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► Given are the following information at take-off
STATION MASS (kg) / ARM (cm) / MOMENT (kgcm)
Basic Empty Condition ----- 12045 / +30 / +361350
Crew ------------------------ 145 / -160 / -23200
Freight 1 -------------------- 5455 / +200 / +1091000
Freight 2 -------------------- 410 / -40 / -16400
Fuel ------------------------- 6045 / -8 / -48360
Oil --------------------------- 124 / +40 / +4960
Given that the flight time is 2 hours and the estimated fuel flow will be 1050 litres per hour and the average oil consumption will be 2.25 litres per hour, the specific density of fuel is 0.79 and the specific density of oil is 0.96
Calculate the landing centre of gravity.
A) 61.26 cm aft of datum
B) 61.28 cm aft of datum
C) 61.27 cm aft of datum
D) 61.29 cm aft of datum
1- Find fuel and oil used after 2 hour flight:
Fuel Flow = 1050 l/h
Fuel used after 2h = 2100 L (1659 kg)
Oil consumption = 2.25 l/h
Oil used after 2h = 4.50 L (4.32 kg)
2- Now modify the values for fuel and oil given above:
Fuel ------------------------- 6045 / -8 / -48360
Oil --------------------------- 124 / +40 / +4960
Becomes
Fuel ------------------------- 4386 / -8 / -35088
Oil --------------------------- 119.68 / +40 / +4787.2
3- Find total mass and total moment
Total Mass = 22560.68
Total Moment = 1382449.2
CG = Total Moment / Total Mass
CG = 61.28 cm aft of datum
► Given the following information, calculate the loaded centre of gravity (CG).
STATION MASS (kg) / ARM (cm) / MOMENT (kgcm)
BEM -------------- 12045 / +30 / +361350
Crew ------------- 145 / -160 / -23200
Freight 1 --------- 5455 / +200 / +1091000
Freight 2 --------- 410 / -40 / -16400
Fuel --------------- 6045 / -8 / -48360
Oil ---------------- 124 / +40 / +4960
A) 56.35 cm aft datum
B) 56.53 cm aft datum
C) 60.16 cm aft datum
D) 53.35 cm aft datum
Total Mass = 12045+145+5455+410+6045+124 = 24224 kg
Total Moment = 361350 - 23200 + 1091000 - 16400 - 48360 + 4960 = 1369350 kgcm
CG = total moment / total mass
CG = 56.53 cm
► The loading for a flight is shown in the attached load sheet, with the following data applying to the airplane:
Maximum takeoff mass: 150.000kg
Maximum landing mass: 140.000kg
Forward CG limit: 10.5 m aft of datum
Aft CG limit: 13.0 m aft of datum
Estimated Trip Fuel: 55.000kg
A) Take-off CG is out of limits at 12.34m aft of datum
B) Landing CG is out of limits at 11.97m aft of datum
C) Landing CG is out of limits at 10.17m aft of datum
D) Take-off CG is out of limits at 10.17m aft of datum
1- Take the attached load sheet and find all the moments for Take off:
Basic Mass -------- 55.000 kg / +10 / 550.000
Fuel ---------------- 65.000 kg / +15 / 975.000
Crew --------------- 800 kg / -20 / -16.000
PAX ---------------- 8.200 kg / +10 / 82.000
FWD Freight ------- 8.000 kg / -5 / -40.000
AFT Freight -------- 11.000 kg / +20 / 220.000
Take off CG = Total Moment / Total Mass
Take off CG = 1771.000 / 148.000
Take off CG = 11.97
Take off CG is within limits!
2- Take the attached load sheet and find all the moments for landing:
Basic Mass -------- 55.000 kg / +10 / 550.000
Fuel ---------------- 10.000 kg / +15 / 150.000
Crew --------------- 800 kg / -20 / -16.000
PAX ---------------- 8.200 kg / +10 / 82.000
FWD Freight ------- 8.000 kg / -5 / -40.000
AFT Freight -------- 11.000 kg / +20 / 220.000
(Instead of adding/subtracting all the numbers again just subtract 55.000kg from the 148.000kg you calculated above and subtract (975.000-150.000) 825.000 from total moment calculated above)
Landing CG = Total Moment / Total Mass
Landing CG = 946.000 / 93.000
Landing CG = 10.17
Landing CG is out limits!
► Without the crew, the mass and longitudinal CG position of the aircraft are 6.000 kg and 4.70 m.
The mass of the pilot: 90kg
The mass of the copilot: 100kg
The mass of the flight engineer: 80kg
With the crew on board, the mass and longitudinal CG position of the aircraft are:
A) 6270 kg and 4.796m
B) 6270 kg and 5.012m
C 6270 kg and 4.61m
D) 6270 kg and 4.594m
Calculate the total Moments and total Mass:
BEM --------- 6.000 / +4.7 / 28200
Pilot --------- 90 / +2.045 / 184,05
Copilot ------ 100 / +2.045 / 204,5
Engineer ---- 80 / +2.690 / 215,2
(Moments for Pilot and Copilot (A) and engineer (B) can also be found from the table at the right side)
CG = T Moment / T Mass
CG = 28804.2 / 6270kg
CG = 4.594
► Without the man on the winch, the mass and the lateral CG position of the aircraft are 6000 kg and 0,04 m to the right. the mass of the man on the winch is 100 kg. With the man on the winch, the lateral CG position of the aircraft will be:
A) 0,062 m to the right
B) 0,016 m to the left
C) beyond the limits
D) 0,0633 to the right
Find the total moment and total mass:
Total Mass = 6000 + 100 = 6100kg
Total Moment = 240 (6000x0,04) + 140 (100x1,40) = 380
CG = 380 / 6100
CG = 0,062
STATION MASS (kg) / ARM (cm) / MOMENT (kgcm)
Basic Empty Condition ----- 12045 / +30 / +361350
Crew ------------------------ 145 / -160 / -23200
Freight 1 -------------------- 5455 / +200 / +1091000
Freight 2 -------------------- 410 / -40 / -16400
Fuel ------------------------- 6045 / -8 / -48360
Oil --------------------------- 124 / +40 / +4960
Given that the flight time is 2 hours and the estimated fuel flow will be 1050 litres per hour and the average oil consumption will be 2.25 litres per hour, the specific density of fuel is 0.79 and the specific density of oil is 0.96
Calculate the landing centre of gravity.
