Piper Seminole Aircraft Systems

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| By Eduardo Mijares
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Eduardo Mijares
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Piper Seminole Aircraft Systems - Quiz

Instructions. Please read.
After completing Unit 3 of the Multiengine Addon Training Course, you must take this quiz. The minimum passing grade is 80%.
If you fail the quiz, please review Unit 3. Put special attention on the questions you got wrong in the quiz. You may retake the quiz until you get 80% at least.
After successfully completing the quiz, you will get a completion certificate that you must download and keep in your records as proof of passing this quiz. This certificate is a requirement to receive credit for the Unit and graduation of the Course. Please type Read moreyour name in the fields below for your completion certificate after passing the quiz.


Questions and Answers
  • 1. 

    Which type of engines is the seminole equipped with?

    • A.

      Lycoming TO-320

    • B.

      Continental TIO-520

    • C.

      Lycoming (L)TO-360

    • D.

      Continental O-200

    Correct Answer
    C. Lycoming (L)TO-360
    Explanation
    The seminole is equipped with a Lycoming (L)TO-360 engine.

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  • 2. 

    What is the rated power of the Piper Turbo Seminole engines?

    • A.

      200 horsepower at 2700 RPM

    • B.

      180 horsepower at 2700 RPM

    • C.

      160 horsepower at 2575 RPM

    • D.

      180 horsepower at 2575 RPM

    Correct Answer
    D. 180 horsepower at 2575 RPM
    Explanation
    The rated power of the Piper Turbo Seminole engines is 180 horsepower at 2575 RPM. This means that the engines are designed to produce a maximum power output of 180 horsepower when running at a speed of 2575 RPM.

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  • 3. 

    How is the propeller driven on the Piper Turbo Seminole engines?

    • A.

      Reduction Gearbox Drive

    • B.

      Direct Drive

    • C.

      Non-Direct Drive

    Correct Answer
    B. Direct Drive
    Explanation
    The propeller on the Piper Turbo Seminole engines is driven through a direct drive system. This means that the propeller is directly connected to the engine crankshaft, without the use of any intermediate components such as a reduction gearbox. This type of drive system is simple and efficient, as it allows for a direct transfer of power from the engine to the propeller.

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  • 4. 

    The Piper Turbo Seminole engines are not susceptible to induction icing:

    • A.

      True

    • B.

      False

    Correct Answer
    A. True
    Explanation
    The Piper Turbo Seminole engines are not susceptible to induction icing because they are equipped with a turbocharger. The turbocharger compresses the air before it enters the engine, which raises the temperature and prevents the formation of ice. This feature makes the Piper Turbo Seminole engines less prone to induction icing compared to engines without a turbocharger.

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  • 5. 

    How many blades does the propeller of each engine has?

    • A.

      1 blade

    • B.

      2 blades

    • C.

      3 blades

    • D.

      4 blades

    Correct Answer
    B. 2 blades
    Explanation
    The propeller of each engine has 2 blades.

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  • 6. 

    This is the capability of a propeller to change the blade angle:

    • A.

      Full Feathering

    • B.

      Constant Speed

    • C.

      Controllable Pitch

    Correct Answer
    C. Controllable Pitch
    Explanation
    Controllable pitch refers to the capability of a propeller to change the blade angle. This means that the pitch of the propeller blades can be adjusted in order to optimize the performance of the aircraft. By changing the blade angle, the pilot can control the amount of thrust generated by the propeller, allowing for better efficiency and performance in different flight conditions. This feature is particularly useful in aircraft with variable speed engines, as it allows for fine-tuning of the propeller's performance to match the engine's power output.

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  • 7. 

    This is the capability of the propeller blades to align with the relative wind to decrease drag:

    • A.

      Full Feathering

    • B.

      Constant Speed

    • C.

      Controlable Pitch

    Correct Answer
    A. Full Feathering
    Explanation
    Full feathering refers to the ability of the propeller blades to rotate parallel to the airflow, reducing drag. This feature is commonly used in aircraft to optimize performance during engine shutdown or in emergency situations. By feathering the propeller blades, the aircraft's drag is minimized, allowing for better glide performance and increased safety.

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  • 8. 

    The propeller governor constantly varies oil pressure into the propeller hub to change the propeller blade pitch. This is known as:

    • A.

      Full Feathering

    • B.

      Constant Speed

    • C.

      Controlable Pitch

    Correct Answer
    B. Constant Speed
    Explanation
    The correct answer is Constant Speed. The propeller governor is responsible for maintaining a constant speed of the propeller by constantly adjusting the oil pressure into the propeller hub, which in turn changes the pitch of the propeller blades. This allows the propeller to maintain a consistent rotational speed, regardless of changes in engine power or aircraft speed.

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  • 9. 

    Regardless of the propeller lever position, what will happen when oil pressure is lost?

    • A.

      Propeller will not feather.

    • B.

      Propeller will feather if the RPM are above 950

    • C.

      Propeller will feather if the RPM are below 950

    • D.

