ATP CTP Course REAL EXAM 2023/2024 QUESTIONS AND EXPERT VERIFIED ANSWERS ALREADY GRADED A GUARANTEED PASS ASSURED
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ATP CTP Course
ATP CTP Course REAL EXAM 2023/2024
QUESTIONS AND EXPERT VERIFIED ANSWERS
ALREADY GRADED A GUARANTEED PASS
ASSURED
Which of the following statements regarding energy is true?
A. Kinetic energy decreases with increasing airspeed
B. Potential energy is approximately proportional to airspeed
C. ...
which of the following statements regarding energy
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ATP CTP Course REAL EXAM 2023/2024
QUESTIONS AND EXPERT VERIFIED ANSWERS
ALREADY GRADED A GUARANTEED PASS
ASSURED
Which of the following statements regarding energy is true?
A. Kinetic energy decreases with increasing airspeed
B. Potential energy is approximately proportional to airspeed
C. Chemical Energy remains constant throughout flight
D. Kinetic energy can be traded for potential energy and potential energy can be traded for
kinetic energy
D. Kinetic energy can be traded for potential energy and potential energy can be traded for
kinetic energy
The objective in maneuvering the airplane is to manage the energy so that:
A. Kinetic energy stays between limits (stall and placards)
B. Potential energy stays between limits (terrain and buffet altitude)
C. Chemical energy stays above certain thresholds (not running out of fuel)
D. All of the above
D. All of the above
What is the effect on total drag if airspeed slows below L/DMax?
A. Drag increases because of increased parasite drag.
B. Drag decreases because of lower induced drag.
C. Drag increases because of increased induced drag.
C. Drag increases because of increased induced drag
A jet pilot flying at L/DMax will obtain best:
A. Range
B. Endurance
C. Ride Quality
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B. Endurance
When a jet aircraft is flown at the appropriate airspeed for maximum range, which type of drag
predominates?
a. Parasite
b. Induced
c. Each type of drag contributes equally
a. Parasite
While already at high speed, what happens if Mach is allowed to increase?
a. Airflow over parts of the airplane begin to exceed the speed of sound
b. Shock waves can cause local airflow separation
c. Characteristics such as pitch-up, pitch-down, or buffeting may occur.
d. All of the above
d. All of the above
What is the result of a shock-induced separation of airflow occurring symmetrically near the
wing root of a swept wing aircraft?
a. A high-speed stall and sudden pitch-up
b. Severe porpoising.
c. A severe moment or "Mach Tuck".
c. A severe moment or "Mach Tuck".
The speed of sound generally decreases with increasing altitude. This occurs because:
a. The air temperature decreases.
b. The air pressure decreases.
c. The composition of the air changes.
a. The air temperature decreases.
Critical Mach number can be defined as:
a. The speed at which the aircraft is traveling faster than sound.
b. The maximum Mach number at which an aircraft may be safely operated.
c. the speed of an aircraft in which airflow over any part of the aircraft or structure first reaches,
but doesn't exceed, Mach 1.0
, onlystudents
c. the speed of an aircraft in which airflow over any part of the aircraft or structure first reaches,
but doesn't exceed, Mach 1.0
Stability in the vertical axis tends to drive the sideslip angle toward zero. The most dynamic
stability about the vertical axis on modern jet transports is from:
a. The vertical fin
b. The rudder
c. An active stability augmentation system/yaw damper
d. Pilot roll input
c. An active stability augmentation system/yaw damper
Swept wings cause a significant:
a. increase in effectiveness of flaps.
b. Reduction in effectiveness of flaps
c. flap actuation reliability issue
b. Reduction in effectiveness of flaps
Why is convergence of Stall AOA and MMO hazardous?
a. Any decrease in airspeed will cause the aircraft to buffet and potentially stall
b. Any increase in airspeed will cause the aircraft to buffet and potentially cause Mach Tuck
c. Airspeed changes may occur due to environmental factors, without pilot input.
d. All of the above
d. All of the above
To maintain altitude in a banked turn, the lift produced by an airplane must be:
a. Greater than the airplane weight, and the amount is a function of bank angle
b. Greater than the airplane weight, and the amount is a function of altitude
c. Equal to the weight of the airplane
a. Greater than the airplane weight, and the amount is a function of bank angle
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