QUESTIONS of the DAY for A&P/jar part 66 examinations ANSWER with BRIEF EXPLAINATIONS

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Question of the DAY  for (AIRFRAME) 0230 

Q Which answer is correct  The purpose of a wing dihedral is to:

1. Increase stability about the longitudinal axis.

2. Reduce drag.

3. Increase lift.

4 Improve the structural strength of the wing

.  

CORRECT ANSWER IS

1. Increase stability about the longitudinal axis.

  EXPLANATIONReason:

Dihedral refers to the upward angle of an aircraft’s wings from the horizontal. This design feature provides stability around the longitudinal axis, which runs from the nose to the tail of the aircraft. With dihedral, if an aircraft is rolled to one side, the increased angle of attack on the downward wing produces more lift, helping to level the aircraft and maintain stability.
The other options are incorrect:
  • Reducing drag is not the primary purpose of dihedral.
  • Increasing lift is not directly related to dihedral, although it does contribute to stability, which can help maintain lift.

  • Improving structural strength is not the primary purpose of dihedral, although the wing’s structure is important for its overall performance.

 

 

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Question of the DAY  for (AIRFRAME) 0231

Q In what way are the flight controls in an aircraft that has both ailerons and a rudder operated?

  1.   The ailerons control direction and the rudder controls pitch.

  2.   The ailerons control roll and the rudder controls direction.

  3.   The ailerons control roll and the rudder controls roll.

4   The ailerons control pitch and the rudder controls direction.

CORRECT ANSWER IS 

2. The ailerons control roll and the rudder controls direction.

 EXPLANATION 

  1. Ailerons control roll:

    • Ailerons are located on the outer trailing edges of the wings.

    • They work in opposite directions (one moves up, the other moves down) to create differential lift, causing the aircraft to roll about its longitudinal axis.

    • This rolling motion allows the aircraft to bank, which is essential for turning.

  2. Rudder controls direction:

    • The rudder is located on the vertical stabilizer (tail fin).

    • It controls yaw, which is the rotation of the aircraft around its vertical axis.

    • By deflecting the rudder to the left or right, the nose of the aircraft moves in the corresponding direction, helping to coordinate turns and counteract adverse yaw during roll.

Why the other options are incorrect:

  1. The ailerons control direction and the rudder controls pitch:

    • Incorrect because ailerons do not directly control direction (yaw); they control roll.

    • Rudder does not control pitch; that is the function of the elevators.

  2. The ailerons control roll and the rudder controls roll:

    • Incorrect because the rudder does not control roll; it controls yaw (direction).

  3. The ailerons control pitch and the rudder controls direction:

    • Incorrect because ailerons do not control pitch; that is the function of the elevators.

In summary, aileron = roll and rudder = direction/yaw, making option 2 the correct choice.

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Question of the DAY  for (AIRFRAME) 0232

Q The term “center of gravity” is used to denote:

  1.   The point where the lift and drag forces meet.

  2.   The point where the aircraft’s weight is balanced.

  3.   The point of the center of gravity in a given flight condition.

  4.   The point on the longitudinal axis of the aircraft where the weight is centered.

   

 CORRECT ANSWER  IS

2.  The point where the aircraft’s weight is balanced.

 

 EXPLANATION  

The center of gravity (CG) is the point where the weight of the aircraft can be considered to be concentrated. It is the point where the aircraft would balance if it were placed on a pivot. The CG is a critical factor in an aircraft’s stability and performance, as it affects the way the aircraft responds to control inputs and its overall stability.

The other options are incorrect:
  • Option   refers to the center of pressure, not the center of gravity.
  • Option   is redundant and does not provide a clear definition.

  • Option   is close, but the CG is not necessarily centered on the longitudinal axis. It can vary depending on the aircraft’s design and loading

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Question of the DAY  for (AIRFRAME) 0233  

Q. Which control surface is used to control the pitch of the aircraft?

1   Ailerons.

2   Elevators.

3  Rudder.

  1.   Flaps.

 

CORRECT ANSWER IS  :

  • 2. Elevators.

