ATP-CTP Exam Questions and Verified Answers | Latest
Updated 2026/2027 | Graded A+ | Guaranteed Success.
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 .a .flight
(D) .Kinetic .energy .can .be .traded .for .potential .energy, .and .potential .energy .can .be
.traded .for .kinetic .energy .- .CORRECT .ANSWER-(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 .energy .so .that:
(A) .Kinetic .energy .stays .between .limits .(stall .and .placard)
(B) .Potential .energy .sstays .between .limits .(terrain .and .buffet .altitude)
(C) .Chemical .energy .stays .above .certain .thresholds .(not .running .out .of .fuel)
(D) .All .of .the .above .- .CORRECT .ANSWER-(D) .All .of .the .above
What .is .the .effect .on .total .drag .is .airspeed .slows .below .L/D .Max?
(A) .Drag .increases .because .of .increased .parasite .drag
(B) .Drag .decreases .because .of .lower .induced .drag
(C) .Drag .increases .because .of .increased .induced .drag .- .CORRECT .ANSWER-(C)
.Drag .increses .because .of .increased .induced .drag
A .jet .pilot .flying .at .L/D .Max .is .obtain .best:
(A) .Range
(B) .Endurance
(C) .Ride .Quality .- .CORRECT .ANSWER-(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 .- .CORRECT .ANSWER-(A) .Parasite
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. .- .CORRECT .ANSWER-(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 .aicraft .in .which .airflow .over .any .part .of .the .aircraft .or .structure
.first .reaches, .but .doesn't .exceed, .Mach .1.0. .- .CORRECT .ANSWER-(C) .The .speed .of
.an .aicraft .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 .- .CORRECT .ANSWER-(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 .- .CORRECT .ANSWER-(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 .- .CORRECT .ANSWER-(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. .- .CORRECT .ANSWER-(A) .Greater .than .the
.airplane .weight, .and .the .amount .is .a .function .of .bank .angle
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 .- .CORRECT .ANSWER-(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 .- .CORRECT .ANSWER-(C) .A .severe .moment .or
."Mach .Tuck
Excessive .bank .angles .at .high .altitudes .can .be .hazardous .because:
(A) .The .extra .drag .produced .by .the .turn .can .lead .to .an .excursion .below .L/DMax
(B) .Aircraft .engines .at .higher .altitudes .produce .less .thrust .to .overcome .drag
(C) .The .aircraft .will .be .operating .closer .to .its .buffet .boundaries
(D) .All .of .the .above .- .CORRECT .ANSWER-(D) .All .of .the .above
When .operating .at .a .constant .airspeed .with .a .contact .thrust .setting .at .high .altitude
.(typically .above .FL250) .in .slow .flight .below .L/DMax .airspeed, .any .disturbance
.causing .decrease .in .airspeed .will .result .in .a .further .decrease .in .airspeed .unless
.thrust .in .increased. .High .altitude .recovery .from .slow .flight .while .turning .is .best
.accomplished .by:
(A) .Increasing .thrust .to .arrest .the .slowdown
(B) .Increasing .thrust .to .accelerate .to .airspeed .above .L/DMax .speed
(C) .Increasing .thrust .to .maximum .available .thrust .and .reducing .bank .angle .while
.accelerating .to .airspeed .above .L/D .Max .speed. .In .a .thrust .limited .situation, .exiting
.slow .flight .will .require .an .immediate .descent .as .an .aerodynamic .stall .is .imminent.
.- .CORRECT .ANSWER-(C) .Increasing .thrust .to .maximum .available .thrust .and
.reducing .bank .angle .while .accelerating .to .airspeed .above .L/D .Max .speed. .In .a
.thrust .limited .situation, .exiting .slow .flight .will .require .an .immediate .descent .as .an
.aerodynamic .stall .is .imminent.
Updated 2026/2027 | Graded A+ | Guaranteed Success.
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 .a .flight
(D) .Kinetic .energy .can .be .traded .for .potential .energy, .and .potential .energy .can .be
.traded .for .kinetic .energy .- .CORRECT .ANSWER-(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 .energy .so .that:
(A) .Kinetic .energy .stays .between .limits .(stall .and .placard)
(B) .Potential .energy .sstays .between .limits .(terrain .and .buffet .altitude)
(C) .Chemical .energy .stays .above .certain .thresholds .(not .running .out .of .fuel)
(D) .All .of .the .above .- .CORRECT .ANSWER-(D) .All .of .the .above
What .is .the .effect .on .total .drag .is .airspeed .slows .below .L/D .Max?
(A) .Drag .increases .because .of .increased .parasite .drag
(B) .Drag .decreases .because .of .lower .induced .drag
(C) .Drag .increases .because .of .increased .induced .drag .- .CORRECT .ANSWER-(C)
.Drag .increses .because .of .increased .induced .drag
A .jet .pilot .flying .at .L/D .Max .is .obtain .best:
(A) .Range
(B) .Endurance
(C) .Ride .Quality .- .CORRECT .ANSWER-(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 .- .CORRECT .ANSWER-(A) .Parasite
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. .- .CORRECT .ANSWER-(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 .aicraft .in .which .airflow .over .any .part .of .the .aircraft .or .structure
.first .reaches, .but .doesn't .exceed, .Mach .1.0. .- .CORRECT .ANSWER-(C) .The .speed .of
.an .aicraft .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 .- .CORRECT .ANSWER-(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 .- .CORRECT .ANSWER-(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 .- .CORRECT .ANSWER-(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. .- .CORRECT .ANSWER-(A) .Greater .than .the
.airplane .weight, .and .the .amount .is .a .function .of .bank .angle
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 .- .CORRECT .ANSWER-(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 .- .CORRECT .ANSWER-(C) .A .severe .moment .or
."Mach .Tuck
Excessive .bank .angles .at .high .altitudes .can .be .hazardous .because:
(A) .The .extra .drag .produced .by .the .turn .can .lead .to .an .excursion .below .L/DMax
(B) .Aircraft .engines .at .higher .altitudes .produce .less .thrust .to .overcome .drag
(C) .The .aircraft .will .be .operating .closer .to .its .buffet .boundaries
(D) .All .of .the .above .- .CORRECT .ANSWER-(D) .All .of .the .above
When .operating .at .a .constant .airspeed .with .a .contact .thrust .setting .at .high .altitude
.(typically .above .FL250) .in .slow .flight .below .L/DMax .airspeed, .any .disturbance
.causing .decrease .in .airspeed .will .result .in .a .further .decrease .in .airspeed .unless
.thrust .in .increased. .High .altitude .recovery .from .slow .flight .while .turning .is .best
.accomplished .by:
(A) .Increasing .thrust .to .arrest .the .slowdown
(B) .Increasing .thrust .to .accelerate .to .airspeed .above .L/DMax .speed
(C) .Increasing .thrust .to .maximum .available .thrust .and .reducing .bank .angle .while
.accelerating .to .airspeed .above .L/D .Max .speed. .In .a .thrust .limited .situation, .exiting
.slow .flight .will .require .an .immediate .descent .as .an .aerodynamic .stall .is .imminent.
.- .CORRECT .ANSWER-(C) .Increasing .thrust .to .maximum .available .thrust .and
.reducing .bank .angle .while .accelerating .to .airspeed .above .L/D .Max .speed. .In .a
.thrust .limited .situation, .exiting .slow .flight .will .require .an .immediate .descent .as .an
.aerodynamic .stall .is .imminent.
