Which would provide the greatest gain in altitude in the
shortest distance during climb after takeoff? A-Vy B-VA C-Vx.
After takeoff, which airspeed would the pilot use to
gain the most altitude in a given period of time? A-Vy B-Vx C-VA.
What effect does high density altitude, as compared to
low density altitude, have on propeller efficiency and
why? A-Efficiency is increased due to less friction on the
propeller blades. B-Efficiency is reduced because the propeller exerts
less force at high density altitudes than at low
density altitudes. C-Efficiency is reduced due to the increased force of
the propeller in the thinner air.
Which combination of atmospheric conditions will
reduce aircraft takeoff and climb performance? A-Low temperature, low relative humidity, and low
density altitude. B-High temperature, low relative humidity, and low
density altitude. C-High temperature, high relative humidity, and high
density altitude.
What effect does high density altitude have on aircraft
performance? A- It increases engine performance. B- It reduces climb performance. C- It increases takeoff performance.
What effect, if any, does high humidity have on aircraft
performance? A-It increases performance. B- It decreases performance. C- It has no effect on performance.
(Refer to figure 36 on page 8-4.)
Approximately what true airspeed should a pilot expect
with 65 percent maximum continuous power at 9,500
feet with a temperature of 36°F below standard? A-178 MPH. B-181 MPH. C-183 MPH.
(Refer to figure 36 on page 8-4.)
What is the expected fuel consumption for a
1,000-nautical mile flight under the following
conditions?
Pressure altitude ... 8,000 ft
Temperature ... 22°C
Manifold pressure ... 20.8 inches Hg.
Wind ... Calm. A-60.2 gallons. B- 70.1 gallons. C- 73.2 gallons.
(Refer to figure 36 on page 8-4.)
What fuel flow should a pilot expect at 11,000 feet on
a standard day with 65 percent maximum continuous
power? A-10.6 gallons per hour. B- 11.2 gallons per hour. C- 11.8 gallons per hour.
(Refer to figure 36 on page 8-4.)
Determine the approximate manifold pressure setting
with 2,450 RPM to achieve 65 percent maximum
continuous power at 6,500 feet with a temperature of
36°F higher than standard. A-19.8 inches Hg. B-20.8 inches Hg. C-21.0 inches Hg.
(Refer to figure 3 7 on page 8-5.)
What is the headwind component for a landing on
Runway 18 if the tower reports the wind as 220° at 30
knots? A-19 knots. B-23 knots. C-26 knots.
(Refer to figure 37 on page 8-5.)
Determine the maximum wind velocity for a 45°
crosswind if the maximum crosswind component for
the airplane is 25 knots. A-25 knots. B-29 knots. C-35 knots.
(Refer to figure 37 on page 8-5.)
What is the maximum wind velocity for a 30°
crosswind if the maximum crosswind component for
the airplane is 12 knots? A-16 knots. B-20 knots. C-24 knots.
(Refer to figure 3 7 on page 8-5.)
With a reported wind of north at 20 knots, which
runway (6, 29, or 32) is acceptable for use for
an airplane with a 13-knot maximum crosswind
component? A-Runway 6. B-Runway 29. C-Runway 32.
(Refer to figure 37 on page 8-5.)
With a reported wind of south at 20 knots, which
runway ( 10, 14, or 24) is appropriate for an airplane
with a 13-knot maximum crosswind component? A-Runway 10. B-- Runway 14. C-- Runway 24.
(Refer to figure 37 on page 8-5.)
What is the crosswind component for a landing on
Runway 18 if the tower reports the wind as 220° at 30
knots? A-19 knots. B-23 knots. C-30 knots.
(Refer to figure 38 on page 8-8.)
Determine the approximate total distance required to
land over a 50-foot obstacle.
OAT. .. 90°F
Pressure altitude .. .4,000 ft
Weight...2,800 lb
Headwind component... IO kts A-1,525 feet. B- 1,950 feet. C- 1,775 feet.
(Refer to figure 39 on page 8-9.)
Determine the approximate landing ground roll
distance.
Pressure altitude ... Sea level
Headwind .. .4 kts
Temperature ... Std A-356 feet. B-401 feet. C-490 feet.
(Refer to figure 39 on page 8-9.)
Determine the total distance required to land over a
50-foot obstacle.
Pressure altitude ... 7,500 ft
Headwind ... 8 kts
Temperature ... 32°F
Runway ... Hard surface A-1,004 feet. B- 1,205 feet. C- 1,506 feet.
(Refer to figure 39 on page 8-9.)
Determine the total distance required to land over a
50-foot obstacle.
Pressure altitude ... 5,000 ft
Headwind ... 8 kts
Temperature . ..41 °F
Runway ... Hard surface A-837 feet. B-956 feet. C- 1,076 feet.