      Propeller will feather regardless of the RPM

    Correct Answer
    B. Propeller will feather if the RPM are above 950
    Explanation
    When oil pressure is lost, the propeller will not feather regardless of the propeller lever position. However, if the RPM (Revolution Per Minute) is above 950, the propeller will feather. This means that the blades of the propeller will rotate into a position parallel to the airflow to reduce drag. If the RPM is below 950, the propeller will not feather, indicating that the propeller blades will remain in their current position.

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  • 10. 

    The landing gear on the Seminole is:

    • A.

      Manually operated

    • B.

      Electrically operated

    • C.

      Hydraulically actuated, electrically operated

    • D.

      Electrically actuated, hydraulically operated

    Correct Answer
    C. Hydraulically actuated, electrically operated
    Explanation
    The landing gear on the Seminole is hydraulically actuated, which means that it is controlled by hydraulic power. This allows for smooth and efficient operation of the landing gear. Additionally, the landing gear is also electrically operated, meaning that it can be controlled and operated using electrical power. This combination of hydraulic and electrical operation ensures reliable and effective functioning of the landing gear system on the Seminole aircraft.

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  • 11. 

    The landing gear is held up by:

    • A.

      Mechanical up locks 

    • B.

      Hydraulic pressure

    • C.

      Electrical actuators

    • D.

      Spring system

    Correct Answer
    B. Hydraulic pressure
    Explanation
    The landing gear is held up by hydraulic pressure. Hydraulic pressure is used to activate the hydraulic cylinders that extend and retract the landing gear. This pressure is created by hydraulic pumps and is controlled by the pilot through the use of hydraulic valves. The hydraulic system provides the necessary force to lift and support the weight of the aircraft during landing and takeoff.

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  • 12. 

    The landing gear horn will sound:

    • A.

      When power is approximately below 15” with the landing gear up

    • B.

      Airspeed is below 88 KIAS and the gear is up

    • C.

      Flaps 25 or 40 are selected and the landing gear is not down

    • D.

      Landing gear handle is selected up on ground

    • E.

      RPMs drop below 2300 and the landing gear is up

    Correct Answer(s)
    A. When power is approximately below 15” with the landing gear up
    C. Flaps 25 or 40 are selected and the landing gear is not down
    D. Landing gear handle is selected up on ground
    Explanation
    The landing gear horn will sound when power is approximately below 15" with the landing gear up because this indicates that the aircraft is in a low-power configuration, which could be a potential hazard if the gear is not down. The horn also sounds when flaps 25 or 40 are selected and the landing gear is not down, as this indicates that the aircraft is configured for landing but the gear is still retracted. Additionally, the horn sounds when the landing gear handle is selected up on the ground, which is a safety reminder to ensure that the gear is down before takeoff.

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  • 13. 

    Gear retraction on ground is prevented by:

    • A.

      Squat switch on the right main landing gear

    • B.

      Squat switch on the left main landing gear

    • C.

      Landing gear handle

    • D.

      Hydraulic pressure trapped by a valve

    Correct Answer
    B. Squat switch on the left main landing gear
    Explanation
    The squat switch on the left main landing gear prevents gear retraction on the ground. This switch is designed to detect when the aircraft is on the ground and the weight of the aircraft is resting on the landing gear. When the switch senses this weight, it sends a signal to the aircraft's systems to prevent the gear from retracting. This safety feature ensures that the landing gear remains extended while the aircraft is on the ground, providing stability and support during taxiing, takeoff, and landing.

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  • 14. 

    If hydraulic pressure is lost, the landing gear:

    • A.

      Won’t operate up or down

    • B.

      Will free fall down

    • C.

      Will stay up

    Correct Answer
    B. Will free fall down
    Explanation
    If hydraulic pressure is lost, the landing gear will free fall down. This is because hydraulic pressure is necessary to control the movement of the landing gear. Without the pressure, there is no force to keep the landing gear in the up position, causing it to fall down under gravity.

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  • 15. 

    Emergency landing gear extension is limited to:

    • A.

      88 KIAS

    • B.

      100 KTAS

    • C.

      100 KIAS

    • D.

      140 KIAS

    Correct Answer
    C. 100 KIAS
    Explanation
    The correct answer is 100 KIAS. KIAS stands for Knots Indicated Airspeed, which is the speed at which the aircraft is moving through the air as indicated on the airspeed indicator. The emergency landing gear extension is limited to this speed to ensure the safety and effectiveness of the landing gear deployment. Going above this speed may cause damage to the landing gear or compromise the aircraft's stability during landing.

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  • 16. 

    The Seminole is equipped with brakes on:

    • A.

      Main landing gear

    • B.

      Nose landing gear

    • C.

      Nose and main landing gear

    Correct Answer
    A. Main landing gear
    Explanation
    The correct answer is "Main landing gear." This means that the Seminole aircraft has brakes only on its main landing gear. It does not have brakes on its nose landing gear.

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  • 17. 

    Parking brake is permitted to be used during training flights at TecBlue:

    • A.

