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63 Cards in this Set
- Front
- Back
The performance tables of an aircraft for takeoff and climb are based on
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pressure/density altitude
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To determine pressure altitude prior to takeoff, the altimeter should be set to
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29.92" HG and the altimeter indication noted
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At higher elevation airports the pilots should know that indicated airspeed
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will be unchanged, but groundspeed will be faster
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GIVEN:
pressure altitude..........12,000 ft True air temperature.........+50'F From the conditions given, the approximate density altitude is |
14,130 feet
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GIVEN:
pressure altitude..........5,000 ft True air temperature.........+30'C From the conditions given, the approximate density altitude is |
7,800 feet
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GIVEN:
pressure altitude..........6,000 ft True air temperature.........+30'F From the conditions given, the approximate density altitude is |
5,500 feet
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GIVEN:
pressure altitude..........7,000 ft True air temperature.........+15'C From the conditions given, the approximate density altitude is |
8,500 feet
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(Refer to figure 32 on page 135)
GIVEN: Temperature....................30'F pressure altitude..........6,000 ft weight........................3,000lb Headwind.....................20 kts what is the total takeoff distance over a 50-foot obstacle? |
1,500 feet
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(Refer to figure 32 on page 135)
GIVEN: Temperature....................100'F pressure altitude..........4,000 ft weight........................3,200lb wind............................calm what is the ground roll required for takeoff over a 50-foot obstacle? |
1,350 feet
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(Refer to figure 32 on page 135)
GIVEN: Temperature....................50'F pressure altitude..........2,000 ft weight........................2,700lb wind............................calm what is the total takeoff distance over a 50-foot obstacle? |
800 feet
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(Refer to figure 32 on page 135)
GIVEN: Temperature....................75'F pressure altitude..........6,000 ft weight........................2,900lb Headwind.....................20 kts To safely take off a 50-foot obstacle in 1,000 feet, what weight reduction is necessary? |
300 pounds
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What effect does an uphill runway slope have on takeoff performance?
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increases takeoff distance
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(Refer to figure 13 on page 137)
GIVEN: Aircraft weight..............4,000lb Airport pressure altitude.............2,000 ft temperature at 2,000 ft ............32'C Using maximum rate of climb under the given conditions, how much time would be required to climb to a pressure altitude of 8,000 feet? |
8.4 minutes
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(Refer to figure 13 below)
GIVEN: Aircraft weight..............3,400lb Airport pressure altitude.............6,000 ft temperature at 6,000 ft ............10'C Using maximum rate of climb under the given conditions, how much fuel would be used from engine start to a pressure altitude of 16,000 feet? |
43 pounds
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(Refer to figure 14 on page 138)
GIVEN: Aircraft weight..............3,700lb Airport pressure altitude.............4,000 ft temperature at 4,000 ft ............21'C Using q normal climb under the given conditions, how much fuel would be used from engine start to a pressure altitude of 12,000 feet? |
46 pounds
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(Refer to figure 14 on page 138)
GIVEN: Aircraft weight..............3,400lb Airport pressure altitude.............4,000 ft temperature at 4,000 ft ............14'C Using a normal climb under the given conditions, how much time would be required to climb to a pressure altitude of 8,000 feet? |
5.5 minutes
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(Refer to figure 15 on page 140)
GIVEN: airport pressure altitude............4,000 ft airport temperature.............12'C Cruise pressure altitude............9,000 ft Cruise temperature................-4'C what will be the distance required to climb to cruise the altitude under the given conditions? |
8.5 miles
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(Refer to figure 15 on page 140)
GIVEN: airport pressure altitude............2,000 ft airport temperature.............20'C Cruise pressure altitude............10,000 ft Cruise temperature................0'C what will be the fuel, time, and distance required to climb to cruise the altitude under the given conditions? |
5 gallons, 9 minutes, 13 NM
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(refer to figure 9 on page 142) Using normal climb, how much fuel would be used from engine start to 12,000 feet pressure altitude?
aircraft weight..............3,800lb airport pressure altitude...............4,000 ft temperature..................26'C |
58 pounds
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(refer to figure 9 on page 142) Using normal climb, how much fuel would be used from engine start to 10,000 feet pressure altitude?
aircraft weight..............3,500lb airport pressure altitude...............4,000 ft temperature..................21'C |
35 pounds
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(refer to figure 10 on page 145) Using a maximum rate of climb, how much fuel would be used from engine start to 6,000 feet pressure altitude?
aircraft weight..............3,200lb airport pressure altitude...............2,000 ft temperature..................27'C |
24 pounds
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(refer to figure 10 on page 145) Using a maximum rate of climb, how much fuel would be used from engine start to 10,000 feet pressure altitude?