A) 61.26 cm aft of datum
B) 61.28 cm aft of datum
C) 61.27 cm aft of datum
D) 61.29 cm aft of datum
1- Find fuel and oil used after 2 hour flight:
Fuel Flow = 1050 l/h
Fuel used after 2h = 2100 L (1659 kg)
Oil consumption = 2.25 l/h
Oil used after 2h = 4.50 L (4.32 kg)
2- Now modify the values for fuel and oil given above:
Fuel ------------------------- 6045 / -8 / -48360
Oil --------------------------- 124 / +40 / +4960
Becomes
Fuel ------------------------- 4386 / -8 / -35088
Oil --------------------------- 119.68 / +40 / +4787.2
3- Find total mass and total moment
Total Mass = 22560.68
Total Moment = 1382449.2
CG = Total Moment / Total Mass
CG = 61.28 cm aft of datum
► Given the following information, calculate the loaded centre of gravity (CG).
STATION MASS (kg) / ARM (cm) / MOMENT (kgcm)
BEM -------------- 12045 / +30 / +361350
Crew ------------- 145 / -160 / -23200
Freight 1 --------- 5455 / +200 / +1091000
Freight 2 --------- 410 / -40 / -16400
Fuel --------------- 6045 / -8 / -48360
Oil ---------------- 124 / +40 / +4960
A) 56.35 cm aft datum
B) 56.53 cm aft datum
C) 60.16 cm aft datum
D) 53.35 cm aft datum
Total Mass = 12045+145+5455+410+6045+124 = 24224 kg
Total Moment = 361350 - 23200 + 1091000 - 16400 - 48360 + 4960 = 1369350 kgcm
CG = total moment / total mass
CG = 56.53 cm
► The loading for a flight is shown in the attached load sheet, with the following data applying to the airplane:
Maximum takeoff mass: 150.000kg
Maximum landing mass: 140.000kg
Forward CG limit: 10.5 m aft of datum
Aft CG limit: 13.0 m aft of datum
Estimated Trip Fuel: 55.000kg
A) Take-off CG is out of limits at 12.34m aft of datum
B) Landing CG is out of limits at 11.97m aft of datum
C) Landing CG is out of limits at 10.17m aft of datum
D) Take-off CG is out of limits at 10.17m aft of datum
1- Take the attached load sheet and find all the moments for Take off:
Basic Mass -------- 55.000 kg / +10 / 550.000
Fuel ---------------- 65.000 kg / +15 / 975.000
Crew --------------- 800 kg / -20 / -16.000
PAX ---------------- 8.200 kg / +10 / 82.000
FWD Freight ------- 8.000 kg / -5 / -40.000
AFT Freight -------- 11.000 kg / +20 / 220.000
Take off CG = Total Moment / Total Mass
Take off CG = 1771.000 / 148.000
Take off CG = 11.97
Take off CG is within limits!
2- Take the attached load sheet and find all the moments for landing:
Basic Mass -------- 55.000 kg / +10 / 550.000
Fuel ---------------- 10.000 kg / +15 / 150.000
Crew --------------- 800 kg / -20 / -16.000
PAX ---------------- 8.200 kg / +10 / 82.000
FWD Freight ------- 8.000 kg / -5 / -40.000
AFT Freight -------- 11.000 kg / +20 / 220.000
(Instead of adding/subtracting all the numbers again just subtract 55.000kg from the 148.000kg you calculated above and subtract (975.000-150.000) 825.000 from total moment calculated above)
Landing CG = Total Moment / Total Mass
Landing CG = 946.000 / 93.000
Landing CG = 10.17
Landing CG is out limits!
► Without the crew, the mass and longitudinal CG position of the aircraft are 6.000 kg and 4.70 m.
The mass of the pilot: 90kg
The mass of the copilot: 100kg
The mass of the flight engineer: 80kg
With the crew on board, the mass and longitudinal CG position of the aircraft are:
A) 6270 kg and 4.796m
B) 6270 kg and 5.012m
C 6270 kg and 4.61m
D) 6270 kg and 4.594m
Calculate the total Moments and total Mass:
BEM --------- 6.000 / +4.7 / 28200
Pilot --------- 90 / +2.045 / 184,05
Copilot ------ 100 / +2.045 / 204,5
Engineer ---- 80 / +2.690 / 215,2
(Moments for Pilot and Copilot (A) and engineer (B) can also be found from the table at the right side)
CG = T Moment / T Mass
CG = 28804.2 / 6270kg
CG = 4.594
► Without the man on the winch, the mass and the lateral CG position of the aircraft are 6000 kg and 0,04 m to the right. the mass of the man on the winch is 100 kg. With the man on the winch, the lateral CG position of the aircraft will be:
A) 0,062 m to the right
B) 0,016 m to the left
C) beyond the limits
D) 0,0633 to the right
Find the total moment and total mass:
Total Mass = 6000 + 100 = 6100kg
Total Moment = 240 (6000x0,04) + 140 (100x1,40) = 380
CG = 380 / 6100
CG = 0,062