 EXPLANATION

Elevators are the control surfaces located on the horizontal tail of an aircraft. They are used to control the pitch of the aircraft, which is the movement up or down around the lateral axis. By moving the elevators up or down, the pilot can control the angle of attack of the aircraft, thereby controlling its pitch.

The other options are incorrect:

  • Ailerons (option 1) control roll, which is the movement around the longitudinal axis.
  • Rudder (option 3) controls yaw, which is the movement around the vertical axis.
  • Flaps (option 4) are used to increase lift during takeoff and landing, and to increase drag during descent. They do not control pitch.

ITS  SO  CLEAR NOW 

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Question of the DAY  for (AIRFRAME) 0234

QAn aircraft with high drag and low lift:

1   Will have a lower stall speed.

2   Will require a higher stall speed.

  1.   Will have an increased rate of climb.

4.   Will have an increased rate of descent”

CORRECT ANSWER IS

2. Will require a higher stall speed

  EXPLANATION

An aircraft with high drag and low lift will have a higher stall speed because:

  • High drag means the aircraft will experience more resistance to its motion, making it harder to generate enough lift to fly.
  • Low lift means the aircraft will require a higher airspeed to generate enough lift to counteract its weight.
As a result, the aircraft will require a higher stall speed, which is the minimum speed at which the aircraft can fly without stalling.
The other options are incorrect:
  • Option 1 is incorrect because high drag and low lift would actually increase the stall speed, not decrease it.
  • Option 3 is incorrect because an aircraft with high drag and low lift would not be able to climb efficiently.
  • Option 4 is incorrect because while the aircraft may have a higher rate of descent due to the high drag, this is not directly related to the stall speed.

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Question of the DAY  for (AIRFRAME) 0235

QThe center of pressure is the point where:

  1.   The lift and drag forces are concentrated.

  2.   The lift force is concentrated.

  3.   The drag force is concentrated.

  4.   The weight of the aircraft is concentrated.

CORRECT ANSWER IS

  • 1. The lift and drag forces are concentrated.

 

 

 EXPLANATION

Reason:

The center of pressure (CP) is the point on an airfoil or wing where the total force exerted by the air (including both lift and drag) can be considered to act. It is the point where the sum of all the pressure forces on the airfoil or wing can be represented by a single force vector.
The CP is important because it affects the stability and control of the aircraft. When the CP moves forward or aft, it can change the pitching moment of the aircraft, affecting its stability.
The other options are incorrect:
  • Option 2 is incorrect because the CP is not just the point where the lift force is concentrated, but also where the drag force is concentrated.
  • Option 3 is incorrect because the CP is not just the point where the drag force is concentrated, but also where the lift force is concentrated.
  • Option 4 is incorrect because the CP has nothing to do with the weight of the aircraft, which is concentrated at the center of gravity (CG).

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Question of the DAY  for (AIRFRAME) 0236

Q.  The primary function of a vertical stabilizer is to:

  1.   Increase stability about the vertical axis.

  2.   Increase stability about the longitudinal axis.

  3.   Increase lift.

  4.    Increase drag

 CORRECT ANSWER  IS

  • 1.  Increase stability about the vertical axis.

 

EXPLANATION

The correct answer is:
  • 1. Increase stability about the vertical axis.
Reason:
The primary function of a vertical stabilizer (also known as a fin) is to provide directional stability and control about the vertical axis, also known as the yaw axis. The vertical stabilizer opposes any rotation around the vertical axis, helping to maintain the aircraft’s heading and prevent unwanted yawing motions.
The vertical stabilizer achieves this by:
  • Providing a surface area that creates a restoring moment when the aircraft yaws.
  • Helping to counteract the effects of adverse yaw caused by aileron deflection.
The other options are incorrect:
  • Option 2 is incorrect because stability about the longitudinal axis is provided by the horizontal stabilizer.
  • Option 3 is incorrect because the vertical stabilizer does not produce lift.
  • Option 4 is incorrect because while the vertical stabilizer does produce some drag, its primary function is to provide directional stability.
 

