Mass & Balance | PPL(A) Performance & Planning - EASA & UK CAA
Mass and Balance details of aircraft
Section titled "Mass and Balance details of aircraft"What is the reference point for the center of gravity (CG) limits?
How may the position of the Center of Gravity corresponding to the Basic Empty Mass of an aircraft be obtained?
Where can the Basic Empty Mass of an aircraft be found?
What is the definition of the Center of Gravity?
The name of the point which the sum of all weights of the aircraft are considered to act through during flight is:
The position of the Center of Gravity (CG) of an aircraft is measured from the:
Evaluate the following statements: 1. The datum must be located at the nose of the aircraft; 2. The datum is the point from which all the balance arms begin.
Why is the calculation of the position of the Center of Gravity (CG) necessary in aviation?
For which masses shall the CG position be indicated on the CG envelope?
In which case must be the aircraft reweighed?
If the datum is not located at the nose of the aircraft, the value of a balance arm may be:
Which point on the aircraft has an effect on the stability?
For which masses shall the center of gravity (CG) position be calculated?
What is required for equilibrium regarding forces acting an aircraft?
What is the name of the condition of an aircraft when the sum of all the moments is zero?
Regarding the CG positions, which points cannot be exceeded?
How may the moment of the balance arm of the Basic Empty Mass be obtained?
What are the requirements for equilibrium? 1. Forces acting upwards equal with forces acting downwards; 2. Forces acting forward may not be equal to forces acting backward.
What is the reference point regarding Mass and Balance calculations?
What is the name of the distance from the datum to the center of mass of a body regarding Mass and Balance calculations?
How can the position of the center of gravity (CG) be obtained?
Evaluate the following statements: 1. The name of the distance from the datum to the center of a mass of a body is the balance arm; 2. The balance arm must be a positive value.
What is the name of the point from which all the balance arms begin?
In the case of deviation from the standard configuration, what is the correct action?
Determination of CG position
Section titled "Determination of CG position"What is the purpose of the graphic method regarding the Mass and Balance calculations?
What is the purpose of the arithmetic method concerning CG determination?
Load and trim sheet
Section titled "Load and trim sheet"How can the position of the center of gravity of a given state of an aircraft be obtained?
Refer to figure ppl-030-026. What is the Zero Fuel Mass CG position of the aircraft approximately?
Refer to figure ppl-030-025. What is the landing mass CG position of the aircraft?
How can the moment be obtained?
What can be obtained from the load and trim sheet?
Refer to figure ppl-030-030. Given: 1. BEM: 1200 kg 2. BEM CG: 3.00 3. Pilot and front pax: 200 kg 4. Cargo (PAX floor): 50 kg 5. Fuel: 250 kg Find the center of gravity (CG) by using the attached sheet:
Refer to figure 696 figure 2.5. What is the value of the Take-off Mass and the corresponding CG position?
Refer to CAP 696 figure 2.5. What is the value of the Zero Fuel Mass and the corresponding CG position?
Refer to figure ppl-030-025. What is the value of the Take-off Mass (TOM) of the aircraft?
What is the purpose of the load and trim sheet?
Refer to figure 696 figure 2.5. What is the value of the Landing Mass and the corresponding CG position?
Purpose of mass and balance considerations
Section titled "Purpose of mass and balance considerations"What are the effects with regards to the performance, when the center of gravity (CG) is at the aft limit of an aeroplane, compared to a CG further forward?
Regarding the structural limitations, what can reduce the aeroplane performance?
What is the result of the aft center of gravity position of an aircraft in case of a spin?
Regarding performance, what could the consequence be when exceeding the structural limitations of an aircraft?
Why would exceeding the structural limitations of an aircraft become a problem later on?
What are the effects with regards to performance, when the center of gravity (CG) is at the forward limit of an aeroplane, compared to a center of gravity (CG) further aft?
What are the effects when the CG is outside the aft limit regarding stability and controllability?