(Refer to figure 39 on page 8-9.)
Determine the approximate landing ground roll
distance.
Pressure altitude ... 5,000 ft
Headwind ... Calm
Temperature ... 101 °F A-495 feet. B-545 feet. C-445 feet.
(Refer to figure 39 on page 8-9.)
Determine the total distance required to land over a
50-foot obstacle.
Pressure altitude ... 3,750 ft
Headwind ... 12 kts
Temperature ... Std A-794 feet. B-836 feet. C-816 feet.
(Refer to figure 39 on page 8-9.)
Determine the approximate landing ground roll
distance.
Pressure altitude ... l ,250 ft
Headwind ... 8 kts
Temperature ... Std A-275 feet. B-366 feet. C-470 feet.
If an emergency situation requires a downwind
landing, pilots should expect a faster A-airspeed at touchdown, a longer ground roll, and
better control throughout the landing roll. B- groundspeed at touchdown, a longer ground roll,
and the likelihood of overshooting the desired
touchdown point. C- groundspeed at touchdown, a shorter ground roll,
and the likelihood of undershooting the desired
touchdown point.
(Refer to figure 41 on page 8-12.)
Determine the total distance required for takeoff to
clear a 50-foot obstacle.
OAT ... Std
Pressure altitude .. .4,000 ft
Takeoff weight...2,800 lb
Headwind component. .. Calm A-1,500 feet. B-1,750 feet. C- 2,000 feet.
(Ref er to figure 41 on page 8-12.)
Determine the total distance required for takeoff to
clear a 50-foot obstacle.
OAT...Std
Pressure altitude ... Sea level
Takeoff weight...2, 700 lb
Headwind component...Calm A-1,000 feet. B- 1,400 feet. C- 1,700 feet.
(Refer to figure 41 on page 8-12.)
Determine the approximate ground roll distance
required for takeoff.
OAT ... 100°F
Pressure altitude ... 2,000 ft
Takeoff weight...2,750 lb
Headwind component. .. Calm A-1,150 feet. B- 1,300 feet. C-1,800 feet.
(Refer to figure 41 on page 8-12.)
Determine the approximate ground roll distance
required for takeoff.
OAT ... 90°F
Pressure altitude ... 2,000 ft
Takeoff weight... 2,500 lb
Headwind component...20 kts A-650 feet. B-800 feet. C-1,000 feet.
If an emergency situation requires a downwind
landing, pilots should expect a faster A-airspeed at touchdown, a longer ground roll, and
better control throughout the landing roll. B- groundspeed at touchdown, a longer ground roll,
and the likelihood of overshooting the desired
touchdown point. C- groundspeed at touchdown, a shorter ground roll,
and the likelihood of undershooting the desired
touchdown point.....
Which items are included in the empty weight of an
aircraft? A · Unusable fuel and undrainable oil B · Only the airframe, powerplant, and optional
equipment C- full fuel tanks and engine oil to capacity.
An aircraft is loaded 110 pounds over maximum
certificated gross weight. If fuel (gasoline) is drained to
bring the aircraft weight within limits, how much fuel
should be drained? A-15.7 gallons. B- 16.2 gallons. C-18.4 gallons.
The CG is located how far aft of datum? A-CG 92.44. B-CG 94.01. C-CG 119.8.
(Refer to figure 33 on page 8-16 and figure 34 on
page 8-17.)
What is the maximum amount of baggage that can be
carried when the airplane is loaded as follows?
Front seat occupants ... 387 lb
Rear seat occupants ... 293 lb
Fuel...35 gal A-45 pounds. B- 63 pounds C- 220 pounds.
(Refer to figure 3 3 on page 8-16 and figure 34 on
page 8-17.)
Determine if the airplane weight and balance is within
limits.
Front seat occupants .. .415 lb
Rear seat occupants .. .110 lb
Fuel, main tanks .. .44 gal
Fuel, aux. tanks ... 19 gal
Baggage ... 32 lb. A-19 pounds overweight, CG within limits. B- 19 pounds overweight, CG out of limits forward. C- Weight within limits, CG out of limits.
(Refer to figure 35 on page 8-20.)
What is the maximum amount of baggage that may be
loaded aboard the airplane for the CG to remain within
the moment envelope? A- 105 pounds. B-110 pounds. C-120 pounds.
(Refer to figure 35 on page 8-20.)
Calculate the moment of the airplane and determine
which category is applicable. A-79.2, utility category. B- 80.8, utility category. C- 81.2, normal category.
(Refer to figure 35 on page 8-20.)
