JAA ATPL MASS AND BALANCE PDF

Mass and Balance covers the factors governing the loading of an aeroplane to ensure that the longitudinal centre of gravity and mass are within the structural. Questions-Mass-and-balance · View. Mass and Balance, Oxford · View. Mass and Balance ATPL · View. Operational Procedures · View. Buy JAA ATPL Mass & Balance – JA and other aviation books at yout pilot shop headquarters, Pilots HQ.

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To calculate the linear load divide the weight by the longitudinal length.

Onboard Mass and Balance Systems 9. The amended table should now appear as at Figure The fact that the C of G is within limits does not necessarily mean that the loaded aeroplane is within the bending limitations. There is a set of rules and requirements for each Class of aeroplanes, which dictate the maximum mass at which an aeroplane may be operated during any particular phase of flight. Lab One Inc Lamar Technolog.

A Weight and Centre-of-Gravity Schedule shall be provided for each aircraft the Maximum Total Weight Authorised of which exceeds kg, except that for an aircraft the Maximum Total Weight Authorised or which exceeds kg the information contained in Parts B and C of the Schedule may, for a new aircraft, be given as part of the Weight and Balance Report.

The Calculation of Aircraft Weight 6.

Jeppesen. JAA ATPL Training Mass and Balance [PDF] – Все для студента

The total fuel required on any particular flight comprise the following: In other words to avoid a situation where the elevators are fully deflected in order to maintain a level pitch attitude. Ba,ance revised baggage distribution is snd as shown in the table which follows. The SG of pure water is taken as the datum SG of 1. The size of the traffic load may be restricted by reasons other than mxss disposable load which is available once the fuel load has been decided.

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Under certain circumstances, standard crew and passenger weights are assumed, otherwise the weight of each crew member must be determined by weighing. These structural weights include the maximum structural ramp weight, the maximum structural take-off weight, the maximum zero fuel weight and the maximum structural landing weight. Nose-Wheel Weight Arm Moment lb.

The weights measured through each wheel are: The size of the traffic load may be restricted by reasons other than the disposable load which is available once the fuel load has been decided. The nose-wheel is 10 inches aft of the datum and the main wheels are inches aft of the datum.

031 Aircraft Mass & balance (JAA ATPL theory).

With a severe load shift it may be impossible to return the aircraft to level flight. Determination of Revised Standard Mass Values for Passengers and Checked Baggage Chapter 9 Page 11 a To ensure that, in preference to the use of actual masses determined by weighing, the use of revised standard mass values for passengers and checked baggage does not adversely affect operational safety; a statistical analysis see IEM-OPS 1.

By convention any weight which is positioned forward of the reference datum has a negative arm and therefore produces a negative moment. Conversely, by convention, any weight which is aft of the reference datum has a positive arm and therefore produces a positive moment.

The CG of an aircraft is the point through which all of its weight is assumed to act in a vertically downward direction. The Back Seat P. In order to determine the weight and the arm of the basic aircraft, the first step is to determine the aircraft empty weight without fuel and payload by measuring the weight acting through each wheel on a small aircraft or through each jacking point on larger aircraft.

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Whether or not the fuel carried actually limits the traffic load, it is normally prudent to reduce the fuel load to a safe minimum in order to reduce the all up weight of the aircraft. The Joint Aviation Authority has the task of ensuring that all public transport aircraft, irrespective of size or number of engines, are operated to the highest possible level of safety.

Aircraft Mass & balance (JAA ATPL theory).pdf Download ( Pages | Free )

On pitching nose down any loose cargo will move forward, causing the aircraft to pitch further nose down. What consideration limits maximum ramp weight? C of G 25m. If the distance of the hold or fuel tank is ahead of the present CG the distance ajd a negative value and if it is aft of the present CG it is a positive value.

Hardware – Misc Hardwood Produc. Hardware Momentive Momentum Intera.

Faithful adherence to the fuel management procedures as laid down in the AFM will ensure that the CG remains within the specified limits during the flight. Weight Less Fuel and Payload 67, kg.

An acceptable means of compliance with the requirements would be to include in the Schedule instructions on the following lines: