Aerodynamics and Aircraft Pt 2

Question 1

(Refer to appendix 2, figures 68 and 69.) What is the approximate fuel consumed
when holding under Operating Conditions 0-3?
A) 2,940 pounds.
8) 2520 pounds.
q 3,250 pounds.

Answer 1

A) 2,940 pounds.

Question 2

(Refer to appendix 2, figures 68 and 69,) What is the approximate fuel consumed
when holding under Operating Conditions 0-4?
A) 2,870 pounds.
3) pounds,
C) 1,440 pounds.

Answer 2

C) 1,440 pounds.

Question 3

(Refer to appendix 2, figures 68 and 69.) What is the approximate fuel consumed
when holding under Operating Conditions 0-5?
A) 2950 pounds.
4870 pounds.
C) 2,400 pounds.

Answer 3

C) 2,400 pounds.

Question 4

(Refer to appendix 2, figure 70.) How many minutes of dump time is required to
reduce fuel load to 16,000 pounds (using 2350 pounds/min)?
Initial weight
175,500 lb
Zero fuel weight 138,000 lb
A) 8 minutes.
B. 9 minutes,
C) 10 minutes.

Answer 4

B. 9 minutes,

Question 5

(Refer to appendix 2, figure 72.) What is the approximate level-off pressure
altitude after drift-down under the given conditions? [Please read the
Explanation,]
Engine Anti-Ice: ON
Wing Anti-lce: OFF
Weight at Failure: 100,000 lbs
ISA Temperature: ISA
Air Conditioning: OFF
A) 19,400 feet.
B) 18,000 feet,
C) 20,200 feet.

Answer 5

A) 19,400 feet.

Question 6

(Refer to appendix 2, figures 71 and 72.) What is the approximate level-off
pressure altitude after drift-down under Operating Conditions 0-2?
A) 14,700 feet,
B. 17,500 feet.
C 18,300 feet.

Answer 6

B. 17,500 feet.

Question 7

(Refer to appendix 2, figure 72,) What is the approximate level-off pressure
altitude after drift-down under the given conditions? [Please Read the
Explanation.]
Engine and Wing Anti-lce: ON
Weight at Failure: 90,000 lbs
ISA Temperature: -IO ‘C
Air Conditioning: OFF
A) 2Z200feet.
BJ 19,800 feet.
C 21,600 feet.

Answer 7

C 21,600 feet.

Question 8

(Refer to appendix 2, figures 71 and 72.) What is the approximate level-off
pressure altitude after drift-down under Operating Conditions 04?
A) 27,900 feet,
BJ 2200 feet.
C 24,400 feet.

Answer 8

C 24,400 feet.

Question 9

Which performance factor decreases as airplane gross weight increases?
A) Critical engine failure speed.
B Rotation speed.
C) Accelerate-stop distance,

Answer 9

A) Critical engine failure speed.

Question 10

What effect does an uphill runway slope have upon takeoff performance?
A) Increases takeoff distance,
B Decreases takeoff speed.
C) Decreases takeoff distance,

Answer 10

A) Increases takeoff distance,

Question 11

Under which condition during the landing roll are the main wheel brakes at
maximum effectiveness?
A) When wing lift has been reduced.
BJ At high groundspeeds,
C) When the wheels are locked and skidding.

Answer 11

A) When wing lift has been reduced.

Question 12

Which is a disadvantage of the one-step over the two-step process when
deicing/anti-icing an airplane?
A) It is more complicated.
BJ The holding time is increased.
C) The anti-icing protection is very limited.

Answer 12

C) The anti-icing protection is very limited.

Question 13

Which procedure increases holding time when deicing/anti-icing an airplane
using a two-step process?
A) Heated Type 1 fluid followed by cold Type 2 fluid,
B Cold Type 2 fluid followed by hot Type 2 fluid,
C) Heated Type 1 or 2 fluid followed by cold Type 1 fluid.

Answer 13

A) Heated Type 1 fluid followed by cold Type 2 fluid,

Question 14

Which of the following will decrease the holding time during anti-icing using a
two-step process?
A) Apply heated Type 2 fluid.
B Decrease the water content.
C) Increase the viscosity of Type 1 fluid,

Answer 14

A) Apply heated Type 2 fluid.

Question 15

What should the deice/anti-ice fluid temperature be during the last step of a two-
phase process?
A) Hot,
B Warm.
C Cold.

Answer 15

C Cold.

Question 16

(Refer to appendix 2, figure 240.) Given the following conditions, what is the stab
trim setting?
Flaps: 15
Weight:160,000 lb.
C.G. (%MAC): 24%

A) 41/4%.
B) 5 1/296,
C 6%

Answer 16

B) 5 1/296,

Question 17

(Refer to appendix 2, figures 237, 738.) Given the following conditions, what are
the takeoff V speeds?
Weight:
Flaps:
170,000 lb.
Field pressure altitude: 5431 ft.
Runway slope: 1%
Temp: 16’ c
Wind:10 KTS Headwind
Runway condition:Dry
VR round LIP

A) VI 139 kts„ VR 137 kts., V2 141 kts.
B VI 138 kts., VR 138 kts., V2 141 kts.
C VI 137 kts„ VR 137 kts., V2 140 kts.

