Term
(Refer to Figure 30.) Using a maximum demonstrated crosswind component equal to 0.2 V(SO), what is a pilot able to determine?
V(SO) 60 kts
Landing Rwy 12
Wind 150° at 20 kts |
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Definition
| Crosswind component is within safe limits. |
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Term
(Refer to Figure 26.) Determine the ground roll required for takeoff.
Temperature 25°C
Pressure altitude 2,000 ft
Weight 2,200 lb
Headwind 15 kts |
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Definition
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Term
| When an aircraft's forward CG limit is exceeded, it will affect the flight characteristics of the aircraft by producing |
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Definition
| higher stalling speeds and more longitudinal stability. |
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Term
| The most favorable combination of conditions for rotorcraft performance is |
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Definition
| low density altitude, low gross weight, and moderate to strong wind |
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Term
| (Refer to Figure 33.) How should the 200-pound weight be shifted to balance the plank on the fulcrum? |
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Definition
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Term
| Which statement is true regarding takeoff performance with high density altitude conditions? |
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Definition
| The acceleration rate is slower because the engine and propeller efficiency is reduced. |
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Term
| (Refer to Figure 24.) What is the effect of a temperature increase from 30 to 50 degrees F on the density altitude if the pressure altitude remains at 3,000 feet MSL? |
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Definition
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Term
| (Refer to Figure 39.) What is the maximum altitude for a balloon if the gross weight is 1,060 pounds and standard temperature exists at all altitudes? |
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Definition
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Term
What is the location of the CG if 60 pounds are removed from Station 70?
Aircraft weight: 8,420 lb
CG location station: 85 |
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Definition
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Term
| What can a pilot expect when landing at an airport located in the mountains? |
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Definition
| Higher true airspeed and longer landing distance. |
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Term
| (Refer to Figure 27.) What indicated airspeed at 3,000 feet would result in the greatest increase in altitude for a given distance? |
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Definition
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Term
What is the location of the CG if 90 pounds are removed from Station 140?
Aircraft weight 6,230 lb
CG location Station 79 |
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Definition
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Term
Based on this information, the CG would be located how far aft of datum?
Weight A 120 lb at 15" aft of datum
Weight B 200 lb at 117" aft of datum
Weight C 75 lb at 195" aft of datum |
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Definition
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Term
(Refer to Figure 30.) Using a maximum demonstrated crosswind component equal to 0.2 V(SO), what is a pilot able to determine?
V(SO) 70 kts
Landing Rwy 35
Wind 300° at 20 kts |
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Definition
| Maximum demonstrated crosswind component is exceeded. |
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Term
| If the CG of an aircraft is moved from the aft limit to beyond the forward limit, how will it affect the cruising and stalling speed? |
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Definition
| Decrease the cruising speed and increase the stalling speed. |
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Term
| How does increased weight affect the takeoff distance of an airplane? |
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Definition
| The airplane will accelerate more slowly with the same power output, and a higher airspeed is required to generate necessary lift for takeoff. |
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Term
(Refer to Figure 26.) Determine the takeoff distance required to clear a 50-foot obstacle.
Temperature 3°C
Pressure altitude 6,000 ft
Weight 3,000 lb
Headwind 15 kts |
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Definition
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Term
Based on this information, the CG would be located how far aft of datum?
Weight D 160 lb at 45" aft of datum
Weight E 170 lb at 145" aft of datum
Weight F 105 lb at 185" aft of datum |
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Definition
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Term
| (Refer to Figure 25.) What would be the indicated stall speed during a 40° banked turn with the gear down and flaps set at 45°? |
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Definition
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Term
| An aircraft is loaded with the CG aft of the aft limit. What effect will this have on controllability? |
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Definition
| Stall and spin recovery may be difficult or impossible. |
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Term
| If the nosewheel of an airplane moves aft during gear retraction, how would this aft movement affect the CG location of that airplane? It would |
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Definition
| cause the CG location to move aft. |
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Term
| As the CG moves aft, an aircraft becomes |
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Definition
| less stable and less controllable. |
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Term
| The center of gravity of an aircraft is computed along the |
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Definition
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Term
| What is the significance of the blue radial line on the airspeed indicator of a light multiengine airplane and when is it to be used? it indicates the |
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Definition
| speed which will provide the maximum altitude gain in a given time when one engine is inoperative and should be used for climb and final approach during engine-out operations. |
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Term
| If the CG is located aft of allowable limits, the pilot may find it impossible to |
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Definition
| fly in the upper allowable airspeed range due to insufficient forward cyclic control. |
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Term
(Refer to Figure 30.) Determine the approximate crosswind component.
