage.
D. Brush seal. Decreased air and oil leakage.
What is true of many turbine engine lubrication systems? A. They consume more oil per hour and use wet-sump systems. B. They consume less oil per hour and use dry-sump systems. C. They consume less oil per hour and use wet-sump systems. D. They consume more oil per hour and use dry-sump systems.
B. They consume less oil per hour and use dry-sump systems.
Airplane A (reciprocating) Airplane B What is true regarding the lubrication system purpose in these airplanes? 1). The purpose is the same 2). Airplane A does not oil for sealing 3). Airplane B does not use oil for cleaning 4). Airplane B does not use oil for cooling
1). The purpose is the same
Oil A Oil B Which oil is thicker at high temperatures? 1). Oil A has a higher viscosity 2). The image does not supply enough information 3). The viscosities are the same 4). Oil B has a higher viscosity
3). The viscosities are the same Note: the right-hand digits represent the oil viscosity at higher temps. As they share the same numbers (50), that means that the viscosities are the same at hot temps.
Oil A Oil B Which oil is more appropriate for cold-weather operations and why? 1). Oil A because it has a higher cold-weather viscosity 2). Oil B because it has a higher cold-weather viscosity 3). Oil B because it has a lower cold-weather viscosity 4). Oil A because it has a lower cold-weather viscosity
4). Oil A because it has a lower cold-weather viscosity Note: This is borrowed from the concept in car engine oils, but generally speaking you would want lower viscosity for lower temperatures as it would be able to flow a lot better.
Oil A (5 centistoke) Oil B (3 centistoke) Which oil is better suited for low-temperature operations and why? 1). Oil A because it has a higher cold-weather viscosity 2). Oil B because it has a higher cold-weather viscosity 3). Oil B because it has a lower cold-weather viscosity 4). Oil A because it has a lower cold-weather viscosity
3). Oil B because it has a lower cold-weather viscosity Note: This is borrowed from the concept in car engine oils, but generally speaking you would want lower viscosity for lower temperatures as it would be able to flow a lot better. As for how we can tell which has a lower viscosity, the primary method that will probably be more reliable is by looking at the "centistoke" number. The lower it is, the less viscous. You could probably also rely on the "256" and "560" as well, but just be cautiou…
Pump A Pump B Pump C What type of pump is Pump C? A. Gear-rotor pump B. Gear pump C. Gerotor pump D. Rotary vane pump
D. Rotary vane pump
The oil filter becomes clogged. What (if any) indication(s) do you expect to see in the cockpit? A. High oil temperature B. Low oil pressure C. No change in oil pressure D. High oil pressure
D. High oil pressure
You see this annunciation (Crew Alerting System message...CAS MSG) on the G1000 PFD in your Cessna Caravan turboprop. What is the message's meaning? A. At least one compressor blade is failing B. At least one turbine blade is failing C. A seal has failed D. Metallic chips have been detected in the oil
D. Metallic chips have been detected in the oil
What is/are the primary method(s) by which oil is cooled? A. Air, fuel, coolant B. Only coolant C. Only air D. Only fuel
A. Air, fuel, coolant
What is the name of the system that returns oil to the tank from locations such as the bearings and gearbox? A. Boost pump B. Vent system C. Scavenge system D. Bypass valve
C. Scavenge system
Why do the No. 1, 1.5, 2, and 3 bearing compartments include a breather air line? **Bearing compartments are near the top-center of the image** A. To remove the oxidized particles in the oil B. The bearings are pressurized to prevent foaming C. The oil absorbs air from the deoiler D. Air pressure is the primary means of moving oil Note: If image is difficult to read, please open image in another tab.