Answer 17

B VI 138 kts., VR 138 kts., V2 141 kts.

Question 18

(Refer to appendix 2, figure 730,) Given the following conditions, what is the
takeoff field limit weight?
Temperature (OAT): 38 c
Pressure Altitude:14 ft.
Field length available: 9401 ft.
Runway slope: 0%
Wind (KTS) Tailwind: 3
Engine bleed for packs: On
Anti-ice: off
A) 167,200 lb.
BJ 169,000 lb.
C 173,000 lb,

Answer 18

BJ 169,000 lb.

Question 19

(Refer to appendix 2, figure 232.) Given the following conditions, what is the
takeoff climb limit?
Airport OAT: 30 c
Airport Pressure Altitude: 5431 ft.
Flaps: 25
Engine bleed for packs: On
Anti-ice: off

A) 110000 lb.
8) 118,300 lb.
q 120,000 lb.

Answer 19

A) 110000 lb.

Question 20

(Refer to appendix 2, figure 231 Given the following conditions, what is the
takeoff climb limit?
Airport OAT: 38 c
Airport Pressure Altitude: 14 ft.
Flaps: 15
Engine bleed for packs: On
Anti-ice: off

(Refer to appendix 2, figure 231 Given the following conditions, what is the
takeoff climb limit?
Airport OAT:
Airport Pressure Altitude: 14 ft.
Flaps:
Engine bleed for packs: On
Anti-ice:
A) 136,000 lb.
B 137,500 lb.
C 139,000 lb.

Answer 20

A) 136,000 lb.

Question 21

(Refer to appendix 2, figure 73’t.) What is the takeoff Brake Energy Limit speed
(VM8E)?
Weight:
140000 lbs
Pressure Altitude: 6500 feet
OAT: -18 c
Runway Slope: 0.5% downhill
Tailwind: 3 knots

A) 170 knots.
8) 168.5 knots.
C) 163.1 knots,

Answer 21

C) 163.1 knots,

Question 22

(Refer to appendix 2, figures 237, 738,) Given the following conditions, what are
the takeoff V speeds?
Weight: 160,000 lb.
Flaps: 25
Field pressure altitude: 4240 ft,
Runway slope:0%
Tempt 0 c
Wind: 10 KTS Headwind
Runway condition: Dry
VR round LIP

A) VI 132 kts., VR 132 kts., V2136 kts.
B) VI 139 kts„ VR 139 kts„ V2 141 kts.
C) VI 134 kts., VR 135 kts., V2 141 kts.

Answer 22

A) VI 132 kts., VR 132 kts., V2136 kts.

Question 23

(Refer to appendix 2, figure 734.) What is the takeoff Brake Energy Limit speed
(VM8E)?
Weight:160000 lbs
Pressure Altitude: 5431 feet
OAT: -18tc
Runway Slope: 1% uphill
Headwind: 10 knots

A) 164 knots.
BJ 168 knots.
C) 162 knots.

Answer 23

BJ 168 knots.

Question 24

Free directional oscillation is

A) the result of three oscillations, pitch, roll and yaw about their respective axis.
B a coupled lateral/directional oscillation that is usually dynamically stable.
C) a coupled oscillation that is usually dynamically unstable.

Answer 24

B a coupled lateral/directional oscillation that is usually dynamically stable.

Question 25

Which Freezing Point Depressants are least effective?

A) Type 1.
BJ Type 2.
C) Heated Type 1 followed by cold Type 2.

Answer 25

A) Type 1.

Question 26

At the aft CG limit the horizontal stabilizer and elevator

A) will require less movement to maintain level flight.
B can be trimmed to closer to neutral and be very heavy on the controls.
C) must develop less down force to balance the decreased forward loading,

Answer 26

C) must develop less down force to balance the decreased forward loading,

Question 27

Vortex generators are designed to

A) separate the boundary layer from the turbulent airflow above it.
B slow boundary airflow to prevent separation.
C) delay boundary layer separation.

Answer 27

C) delay boundary layer separation.

Question 28

If an engine’s thrust line is above the center of gravity, it is

A) stabilizing,
B destabilizing.
C) of little consequence to stability,

Answer 28

A) stabilizing,

Question 29

A headwind which is 10% of the landing airspeed will reduce the landing distance

A) 11%,
B 19%.
C 22%

Answer 29

B 19%.

Question 30

A landing weight increase of IO percent will result in

A) a 7 percent increase in kinetic energy.
B a 21 percent increase in kinetic energy.
C) a 33 percent increase in kinetic energy.

Answer 30

B a 21 percent increase in kinetic energy.

