3. 30 Flashcards
(30 cards)
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.
Given an aeroplane with:
Maximum Structural Landing Mass: 68000 kg
Maximum Zero Fuel Mass: 70200 kg
Maximum Structural Take-off Mass: 78200 kg
Dry Operating Mass : 48000 kg
Scheduled trip fuel is 7000 kg and the reserve fuel is 2800 kg,
Assuming performance limitations are not restricting, the maximum permitted take-off mass and maximum traffic load are respectively:
75000 kg and 17200 kg
The datum is a reference from which all moment (balance) arms are measured. Its precise position is given in the control and loading manual and it is located
at a convenient point which may not physically be on the aircraft.
Moment (balance) arms are measured from a specific point to the body station at which the mass is located. That point is known as
the datum.
The centre of gravity of an aircraft is that point through which the total mass of the aircraft is said to act. The weight acts in a direction
parallel to the gravity vector.
When an aircraft is stationary on the ground, its total weight will act vertically
through its centre of gravity.
The weight of an aircraft, which is in level non accelerated flight, is said to act
vertically through the centre of gravity.
An aeroplane is weighed and the following recordings are made:
nose wheel assembly scale 5330 kg
left main wheel assembly scale 12370 kg
right main wheel assembly scale 12480 kg
If the ‘operational items’ amount to a mass of 1780 kg with a crew mass of 545 kg, the empty mass, as entered in the weight schedule, is
30180 kg
If individual masses are used, the mass of an aircraft must be determined prior to initial entry into service and thereafter
at intervals of 4 years if no modifications have taken place.
The empty mass of an aeroplane is recorded in
the weighing schedule and is amended to take account of changes due to modifications of the aeroplane.