aircraft weight..............3,800lb airport pressure altitude...............4,000 ft temperature..................30'C |
40 pounds
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(Refer to figure 33 on page 146)
GIVEN: weight...................3,700 lb pressure altitude...............22,000 ft temperature..................-10'C what is the maximum rate of climb under the given conditions? |
384 ft/min
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(Refer to figure 33 on page 146)
GIVEN: weight...................4,000 lb pressure altitude...............5,000 ft temperature..................30'C what is the maximum rate of climb under the given conditions? |
702 ft/min
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(refer to figure 11 on page 148) If the cruise altitude is 7,500 feet, using 64 percent power at 2,500 RPM, what would be the range with 48 gallons of useable fuel
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810 miles
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(Refer to figure 11 on page 148) What would be the endurance at an altitude of 7,500 feet, using 52 percent power?
NOTE: (wit 48 gallons of fuel-no reserve) |
7.7 hours
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(Refer to figure 11 on page 148) What would be the approximate true airspeed and fuel consumption per hour at an altitude of 7,500 feet, using 52 percent power?
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105 MPH TAS, 6.2 GPH
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(Refer to figure 12o n page 150)
GIVEN: pressure altitude............18,000 ft temperature.............-21'C power.................2,400 RPM-28" MP Recommended lean mixture useable fuel.......................425lb what is the approximate flight time available under the given conditions? (allow for VFR day fuel reserve) |
4 hours 1 minute
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(Refer to figure 12o n page 150)
GIVEN: pressure altitude............18,000 ft temperature.............-41'C power.................2,500 RPM-26" MP Recommended lean mixture useable fuel.......................318lb what is the approximate flight time available under the given conditions? (allow for VFR day fuel reserve) |
2 hours 27 minutes
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(Refer to figure 12o n page 150)
GIVEN: pressure altitude............18,000 ft temperature.............-1'C power.................2,200 RPM-20" MP Best economy useable fuel.......................344lb what is the approximate flight time available under the given conditions? (allow for VFR day fuel reserve) |
5 hours 59 minutes
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(Refer to figure 34 on page 152)
GIVEN: pressure altitude............6,000 ft temperature.............+3'C power.................2,200 RPM-22" MP useable fuel available.......................465lb what is the maximum available flight under the conditions stated? |
6 hours 39 minutes
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(Refer to figure 34 on page 152)
GIVEN: pressure altitude............6,000 ft temperature.............-17'C power.................2,300 RPM-23" MP useable fuel available.......................370lb what is the maximum available flight under the conditions stated? |
4 hours 30 minutes
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(Refer to figure 34 on page 152)
GIVEN: pressure altitude............6,000 ft temperature.............+13'C power.................2,500 RPM-23" MP useable fuel available.......................460lb what is the maximum available flight under the conditions stated? |
5 hours 12 minutes
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which maximum range factor decreases as weight decreases
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airspeed
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(refer to figure 8 on page 154)
GIVEN: fuel quantity.............47 gal Power-cruise (lean).............55 percent approximately how much flight time would be available with a night VFR fuel reserve remaining |
3 hours 22 minutes
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(refer to figure 8 on page 154)
GIVEN: fuel quantity.............65 gal Power-cruise (lean).............55 percent approximately how much flight time would be available with a night VFR fuel reserve remaining |
4 hours 30 minutes
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(refer to figure 8 on page 154) approximately how much fuel would be consumed when climbing at 75 percent power for 7 minutes?
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2.12 gallons
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(refer to figure 8 on page 154) Determine the amount of fuel consumed during takeoff and climb at 70 percent power for 10 minutes?
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2.88 gallons
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(refer to figure 8 on page 154) with 38 gallons of fuel aboard at cruise power (55 percent), how much flight time is available with night VFR fuel reserves still remaining
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2 hours 34 minutes
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(refer to figure 31 on page 156) Rwy 30 is being used for landing. Which surface wind would exceed the airplane's crosswind capability of 0.2 Vso+ if Vso is 60 knots
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260 ' at 20 knots
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(refer to figure 31 on page 156) the surface wind is 180' at 25 knots. what is the crosswind component for a Rwy 13 landing
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19 knots
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(refer to figure 31 on page 156) What is the headwind component for a Rwy 13 takeoff if the surface wind is 190' at 15 knots
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7 knots
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(refer to figure 31 on page 156) If the tower-reported surface wind is 010' at 18 knots, what is the crosswind component for a Rwy 08 landing?
