# Aerodynamics and Aircraft Pt 2 Flashcards

1
Q

(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.

A

A) 2,940 pounds.

2
Q

(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.

A

C) 1,440 pounds.

3
Q

(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.

A

C) 2,400 pounds.

4
Q

(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.

A

B. 9 minutes,

5
Q

(Refer to appendix 2, figure 72.) What is the approximate level-off pressure
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.

A

A) 19,400 feet.

6
Q

(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.

A

B. 17,500 feet.

7
Q

(Refer to appendix 2, figure 72,) What is the approximate level-off pressure
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.

A

C 21,600 feet.

8
Q

(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.

A

C 24,400 feet.

9
Q

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

A

A) Critical engine failure speed.

10
Q

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

A

A) Increases takeoff distance,

11
Q

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.

A

A) When wing lift has been reduced.

12
Q

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.

A

C) The anti-icing protection is very limited.

13
Q

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.

A

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

14
Q

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,

A

A) Apply heated Type 2 fluid.

15
Q

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

A

C Cold.

16
Q

(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%

A

B) 5 1/296,

17
Q

(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
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.

A

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

18
Q

(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,

A

BJ 169,000 lb.

19
Q

(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.

A

A) 110000 lb.

20
Q

(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.

A

A) 136,000 lb.

21
Q

(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,

A

C) 163.1 knots,

22
Q

(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
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.

A

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

23
Q

(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

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

A

BJ 168 knots.

24
Q

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.

A

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

25
Q

Which Freezing Point Depressants are least effective?

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

A

A) Type 1.

26
Q

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,

A

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

27
Q

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.

A

C) delay boundary layer separation.

28
Q

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

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

A

A) stabilizing,

29
Q

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

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

A

B 19%.

30
Q

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.

A

B a 21 percent increase in kinetic energy.

31
Q

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.

A

C excessive pitch rotation may preclude a successful takeoff.

32
Q

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,

A

A) engine thrust decreases horizontal stabilizer effectiveness.

33
Q

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.

A

A) Mach 0.70 to Mach 0.90.

34
Q

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,

A

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

35
Q

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.

A

A) a stall could occur prior to stall warning.

36
Q

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,

A

C) High climb attitude and low airspeed,

37
Q

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.

A

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

38
Q

Deploying spoilers upon landing

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

A

C) increases braking effectiveness and decreases lift.

39
Q

Spoilers will

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

A

B help eliminate adverse yaw in a turn.

40
Q

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.

A

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

41
Q

(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
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.

A

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

42
Q

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.

A

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

43
Q

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.

A

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

44
Q

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.

A

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

45
Q

(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,

A

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

46
Q

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,

A

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

47
Q
A