Landing Rwy 22
Wind 260° at 23 kts |
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Definition
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Term
| Aft center of gravity in a helicopter limits the |
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Definition
| upper allowable airspeed range. |
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Term
| The V(NE) of a helicopter is limited by |
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Definition
| lateral controllability or retreating blade stall. |
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Term
(Refer to Figure 36.) Determine the condition of the airplane:
Pilot and copilot 400 lb
Passengers - aft position 240 lb
Baggage 20 lb
Fuel 75 gal |
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Definition
| 180 pounds under allowable gross weight; CG is located within limits. |
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Term
(Refer to Figure 28.) Determine the approximate total distance required to clear a 50-foot obstacle.
Temperature 20°C
Pressure altitude 1,000 ft
Surface sod
Weight 5,300 lb
Wind 15 kts headwind |
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Definition
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Term
| In a twin-engine airplane, the single-engine service ceiling is the maximum density altitude at which V(YSE) will produce |
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Definition
| 50 ft per minute rate of climb. |
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Term
| If the atmospheric pressure and temperature remain the same, how would an increase in humidity affect takeoff performance? |
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Definition
| Longer takeoff distance; the air is less dense. |
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Term
| (Refer to Figure 27.) To maintain the best rate of climb, the indicated speed should be |
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Definition
| reduced approximately .8 knots per 1,000 feet of altitude. |
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Term
(Refer to Figure 28.) Determine the approximate total distance required to clear a 50-foot obstacle.
Temperature 35°C
Pressure altitude 3,000 ft
Surface sod
Weight 5,100 lb
Wind 20 kts headwind |
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Definition
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Term
| (Refer to figure 39) What is the maximum altitude for a balloon if the gross weight is 960 pounds and the ambient temperature is 76F? |
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Definition
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Term
| To maintain level flight in an airplane which is loaded with the CG at the forward limit, an additional download must be imposed on the horizontal stabilizer. This in turn produces |
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Definition
| an additional load which the wing must support. |
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Term
| The stalling speed of an aircraft will be highest when the aircraft is loaded with a |
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Definition
| high gross weight and forward CG. |
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Term
(Refer to Figure 36.) Determine the condition of the airplane:
Pilot and copilot 316 lb
Passengers (rear)
Fwd 130 lb
Aft 147 lb
Baggage 50 lb
Fuel 75 gal |
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Definition
| 197 pounds under allowable gross weight; CG 83.6 inches aft of datum. |
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Term
What is the maximum weight that could be added at Station 150.0 without exceeding the aft CG limit?
Aircraft weight 5,000 lb
CG location Station 80.0
Aft CG limit Station 80.5 |
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Definition
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Term
| (Refer to Figure 25.) What would be the indicated stall speed in a 30° banked turn with the gear down and flaps set at 15°? |
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Definition
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Term
(Refer to Figure 26.) Determine the takeoff distance required to clear a 50-foot obstacle.
Temperature 23°C
Pressure altitude 3,000 ft
Weight 2,400 lb
Headwind 15 kts |
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Definition
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Term
(Refer to Figure 30.) Determine the approximate crosswind component.
Landing Rwy 03
Wind 060° at 35 kts |
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Definition
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Term
| Which is true regarding the operation of a multiengine airplane with one engine inoperative? |
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Definition
| Banking toward the inoperative engine increases V(MC). |
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Term
| An aircraft is loaded with the CG at the aft limit. What are the performance characteristics compared with the CG at the forward limit? |
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Definition
| The aft CG provides the lowest stalling speed, the highest cruising speed, and least stability. |
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Term
| For an airplane with reciprocating, non-turbocharged engines, V(MC) |
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Definition
|
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Term
| (Refer to Figure 25.) What would be the indicated stall speed in a 60° banked turn with the gear and flaps up? |
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Definition
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Term
(Refer to Figure 24.) Determine the density altitude.
Airport elevation 3,795 ft
OAT 24°C
Altimeter setting 29.70" Hg |
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Definition
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Term
| (Refer to Figure 24.) Determine the pressure altitude at an airport that is 3,563 feet MSL with an altimeter setting of 29.96. |
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Definition
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Term
(Refer to Figure 29.) What is the approximate glide distance?
Height above terrain 5,500 ft
Tailwind 10 kts |
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Definition
|
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Term
| The center of gravity of an aircraft can be determined by |
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Definition
| dividing total moment by total weight. |
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