IT IS SO  CLEAR NOW

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Question of the DAY  for (AIRFRAME) 0237

Q. The purpose of the horizontal stabilizer is to:

1Provide stability about the longitudinal axis.

2  Provide stability about the vertical axis.

3    Provide lift and balance about the lateral axis.

4.   Provide drag reduction.

CORRECT ANSWER  IS

3. Provide lift and balance about the lateral axis

EXPLANATION

The horizontal stabilizer is a fixed surface located at the tail of the aircraft. Its primary function is to provide stability and control about the lateral axis (pitch axis), which runs from wingtip to wingtip.

  1. Stability About the Lateral Axis (Pitch Stability):
    • The horizontal stabilizer helps balance the aircraft in pitch (nose-up or nose-down motion).
    • It generates a downward or upward force as needed to counteract the pitching moment caused by the center of gravity and aerodynamic forces.
    • The elevator, attached to the horizontal stabilizer, controls the aircraft’s pitch.

Why the other options are incorrect?

  1. “Provide stability about the longitudinal axis” (Incorrect)
    • Stability about the longitudinal axis (nose-to-tail) is called roll stability, which is mainly controlled by the wing dihedral and vertical stabilizer. The horizontal stabilizer does not play a direct role in roll stability.
  2. “Provide stability about the vertical axis” (Incorrect)
    • Stability about the vertical axis (yaw stability) is controlled by the vertical stabilizer (fin), not the horizontal stabilizer.
  3. “Provide drag reduction” (Incorrect)
    • The horizontal stabilizer is not designed to reduce drag. While aerodynamic efficiency is considered, its primary function is pitch stability and control.

Conclusion:

The horizontal stabilizer provides lift and balance about the lateral axis (pitch stability), making option 3 the correct answer.

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Question of the DAY  for (AIRFRAME) 0238

Q. If the wing is moved to a more positive angle of attack, what will happen to the lift generated by the wing?

      1  Lift will increase.

  1.   Lift will decrease.

  2.   Lift will remain constant.

     4.   Lift will become zero. 

CORRECT ANSWER  IS

  • 1.Lift will increase.

Explanation:

When the wing is moved to a more positive angle of attack, the airflow around the wing changes, creating a greater pressure difference between the upper and lower surfaces of the wing. This increased pressure difference results in an increase in the lift generated by the wing. However, it’s worth noting that if the angle of attack becomes too great, the wing can stall, leading to a sudden decrease in lift. But within the normal operating range, increasing the angle of attack will increase lift

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THESE ANSWERS ARE

 RESEARCHED ANSWERS

and  MOSTLY    EXPLAINED

FOR A STUDENT  SEARCHING  FOR  KNOWLEDGE  UPDATE

THE SOONER  I GET THROUGH THE AIRFRAME  QUESTION & THE RIGHT ANSWER  WITH  EXPLANATIONS      WILL START THE POWER PLANT  QUESTION AND RIGHT ANSWER WITH THE EXPLANATIONS

FOR  EXAMPLE, SAMPLE QUESTION AND ANSWER  COMING SHORTLY 

 When a propeller on a reciprocating engine strikes an object causing the engine to suddenly stop, what should be done to the engine?

  1. Perform a power check to determine internal damage.
  2. Check the fuel screens for metal deposits.
  3. Perform a compression check.
  4. Check the crankshaft for distortion.

CORRECT ANSWER IS

4.Check the crankshaft for distortion.

EXPLANATION

When a propeller strikes an object and causes the engine to suddenly stop, it can cause a sudden shock load on the crankshaft. This can lead to internal engine damage, including crankshaft distortion or bending.
Checking the crankshaft for distortion is critical because:
  • A bent or distorted crankshaft can cause catastrophic engine failure if the engine is restarted.
  • A visual inspection of the crankshaft may not reveal any damage, so a detailed check using specialized tools is necessary.
The other options are incorrect:
  • Option 1: A power check may not reveal internal damage caused by the sudden stop.
  • Option 2: Checking fuel screens for metal deposits may indicate other issues, but it’s not directly related to the sudden engine stop.
  • Option 3: A compression check can indicate engine problems, but it may not specifically reveal crankshaft distortion.

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