Question 31

During takeoff

A) pitch control is a relatively minor skill requirement,
B pitch rotation is not an important factor in performance calculations,
C excessive pitch rotation may preclude a successful takeoff.

Answer 31

C excessive pitch rotation may preclude a successful takeoff.

Question 32

If the engine thrust line is below the center of gravity

A) engine thrust decreases horizontal stabilizer effectiveness.
BJ a power increase will tend to raise the nose.
C) reverse thrust will tend to raise the nose,

Answer 32

A) engine thrust decreases horizontal stabilizer effectiveness.

Question 33

Civilian jet airplanes normally operate in a cruise speed range of

A) Mach 0.70 to Mach 0.90.
BJ Mach 0.72 to Mach 0.95.
C) Mach 0.75 to Mach 0.96.

Answer 33

A) Mach 0.70 to Mach 0.90.

Question 34

What are some characteristics of an airplane loaded with the CG at the forward
limit?

A) Lowest stall speed, lowest cruise speed, and highest stability,
B Highest stall speed, lowest cruise speed, and highest stability.
C Highest stall speed, highest cruise speed, and least stability,

Answer 34

B Highest stall speed, lowest cruise speed, and highest stability.

Question 35

Takeoff with ice, snow, or frost is hazardous because

A) a stall could occur prior to stall warning.
B aircraft pitches up prematurely.
C indicated stall speed decreases.

Answer 35

A) a stall could occur prior to stall warning.

Question 36

On some jet transport airplanes there are two sets of ailerons. You would expect
the outboard ailerons to control the airplane under what circumstance?

A) High altitude and high airspeed,
BJ High altitude and turbulent air conditions.
C) High climb attitude and low airspeed,

Answer 36

C) High climb attitude and low airspeed,

Question 37

With regard to aft CG loading,

A) aircraft handling will be affected even though CG is within range.
BJ aircraft handling will not be affected by an aft CG within range,
C) aircraft handling will be affected about the roll axis.

Answer 37

A) aircraft handling will be affected even though CG is within range.

Question 38

Deploying spoilers upon landing

A) reduces directional stability.
B reduces induced drag.
C) increases braking effectiveness and decreases lift.

Answer 38

C) increases braking effectiveness and decreases lift.

Question 39

Spoilers will

A) cause adverse yaw in a turn.
B help eliminate adverse yaw in a turn.
C) increase lift and decrease drag.

Answer 39

B help eliminate adverse yaw in a turn.

Question 40

At the forward CG limit the horizontal stabilizer and elevator

A) will require more movement to maintain level flight.
8) can be trimmed to closer to neutral and be very heavy on the controls.
C) must develop more down force to balance the increased forward loading.

Answer 40

C) must develop more down force to balance the increased forward loading.

Question 41

(Refer to appendix 2, figures 237, 238,) Given the following conditions, what are
the takeoff V speeds?
Weight: 170,000 lb,
Flaps: 10
Field pressure altitude: 425 ft,
Runway slope:
Temp: 25 c
Wind: 8 Headwind
Runway condition: Wet
VR round UP

A) VI 133 kts., VR 140 kts., V2145 kts,
8) VI 140 kts., VR 140 kts., V2 145 kts.
C) VI 138 kts., VR 141 kts., V2145 kts.

Answer 41

A) VI 133 kts., VR 140 kts., V2145 kts,

Question 42

The purpose of leading edge slats is to

A) delay airflow separation at high angles of attack and slow speeds,
B decrease rate of sink.
C) increase parasite drag to slow the airplane.

Answer 42

A) delay airflow separation at high angles of attack and slow speeds,

Question 43

On a preflight inspection, you notice the elevator trim tab is in the full down
position. You know this will

A) cause the tail of the airplane to move up and the nose to dive down.
B cause the tail of the airplane to move down and the nose to rise.
C) require a zero degree flap setting for a normal takeoff.

Answer 43

B cause the tail of the airplane to move down and the nose to rise.

Question 44

When landing, leading edge flaps are

A) operated in conjunction with spoilers to increase drag.
8) extended to increase pitch down tendency caused by extension of trailing
edge flaps.
C) extended to decrease pitch down tendency caused by extension of trailing
edge flaps.

Answer 44

C) extended to decrease pitch down tendency caused by extension of trailing
edge flaps.

Question 45

(Refer to appendix 2, figure 905.) You see this indication on your PFD. Your
standby indicator reads 120 knots, and the power is set for 120 knots in cruise,
level flight. You decide that the

A) airspeed means the attitude is incorrect,
B pilot tube may be clogged with ice or a bug,
C) standby indicator is defective because there is no red ‘X’ on the speed tape,

Answer 45

B piiot tube may be clogged with ice or a bug,

Question 46

An airplane loaded with the center of gravity at the forward CG limit will

A) have a faster cruise speed.
B require less tail down force to maintain altitude,
C) have a higher stall speed than an aft CG,

Answer 46

C) have a higher stall speed than an aft CG,