Commercial Ch 5

Front 1

The performance tables of an aircraft for takeoff and climb are based on

Back 1

pressure/density altitude

Front 2

To determine pressure altitude prior to takeoff, the altimeter should be set to

Back 2

29.92" HG and the altimeter indication noted

Front 3

At higher elevation airports the pilots should know that indicated airspeed

Back 3

will be unchanged, but groundspeed will be faster

Front 4

GIVEN:

pressure altitude..........12,000 ft
True air temperature.........+50'F

From the conditions given, the approximate density altitude is

Back 4

14,130 feet

Front 5

GIVEN:

pressure altitude..........5,000 ft
True air temperature.........+30'C

From the conditions given, the approximate density altitude is

Back 5

7,800 feet

Front 6

GIVEN:

pressure altitude..........6,000 ft
True air temperature.........+30'F

From the conditions given, the approximate density altitude is

Back 6

5,500 feet

Front 7

GIVEN:

pressure altitude..........7,000 ft
True air temperature.........+15'C

From the conditions given, the approximate density altitude is

Back 7

8,500 feet

Front 8

(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?

Back 8

1,500 feet

Front 9

(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?

Back 9

1,350 feet

Front 10

(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?

Back 10

800 feet

Front 11

(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?

Back 11

300 pounds

Front 12

What effect does an uphill runway slope have on takeoff performance?

Back 12

increases takeoff distance

Front 13

(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?

Back 13

8.4 minutes

Front 14

(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?

Back 14

43 pounds

Front 15

(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?

Back 15

46 pounds

Front 16

(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?

Back 16

5.5 minutes

Front 17

(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?

Back 17

8.5 miles

Front 18

(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?

Back 18

5 gallons, 9 minutes, 13 NM

Front 19

(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

Back 19

58 pounds

Front 20

(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

Back 20

35 pounds

Front 21

(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

Back 21

24 pounds

Front 22

(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

Back 22

40 pounds

Front 23

(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?

Back 23

384 ft/min

Front 24

(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?

Back 24

702 ft/min

Front 25

(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

Back 25

810 miles

Front 26

(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)

Back 26

7.7 hours

Front 27

(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?

Back 27

105 MPH TAS, 6.2 GPH

Front 28

(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)

Back 28

4 hours 1 minute

Front 29

(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)

Back 29

2 hours 27 minutes

Front 30

(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)

Back 30

5 hours 59 minutes

Front 31

(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?

Back 31

6 hours 39 minutes

Front 32

(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?

Back 32

4 hours 30 minutes

Front 33

(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?

Back 33

5 hours 12 minutes

Front 34

which maximum range factor decreases as weight decreases

Back 34

airspeed

Front 35

(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

Back 35

3 hours 22 minutes

Front 36

(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

Back 36

4 hours 30 minutes

Front 37

(refer to figure 8 on page 154) approximately how much fuel would be consumed when climbing at 75 percent power for 7 minutes?

Back 37

2.12 gallons

Front 38

(refer to figure 8 on page 154) Determine the amount of fuel consumed during takeoff and climb at 70 percent power for 10 minutes?

Back 38

2.88 gallons

Front 39

(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

Back 39

2 hours 34 minutes

Front 40

(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

Back 40

260 ' at 20 knots

Front 41

(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

Back 41

19 knots

Front 42

(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

Back 42

7 knots

Front 43

(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?

Back 43

17 knots

Front 44

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

Back 44

B.636 feet

Front 45

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?

Back 45

B.1,250 feet

Front 46

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?

Back 46

A.689

Front 47

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?

Back 47

A,742 feet

Front 48

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

Back 48

A. the ususable fuel, full operating fluids, and full oil.

Front 49

49. The CG of an aircraft can be determined by which of the following methods?

Back 49

C. Dividing total moments by total weight

Front 50

50. The CG of an aircraft may be determined by

Back 50

B. Dividing total moments by total weight

Front 51

51. If all index units are positive when computing weight and balance, the location of the datum would be at the

Back 51

B. nose, or out in front of the airplane

Front 52

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

Back 52

B.116.8 inches

Front 53

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?

Back 53

B.96.89 inches

Front 54

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?

Back 54

A. Yes, the weight and CG is within linits.

Front 55

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

Back 55

A. Within the CG envelope

Front 56

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?

Back 56

A, yes, the CG will remain within limits

Front 57

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

Back 57

+16.43.

Front 58

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

Back 58

100.2 inches

Front 59

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

Back 59

118.24 inches

Front 60

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

Back 60

67.79

Front 61

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

Back 61

68.83

Front 62

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?

Back 62

96.13 inches aft of datum

Front 63

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?

Back 63

52.14 pounds