      True

    • B.

      False

    Correct Answer
    B. False
    Explanation
    During training flights at TecBlue, parking brake is not permitted to be used.

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  • 18. 

    The Seminole is equipped with this type of flap system

    • A.

      Electrical

    • B.

      Hydraulic

    • C.

      Pneumatic 

    • D.

      Manual

    Correct Answer
    D. Manual
    Explanation
    The Seminole is equipped with a manual flap system. This means that the pilot has to physically manipulate the flaps using a manual lever or control in the cockpit. This type of flap system does not rely on any external power sources such as electricity, hydraulics, or pneumatics. Instead, the pilot has direct control over the flaps, allowing for precise adjustments during flight.

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  • 19. 

    The Piper Seminole has the following wing flaps positions:

    • A.

      0

    • B.

      5

    • C.

      10

    • D.

      20

    • E.

      25

    • F.

      30

    • G.

      36

    • H.

      40

    • I.

      46

    Correct Answer(s)
    A. 0
    C. 10
    E. 25
    H. 40
    Explanation
    The Piper Seminole has multiple wing flap positions, including 0, 10, 25, and 40 degrees. These positions allow the pilot to adjust the lift and drag characteristics of the aircraft during different phases of flight. The 0-degree position is likely used for takeoff and landing when maximum lift is required. The 10-degree position may be used for climb or cruise when a moderate amount of lift is needed. The 25-degree position may be used for approach and landing to provide additional lift and drag. The 40-degree position is likely used for short field landings or steep descents when maximum lift and drag are required.

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  • 20. 

    Pitot tube and static port are combined together and located on the:

    • A.

      Nose

    • B.

      Left wing

    • C.

      Right wing

    • D.

      Tail

    Correct Answer
    B. Left wing
    Explanation
    The correct answer is Left wing because the pitot tube and static port are typically located on the left wing of an aircraft. The pitot tube measures the dynamic pressure of the airflow, while the static port measures the static pressure. By combining these two measurements, the airspeed and altitude of the aircraft can be accurately determined. Placing them on the left wing helps to minimize any interference from the aircraft's structure and ensure accurate readings.

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  • 21. 

    Total usable fuel on the Piper Seminole is:

    • A.

      100 gals (50 per side)

    • B.

      108 gals (54 per side)

    • C.

      110 gals (55 per side)

    • D.

      116 gals (58 per side

    Correct Answer
    B. 108 gals (54 per side)
    Explanation
    The correct answer is 108 gals (54 per side) because the Piper Seminole has a total usable fuel capacity of 108 gallons, with 54 gallons of fuel available on each side.

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  • 22. 

    The electrical system on the Piper Seminole is:

    • A.

      12 Volt

    • B.

      14 Volt

    • C.

      24 Volt

    • D.

      28 Volt

    Correct Answer
    B. 14 Volt
    Explanation
    The electrical system on the Piper Seminole is 14 Volt. This voltage level is commonly used in small aircraft like the Piper Seminole. It is sufficient to power the various electrical components and systems on board the aircraft, including the avionics, lights, and communication systems. The 14 Volt electrical system ensures reliable and efficient operation of these systems during flight.

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  • 23. 

    How many alternators is the Piper Seminole equipped with?

    • A.

      1 on the left engine

    • B.

      1 on the right engine

    • C.

      2, one on each engine

    • D.

      None

    Correct Answer
    C. 2, one on each engine
    Explanation
    The Piper Seminole is equipped with two alternators, one on each engine. Alternators are essential components of an aircraft's electrical system as they generate electricity to power various systems and charge the aircraft's battery. Having two alternators ensures redundancy and reliability in case one fails, allowing for continued operation of electrical systems during flight.

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  • 24. 

    The inboard stall warning detector provides stall warning at:

    • A.

      Flaps 0

    • B.

      Flaps 10 & 25

    • C.

      Flaps 25 & 40

    • D.

      Flaps 40

    Correct Answer
    C. Flaps 25 & 40
    Explanation
    The inboard stall warning detector provides stall warning at flaps 25 & 40. This means that when the aircraft is configured with flaps set at either 25 or 40, the inboard stall warning detector will activate and provide a warning to the pilot if the aircraft is approaching a stall. The stall warning system is crucial for flight safety as it alerts the pilot of an impending stall, allowing them to take appropriate action to avoid it.

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  • 25. 

    The squat switch has two functions on the Piper Seminole when it is on ground:

    • A.

      Prevents the propeller from feathering

    • B.

      Removes power from the hydraulic pump

    • C.

      Disable radio communications 

    • D.

      Deactivates the stall warning

    Correct Answer(s)
    B. Removes power from the hydraulic pump
    D. Deactivates the stall warning
    Explanation
    The squat switch on the Piper Seminole has two functions when the aircraft is on the ground. One function is to remove power from the hydraulic pump, which helps to prevent unnecessary wear and tear on the pump. The other function is to deactivate the stall warning, as the aircraft is not expected to stall while on the ground.

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