3. 30 Flashcards
At reference or see Loading Manual MEP1 Figure 3.4.
With respect to multi-engine piston powered aeroplane, determine the ramp mass (lbs) in the following conditions:
Basic empty mass: 3 210 lbs, Basic arm: 88.5 Inches, One pilot: 160 lbs, Front seat passenger : 200 lbs, Centre seat passengers: 290 lbs, One passenger rear seat: 110 lbs, Baggage in zone 1: 100 lbs, Baggage in zone 4: 50 lbs, Block fuel: 100 US Gal. Trip fuel: 55 US Gal. Fuel for start up and taxi (included in block fuel): 3 US Gal. Fuel density: 6 lbs/US Gal.
4 720
At reference or see Loading Manual MEP1 Figure 3.4.
With respect to multi-engine piston powered aeroplane, determine the block fuel moment (lbs.In.) in the following conditions:
Basic empty mass: 3 210 lbs. One pilot: 160 lbs. Front seat passenger : 200 lbs. Centre seat passengers: 290 lbs. (total) One passenger rear seat: 110 lbs. Baggage in zone 1: 100 lbs.
Baggage in zone 4: 50 lbs. Block fuel: 100 US Gal. Trip fuel: 55 US Gal. Fuel for start up and taxi (included in block fuel): 3 US Gal. Fuel density: 6 lbs./US Gal. Total moment at take-off: 432226 lbs.In
56 160
See Loading Manual MEP1 Figure 3.4.
With respect to a multi-engine piston powered aeroplane, determine the total moment (lbs.In) at landing in the following conditions:
Basic empty mass: 3 210 lbs. One pilot: 160 lbs. Front seat passenger : 200 lbs. Centre seat passengers: 290 lbs. (total) One passenger rear seat: 110 lbs. Baggage in zone 1: 100 lbs.
Baggage in zone 4: 50 lbs. Block fuel: 100 US Gal. Trip fuel: 55 US Gal. Fuel for start up and taxi (included in block fuel): 3 US Gal. Fuel density: 6 lbs./US Gal. Total moment at take-off: 432226 lbs.In
401 338
At reference or see Loading Manual MEP1 Figure 3.4.
With respect to a multi-engine piston powered aeroplane, determine the CG location at take off in the following conditions:
Basic empty mass: 3 210 lbs. One pilot: 160 lbs. Front seat passenger : 200 lbs. Centre seat passengers: 290 lbs. (total) One passenger rear seat: 110 lbs. Baggage in zone 1: 100 lbs.
Baggage in zone 4: 50 lbs. Zero Fuel Mass: 4120 lbs. Moment at Zero Fuel Mass: 377751 lbs.In
Block fuel: 100 US Gal. Trip fuel: 55 US Gal. Fuel for start up and taxi (included in block fuel): 3 US Gal. Fuel density: 6 lbs./US Gal.
91.92 inches aft of datum
The crew of a transport aeroplane prepares a flight using the following data:
- Dry operating mass: 90 000 kg
- Block fuel: 30 000 kg
- Taxi fuel: 800 kg
- Maximum take-off mass: 145 000 kg
The traffic load available for this flight is:
25 800 kg
At reference or see Loading Manual SEP1 Figure 2.4.
With respect to a single-engine piston powered aeroplane, determine the zero fuel moment (lbs.In./100) in the following conditions:
Basic Empty Mass: 2415 lbs.
Arm at Basic Empty Mass: 77,9 In.
Cargo Zone A: 350 lbs.
Baggage Zone B: 35 lbs.
Pilot and front seat passenger : 300 lbs (total)
2548,8
Determine the Zero Fuel Mass for the following single engine aeroplane.
Given : Basic Empty Mass: 1799 lbs Optional Equipment: 35 lbs
Pilot Front seat passenger : 300 lbs
Cargo Mass : 350 lbs
Ramp Fuel = Block Fuel : 60 Gal.
Trip Fuel : 35 Gal.
Fuel density : 6 lbs/Gal.
2449 lbs
Determine the Landing Mass for the following single engine aeroplane. Given: Standard Empty Mass :1764 lbs Optional Equipment : 35 lbs Pilot Front seat passenger : 300 lbs Cargo Mass : 350 lbs Ramp Fuel = Block Fuel : 60 Gal. Trip Fuel : 35 Gal. Taxi Fuel 1.7 Gal. Fuel density: 6 lbs/Gal Determine the expected landing mass.
2589 lbs
To calculate the allowable take-off mass, the factors to be taken into account include:
the sum of the Maximum Landing Mass and the trip fuel.
In cruise flight, a centre of gravity moving aft will:
decrease longitudinal static stability
Length of the mean aerodynamic chord = 1 m Moment arm of the forward cargo: -0,50 m Moment arm of the aft cargo: + 2,50 m The aircraft mass is 2 200 kg and its centre of gravity is at 25% MAC To move the centre of gravity to 40%, which mass has to be transferred from the forward to the aft cargo hold?
110 kg
The maximum zero fuel mass is a mass limitation for the:
strength of the wing root structure
Which of the following statements is correct?
A tail heavy aeroplane is less stable and stalls at a lower speed than a nose heavy aeroplane
Which of the following statements is correct?
A tail heavy aeroplane is less stable and stalls at a lower speed than a nose heavy aeroplane
Which of the following statements is correct?
The Maximum Landing Mass of an aeroplane is restricted by structural limitations, performance limitations and the strength of the runway.