Which of the following options are correct? 1. Exceeding the structural limitations of an aircraft could cause fatigue. 2. Exceeding the mass limitations of an aircraft could cause structural failure. 3. Exceeding the mass limitations of an aircraft, the take-off and landing distances will increase. 4. Exceeding the mass limitations of an aircraft, climb gradient will decrease. 5. Exceeding the mass limitations of an aircraft, fuel consumption will decrease. 6. Exceeding the mass limitations of an aircraft will increase range.
Which of the following options contain all the forces acting on an aircraft during steady straight and level cruise?
What will happen, if the weight of an aircraft exceeds its structural limitations? 1. It decreases the safe hours of operation of structural parts. 2. It improves the performance of the aircraft.
What is determined by the CG position of an aircraft?
Evaluate the following statements: 1. When the Center of Gravity of an aircraft is outside the forward limit there is a pitch up tendency; 2. When the Center of Gravity of an aircraft is outside the aft limit there is a pitch up tendency.
What are the forms of stress on the structural parts of an aircraft?
What are the effects when the center of gravity (CG) is outside the forward limit regarding stability and controllability?
Loading
Section titled "Loading"When the number of passenger seats in an aeroplane is __, passenger mass may be calculated on the basis of a statement by, or on behalf of, each passenger, adding to it a predetermined mass to account for hand baggage and clothing.
What is included in the Dry Operating Mass?
What is the standard mass value for the flight crew including their hand baggage?
Regarding passenger classification, at what age is a passenger considered as a 'child'?
Under what age shall a passenger be considered as an 'infant'?
What shall be added to the Dry Operating Mass to obtain the Zero Fuel Mass?
What does the Zero Fuel Mass comprise of?
What is included in the useful load?
What is the name of the mass that comprises of the DOM and the Take-Off Fuel?
What is the Traffic Load of an aircraft?
Given the following: 1. Performance-limited take-off mass: 1920 lb 2. Dry operating mass: 1120 lb 3. Take-off fuel: 290 lb 4. Unusable fuel: 5 lb 5. Pilot: 185 lb 6. Passenger: 210 lb 7. Baggage: 60 lb What is the actual take-off mass?
What is the Taxi Mass of an aeroplane?
The maximum landing mass (MLM) for a specific aircraft is 1070 kg. The total fuel onboard for the flight during take-off is 100 kg and the aircraft burns 60 kg during the flight. What is the mass of the aircraft at landing if the take-off mass was 1120 kg?
Which mass includes the mass of the crew?
Given the following data: 1. Maximum Take-off Mass (MTOM): 1150 kg 2. Basic Empty Mass (BEM): 650 kg 3. Fuel mass: 120 kg 4. Passenger mass: 150 kg 5. Baggage mass: 50 kg What is the actual take-off mass, and is it within the maximum take-off mass limit?
What does the Take-off Mass comprise of?
At what age is a passenger considered to be an adult?
What does the Take-off Mass comprise of?
Given: 1. Zero Fuel Mass (ZFM): 5120 kg 2. Trip Fuel: 850 kg 3. Block Fuel: 1320 kg 4. Taxi Fuel: 30 kg What is the actual Take-off Mass (TOM)?
The MTOM of an aircraft is 2800 kg, MLM is 2500 kg, ZFM is 1500 kg. 680 kg of fuel was loaded at the ramp. The pilot's weight is 85 kg, 4 passengers, each weighing 80 kg and additional 150 kg is situated in the cargo compartment. The aircraft burns 10 kg of fuel during taxi and 350 kg of fuel during the whole flight Calculate the LM (Landing Mass) and the TOM (Take-Off Mass).
What is included in the Basic Empty Mass of an aircraft?
For an aircraft with 15 passenger seats:
What does the Take-off Mass comprise of?
For an aeroplane, the standard mass values for baggage are used if:
What shall be added to the Operating Mass to obtain the Take-off Mass?
How shall the Landing Mass of an aeroplane be obtained?
What shall be added to the Dry Operating Mass in order to obtain Take-off Mass?