What is the maximum amount of fuel that may be
aboard the airplane on takeoff if loaded as follows? A-24 gallons. B-32 gallons. C-40 gallons.
(Refer to figure 35 on page 8-20.)
Determine the moment with the following data: A-69.9 pound-inches. B- 74.9 pound-inches. C- 77.6 pound-inches.
(Refer to figure 35 on page 8-20.)
Determine the aircraft loaded moment and the aircraft
category. A- 78.2, normal category B- 79.2, normal category C- 80.4, utility category.
(Refer to figure 3 3 on page 8-16 and figure 34 on
page 8-17.)
Upon landing, the front passenger (180 pounds) departs
the airplane. A rear passenger (204 pounds) moves to
the front passenger position. What effect does this have
on the CG if the airplane weighed 2,690 pounds and
the MOM/100 was 2,260 just prior to the passenger
transfer? A-The CG moves forward approximately 3 inches. B- The weight changes, but the CG is not affected. C- The CG moves forward approximately 0.1 inch.
(Ref er to figure 3 3 on page 8-16 and figure 34 on
page 8-17.)
Which action can adjust the airplane's weight to
maximum gross weight and the CG within limits for
takeoff?
Front seat occupants .. .425 lb
Rear seat occupants ... 300 lb
Fuel, main tanks .. .44 gal A-Drain 12 gallons of fuel. B- Drain 9 gallons of fuel. C- Transfer 12 gallons of fuel from the main tanks to
the auxiliary tanks.
(Refer to figure 3 3 on page 8-16 and figure 34 on
page 8-17.)
What effect does a 35-gallon fuel burn (main tanks)
have on the weight and balance if the airplane weighed
2,890 pounds and the MOM/100 was 2,452 at takeoff? A-Weight is reduced by 210 pounds and the CG is aft
of limits. B- Weight is reduced by 210 pounds and the CG is
unaffected. C- Weight is reduced to 2,680 pounds and the CG
moves forward.
(Refer to figure 3 3 on page 8-16 and figure 34 on
page 8-17.)
With the airplane loaded as follows, what action can be
taken to balance the airplane?
Front seat occupants . .411 lb
Rear seat occupants .. .100 lb
Main wing tanks .. .44 gal A-Fill the auxiliary wing tanks. B- Add a 100-pound weight to the baggage
compartment. C- Transfer 10 gallons of fuel from the main tanks to
the auxiliary tanks.
(Refer to figure 62 on page 8-28.)
If 50 pounds of weight is located at point X and 100
pounds at point Z, how much weight must be located at
point Y to balance the plank? A-30 pounds. B- 50 pounds. C- 300 pounds.
(Refer to figure 61 on page 8-28.)
How should the 500-pound weight be shifted to
balance the plank on the fulcrum? A-1 inch to the left. B- 1 inch to the right. C-4.5 inches to the right.
(Refer to figure 8 on page 8-30.)
What is the effect of a temperature increase from 25
to 50°F on the density altitude if the pressure altitude
remains at 5,000 feet? A- 1,200-foot increase. B- 1,400-foot increase. C- 1,650-foot increase.
(Refer to figure 8 on page 8--30.)
Deterrnine the pressure altitude with an indicated
altitude of 1,380 feet MSL with an altimeter setting of
28.22?, at standard temperature. A- 3,010 feet MSL B- 2,991 feet MSL C- 2,913 feet MSL.
(Refer to figure 8 on page 8-30.)
Determine the density altitude for these conditions:
Altimeter setting ... 29 .25
Runway temperature ... +81 °F
Airport elevation ... 5,250 ft MSL A-4,600 feet MSL. B-5,877 feet MSL. C- 8,500 feet MSL.
(Refer to figure 8 on page 8-30.)
Determine the pressure altitude at an airport that is
3,563 feet MSL with an altimeter setting of 29.96. A-3,527 feet MSL. B- 3,556 feet MSL. C- 3,639 feet MSL.
(Refer to figure 8 on page 8-30.)
What is the effect of a temperature increase from 30
to 50°F on the density altitude if the pressure altitude
remains at 3,000 feet MSL? A- 900-foot increase. B- 1,100-foot decrease. C- 1,300-foot increase.
(Refer to figure 8 on page 8-30.)
Determine the pressure altitude at an airport that is
1,386 feet MSL with an altimeter setting of 29.97. A- 1,341 feet MSL. B- 1,451 feet MSL. C- 1,562 feet MSL.
(Refer to figure 8 on page 8-30.)
What is the effect of a temperature decrease and a
pressure altitude increase on the density altitude from
90°F and 1,250 feet pressure altitude to 55°F and 1,750
feet pressure altitude? A-1,700-foot increase. B-1,300-foot decrease. C- 1, 700-foot decrease.