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17 knots
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44.(Refer to figure 35 on page 158)
GIVEN: Temerperature…………..50’F Pressure altitude…………….Sea level Weight………………………..3,000 lb Headwind……………………….10kts Determine the approximate ground roll |
B.636 feet
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45.(Refer to figure 35 on page 158)
GIVEN: Temerperature…………..80’F Pressure altitude…………….4,000 ft Weight………………………..2,800 lb Headwind……………………….24kts What is the total landing distance over a 50-foot obstacle? |
B.1,250 feet
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46.(Refer to figure 35 on page 158)
GIVEN: Temerperature…………..70’F Pressure altitude…………….Sea level Weight………………………..3,400 lb Headwind……………………….16kts Determine the approximate ground roll? |
A.689
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47.(Refer to figure 35 on page 158)
GIVEN: Temerperature…………..85’F Pressure altitude…………….6,000 ft Weight………………………..2,800 lb Headwind……………………….14kts Determine the approximate ground roll? |
A,742 feet
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48. When computing weight and balance, the basic empty weight includes the weight of the airframe, engine(s) and all installed optional equipment. Basic empty weight also includes
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A. the ususable fuel, full operating fluids, and full oil.
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49. The CG of an aircraft can be determined by which of the following methods?
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C. Dividing total moments by total weight
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50. The CG of an aircraft may be determined by
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B. Dividing total moments by total weight
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51. If all index units are positive when computing weight and balance, the location of the datum would be at the
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B. nose, or out in front of the airplane
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52, GIVEN:
Weight A—155 pounds at 45 inches aft of datum Weight B—165 pounds at 145 inches aft of datum Weight C—95 pounds at 185 inches aft of datum Based on this information, where would the CG be located aft of datum |
B.116.8 inches
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53, GIVEN:
Weight A—140 pounds at 17 inches aft of datum Weight B—120 pounds at 110 inches aft of datum Weight C—85 pounds at 210 inches aft of datum Based on this information, the CG would be located how far aft of datum? |
B.96.89 inches
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54.(Refer to figure 38 on page 162)
GIVEN: Empty weight (oil is included)…………………….1,271 lb Empty weight moment (in-1b/1,000)…………..102.04 Pilot and copilot……………………………….............400 lb Rear seat passenger……………………………………..140lb Cargo……………………………………………………………..100lb Fuel………………………………………………………………….37 ga; Is the airplane loaded within limits? |
A. Yes, the weight and CG is within linits.
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55.(Refer to figure 38 on page 162)
GIVEN: Empty weight (oil is included)…………………….1,271 lb Empty weight moment (in-1b/1,000)…………..102.04 Pilot and copilot……………………………….............260lb Rear seat passenger……………………………………..120lb Cargo……………………………………………………………..60lb Fuel………………………………………………………………….37 ga; Under these conditions, the CG is determined to be located |
A. Within the CG envelope
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56.(Refer to figure 38 on page 162)
GIVEN: Empty weight (oil is included)…………………….1,271 lb Empty weight moment (in-1b/1,000)…………..102.04 Pilot and copilot……………………………….............360 lb Cargo……………………………………………………………..100lb Fuel………………………………………………………………….37 gal Will the CG remain within limits after 30 gallons of fuel has been used in flight? |
A, yes, the CG will remain within limits
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GIVEN:
Empty weight 957 29.07 ? pilot(fwd seat) 140 -45.30 ? passenger(aft seat) 170 +1.60 ? ballast 15 -45.30 ? TOTALS the CG is located at station |
+16.43.
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GIVEN:
Weight A—135 pounds at 15 inches aft of datum Weight B—205 pounds at 117 inches aft of datum Weight C—85 pounds at 195 inches aft of datum Based on this information, the CG would be located how far aft of datum |
100.2 inches
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GIVEN:
Weight A—175 pounds at 135 inches aft of datum Weight B—135 pounds at 115 inches aft of datum Weight C—75 pounds at 85 inches aft of datum The CG for the combined weights would be located how far aft of datum |
118.24 inches
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GIVEN:
Total weight.......................4,1371l CG location....................Station 67.8 Fuel consumption..........................13.7 GPH Fuel CG..............................station 68.0 after 1 hour 30 minutes of flight time, the CG would be located at station |
67.79
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GIVEN:
Total weight.......................3,0371b CG location....................Station 68.8 Fuel consumption..........................112.7 GPH Fuel CG..............................station 68.0 after 1 hour 45 minutes of flight time, the CG would be located at station |
68.83
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An airplane is loaded to a gross weight of 4,800 pounds, with three pieces of luggage in the rear baggage compartment. The CG is located 98 inches aft of datum, which is 1 inch aft of limits. If luggage which weighs 90 pounds is moved from the rear baggage compartment (145 inches aft of datum) to the front compartment (45 inches aft of datum), what is the new CG?
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96.13 inches aft of datum
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An aircraft is loaded with a ramp weight of 3,650 pounds and having a CG of 94.0, approximately how much baggage would have to be moved from the rear baggage area at station 189 to the forward baggage area at station 40 in order to move the CG to 92.0?
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52.14 pounds
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