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) 0216

Q . .When the lift of an airfoil increases, the drag will:

  1.   Decrease.

2   Not be affected.

  1.   Increase while the lift is changing but will return to its original value.

4.   Also increase.

   

   

 

CORRECT ANSWER IS

4. Also increase.

 .

EXPLAINATION 

When the lift of an airfoil increases, the drag typically increases as well. This relationship arises because of the aerodynamic principle of lift-induced drag:

  1. Induced Drag: This is a component of drag directly associated with lift. When lift increases, the angle of attack usually increases, causing greater air disturbance and stronger vortices at the wingtips, which increase induced drag.

  2. Parasitic Drag: While not directly related to lift, changes in configuration (e.g., extending flaps to increase lift) may also increase parasitic drag.

Thus, the total drag on the airfoil generally increases as the lift increases.

 

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Question of the DAY  for (AIRFRAME) 0217

QThe chord of a wing is measured from:

  1.   Leading edge to trailing edge.

  2.   Wing tip to wing tip.

  3.   Wing attachment point to the wing tip.

4   Maximum upper chamber to the base line. .

  

CORRECT ANSWER IS  1—leading edge to trailing edge.

 EXPLANATION 

The chord of a wing is defined as the straight-line distance between the leading edge and the wing’s trailing edge. This measurement represents the fundamental dimension of the airfoil’s cross-sectional profile.

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Question of the DAY  for (AIRFRAME) 0218 

Q If the right wing of a monoplane is rigged to a greater angle of incidence than designated in the manufacturer’s specifications, it will cause:

  1.   The aircraft to be off balance both laterally and directionally.
  2.   The aircraft to pitch and roll about the lateral axis.
  3.   The aircraft to be out of lateral balance ONLY.
4.   The right wing to have both an increased lift and a decreased drag. 

 CORRECT ANSWER  IS

1. The aircraft to be off balance both laterally and directionally

 EXPLANATION  

    • Increased Angle of Incidence on the Right Wing:

      • The angle of incidence determines the fixed angle at which the wing meets the oncoming airflow.

      • If the right wing has a greater angle of incidence than the specified value, it will generate more lift than the left wing.

    • Lateral Imbalance:

      • The increased lift on the right wing will cause the aircraft to roll to the left because the lift forces on the wings are no longer equal.

    • Directional Imbalance:

      • The increased lift on the right wing will also result in more drag (induced drag increases with lift).

      • This unequal drag between the wings causes a yawing motion, with the nose of the aircraft pulling toward the side with less drag (left side in this case).

    Combined Effect:

    This situation creates both lateral imbalance (roll) and directional imbalance (yaw), which makes the aircraft unstable in flight. Therefore, option 1 is the most comprehensive and correct answer

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Question of the DAY  for (AIRFRAME) 0219  

Q.  Flaps increase the effective lift of an airfoil by:

1   Increasing the angle of attack of the airfoil.

  1.   Increasing the camber of the airfoil.

  2.   Reducing the profile drag.

4.   Introducing drag aft of the center of pressure.  

CORRECT ANSWER IS  :

2. Increasing the camber of the airfoil.

 

EXPLANATION
  • Flaps are devices on the trailing edge of an airfoil that, when deployed, change the shape of the airfoil.
  • By extending flaps, the camber (curvature) of the airfoil is increased, which enhances the lift-generating capability of the wing for a given angle of attack.

Key Points:

  • Increasing the camber improves the wing’s ability to create lift by increasing the pressure difference between the upper and lower surfaces.

  • While flaps slightly increase drag as a side effect, their primary purpose is to enhance lift, especially during takeoff and landing.

Why Not the Other Options?

  1. Increasing the angle of attack: Flaps do not directly increase the wing’s overall angle of attack; they alter the camber instead.

  2. Reducing the profile drag: Flaps actually increase drag to some extent, especially at higher flap settings.

  3. Introducing drag aft of the center of pressure: This is incorrect because the primary purpose of flaps is to enhance lift, not to add drag behind the center of pressure.

 

ITS  SO  CLEAR NOW 

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Question of the DAY  for (AIRFRAME) 0220

Q“Washing-in” the left wing of a monoplane for purposes of rigging corrections after flight test will have what effect on the lift and drag of that wing?

1   Both drag and lift will decrease due to the effect that increase of either has on the other.

  1.   The lift will decrease due to the effect of the drag increase.
  2.   The drag will decrease due to the effect of the lift increase.

4   Both drag and lift will increase due to increased angle of attack.

 

CORRECT ANSWER IS

4. Both drag and lift will increase due to the increased angle of attack.

 

 EXPLANATION

      • “Washing-in” refers to increasing the angle of incidence (angle of attack at zero lift) of a wing. When the left wing of a monoplane is “washed-in,” it is set at a higher angle relative to the airflow.

      1. Effect on Lift:

        • An increased angle of attack results in higher lift, as the airflow over the wing generates a greater pressure differential between the upper and lower surfaces.

      2. Effect on Drag:

        • With the increase in lift, induced drag (a byproduct of lift) also increases. Additionally, the higher angle of attack can increase profile drag due to greater air resistance.

      Summary:

      Both lift and drag will increase because of the higher angle of attack caused by washing-in the wing. This adjustment might be used to balance the aircraft’s flight characteristics but at the cost of increased drag on the adjusted wing.

     

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Question of the DAY  for (AIRFRAME) 0221

Q  The elevators of a conventional aircraft are used to provide rotation about the:

  1.   Longitudinal axis.

  2.   Directional axis.

  3.   Lateral axis.

4.   Vertical axis.   

CORRECT ANSWER IS

3. Lateral axis.

1 

 EXPLANATION  

 .Elevators are control surfaces located on the tail of a conventional aircraft (typically on the horizontal stabilizer).

  • Their primary function is to control the aircraft’s pitch, which causes rotation about the lateral axis.

Key Points:

  • The lateral axis runs from wingtip to wingtip.
  • When the elevators are deflected upward, the tail is pushed downward, causing the nose to rise (pitch up).
  • Conversely, when the elevators are deflected downward, the tail is pushed upward, causing the nose to drop (pitch down).

Why Not the Other Options?

  1. Longitudinal axis: This is controlled by the ailerons, which manage roll.

  2. Directional axis: This is the vertical axis and is controlled by the rudder.

  3. Vertical axis: Again, this is controlled by the rudder, not the elevators

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Question of the DAY  for (AIRFRAME) 0222

Q. An aircraft is controlled directionally about its vertical axis by:

1   The rudder.

2   The elevator(s).

  1.   The ailerons.

  2.   The trim tabs.

 

 CORRECT ANSWER  IS 

1. The rudder.

EXPLANATION

Reason:

  • The vertical axis runs vertically through the center of gravity of the aircraft and governs yaw, which is the side-to-side movement of the aircraft’s nose.

  • The rudder, located on the vertical stabilizer, is the primary control surface used to manage yaw. By deflecting the rudder left or right, the airflow creates a force that rotates the aircraft around the vertical axis.

Why Not the Other Options?

  1. The elevator(s): These control pitch and rotate the aircraft about the lateral axis.
  2. The ailerons: These control roll and rotate the aircraft about the longitudinal axis.
  3. The trim tabs: These are used to reduce pilot effort by maintaining a desired control surface position, but they do not directly control any axis.

IT IS SO  CLEAR NOW

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