(Refer to figure 21 on page 4-21.)
En route to First Flight Airport (area 5), your flight
passes over Hampton Roads Airport (area 2) at 1456
and then over Chesapeake Municipal at 1501. At what
time should your flight arrive at First Flight? A-1516. B-1521. C-1526.
(Refer to figure 22 on page 4-23.)
What is the estimated time en route from Mercer
County Regional Airport ( area 3) to Minot
International (area l)? The wind is from 330° at 25
knots and the true airspeed is 100 knots. Add 3-1/2
minutes for departure and climb-out. A-44 minutes. B- 48 minutes. C- 52 minutes.
(Refer to figure 23 on page 4-25.)
What is the estimated time en route from Sandpoint
Airport (area 1) to St. Maries Airport (area 4)? The
wind is from 215° at 25 knots and the true airspeed is
125 knots. A-38 minutes. B- 34 minutes C- 30 minutes.
(Ref er to figure 23 on page 4-25.)
Determine the estimated time en route for a flight
from Priest River Airport (area 1) to Shoshone County
Airport (area 3). The wind is from 030 at 12 knots
and the true airspeed is 95 knots. Add 2 minutes for
climb-out. A-27 minutes. B- 29 minutes. C- 31 minutes.
(Refer to figure 23 on page 4-25.)
What is the estimated time en route for a flight from St.
Maries Airport (area 4) to Priest River Airport (area I)?
The wind is from 300° at 14 knots and the true airspeed
is 90 knots. Add 3 minutes for climb-out. A-38 minutes. B- 43 minutes. C- 48 minutes.
(Refer to figure 24 on page 4-32.)
What is the estimated time en route for a flight from
Allendale County Airport (area 1) to Claxton-Evans
County Airport (area 2)? The wind is from 100° at 18
knots and the true airspeed is 115 knots. Add 2 minutes
for climb-out. A-33 minutes. B-27 minutes. C-30 minutes.
(Refer to figure 24 on page 4-32.)
What is the estimated time en route for a flight from
Claxton-Evans County Airport (area 2) to Hampton
Varnville Airport (area l)? The wind is from 290° at 18
knots and the true airspeed is 85 knots. Add 2 minutes
for climb-out. A-35 minutes. B- 39 minutes. C-44 minutes.
(Refer to figure 24 on page 4-32.)
While en route on Victor 185, a flight crosses the 248°
radial of Allendale VOR at 0953 and then crosses the
216° radial of Allendale VOR at 1000. What is the
estimated time of arrival at Savannah VORTAC? A-1023. B-1036. C-1028.
(Refer to figure 26 on page 4-27.)
What is the estimated time en route for a flight from
Denton Muni (area 1) to Addison (area 2)? The wind
is from 200° at 20 knots, the true airspeed is 110 knots,
and the magnetic variation is 7° east. A-13 minutes. B- 16 minutes. C- 19 minutes.
(Refer to figure 26 on page 4-27.)
Estimate the time en route from Addison (area 2)
to Redbird (area 3). The wind is from 300° at 15
knots, the true airspeed is 120 knots, and the magnetic
variation is 7° east. A-8 minutes. B- 11 minutes. C- 14 minutes.
If a true heading of 135° results in a ground track
of 130° and a true airspeed of 135 knots results in a
groundspeed of 140 knots, the wind would be from A-019° and 12 knots. B- 200° and 13 knots. C- 246° and 13 knots.
(Refer to figure 63 on page 8-38.)
In flying the rectangular course, when would the
aircraft be turned less than 90°? A-Corners 1 and 4. B- Corners l and 2. C- Corners 2 and 4.
(Refer to figure 67 on page 8-38.)
While practicing S-turns, a consistently smaller
half-circle is made on one side of the road than on the
other, and this turn is not completed before crossing the
road or reference line. This would most likely occur in
turn A-1-2-3 because the bank is decreased too rapidly
during the latter part of the turn. B-4-5-6 because the bank is increased too rapidly
during the early part of the turn. C-4-5-6 because the bank is increased too slowly
during the latter part of the turn.
How far will an aircraft travel in 2-1/2 minutes with a
groundspeed of 98 knots? A-2.45 NM. B-3.35 NM. C-4.08 NM.
On a cross-country flight, point A is crossed at
1500 hours and the plan is to reach point B at 1530
hours. Use the following information to determine
the indicated airspeed required to reach point B on
schedule.
Distance between A and B: 70 NM
Forecast wind: 310° at 15 kts
Pressure altitude: 8,000 ft
Ambient temperature: -10°C
True course: 270°
The required indicated airspeed would be
approximately A- 126 knots. B- 137 knots. C- 152 knots.
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