B. The bearings are pressurized to prevent foaming
Bearing A Bearing B Bearing C What type of bearing is Bearing B? 1). Roller bearing 2). Thrust bearing 3). Plain bearing 4). Ball bearing
3). Plain bearing
Bearing A Bearing B Bearing C Which type of bearing allows for the greatest/maximum axial expansion of the engine shaft? 1). Bearing B 2). Bearing B and Bearing C 3). Bearing C 4). Bearing A
4). Bearing A (roller bearing)
During maneuvering, gyroscopic precession of the compressor fan creates a force that is perpendicular to the engine shaft. What is that force called? A. Radial load B. Expansion load C. Axial load D. Compression load
A. Radial load
What is the purpose of this engine component? A. Increase the speed at which the engine shaft spins B. Decrease the speed at which the engine shaft spins C. Absorb loads and transfer the loads to the aircraft frame D. Decrease or eliminate the movement of lubrication and contaminants.
C. Absorb loads and transfer the loads to the aircraft frame
What type of seal is used to seal this bearing? A. Labyrinth seal B. Carbon seal C. Brush seal D. Plain seal
A. Labyrinth seal Note: Even though it may not seem like it, this stupid image actually shows a labyrinth seal. The indicators seem arbitrary, but the radial lines we see (especially at the center with the "s" like structure) is the main thing to look for x_x
Which statement is true regarding these two seals? Seal A Seal B Which statement is true regarding these two seals? A. Both seals allow airflow through the seal B. Only Seal B allows airflow through the seal C. Neither seal allows airflow through the seal D. Only Seal A allows airflow through the seal
A. Both seals allow airflow through the seal Note: The main problem is figuring out what Seal A is. Seal B is, of course, a brush seal -> which does allow for air. However, A looks nothing like anything we have seen. The key thing, though, is to look at the radial lines on the structure (especially at the center with that "s" pattern). This helps to indicate that this is actually a labyrinth seal. Seal A = Labyrinth seal Seal B = Brush seal
Cessna SkyCourier (turboprop) Hawker 800XP What statement is true regarding the lubrication system in these aircraft? A. The Hawker burns more oil per hour because it is a turbofan B. Both airplanes have similar rates of oil consumption per hour C. The Cessna burns more oil per hour because it is a turboprop D. Both airplanes have a higher rate of oil consumption than an aircraft with a reciprocating engine
B. Both airplanes have similar rates of oil consumption per hour
Oil A Oil B Which oil is rated for operations at lower temperatures? 1). Oil B because it has a lower cold-weather viscosity 2). Oil B because it has a higher cold-weather viscosity 3). Oil A because it has a lower cold-weather viscosity 4). Oil A because it has a higher cold-weather viscosity
1). Oil B because it has a lower cold-weather viscosity
Oil A Oil B Which oil is most likely thicker? 1). Oil A because it has a lower viscosity 2). Oil B because it has a higher viscosity 3). OIl B because it has a lower viscosity 4). Oil A because it has a higher viscosity
2). Oil B because it has a higher viscosity
What is the meaning of a centistoke (Cs) number on turbine engine oil? 1). Centistoke does not apply to turbine engine oils 2). Cs3 is better suited for high temperature operations than Cs 5 3). Cs 5 is high viscosity because it flows more slowly than Cs 3 4). Cs 3 is high viscosity because it flows more slowly than Cs 5
3). Cs 5 is high viscosity because it flows more slowly than Cs 3
Why does the Boeing 767 fuel system include a fuel-oil heat exchanger? A. Oil helps cool the fuel and the fuel helps heat the oil B. Fuel cools the oil and the oil helps heat the fuel C. The fuel helps decrease the oil viscosity D. The fuel powers the heat exchanger
B. Fuel cools the oil and the oil helps heat the fuel
What conditions might lead to a high oil pressure indication? A. Clogged oil filter or high oil viscosity B. Low oil quantity C. Decreased flow rate due to low oil viscosity D. Decreased flow rate due to high oil temperature
A. Clogged oil filter or high oil viscosity
What type of oil pump is pictured? A. Impeller pump B. Gerotor pump C. Rotary vane pump D. Gear pump
B. Gerotor pump