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• CG limits—the specified forward and aft points within which the CG must be located during flight. These limits are indicated on pertinent aircraft specifications. 

• CG range—the distance between the forward and aft CG limits indicated on pertinent aircraft specifications. 

• Datum (reference datum)—an imaginary vertical plane or line from which all measurements of arm are taken. The datum is established by the manufacturer. Once the datum has been selected, all moment arms and the location of CG range are measured from this point. 

• Delta—a Greek letter expressed by the symbol r  to indicate a change of values. As an example, r CG indicates a change (or movement) of the CG. 

• Floor load limit—the maximum weight the floor can sustain per square inch/foot as provided by the manufacturer. 

• Fuel load—the expendable part of the load of the aircraft. It includes only usable fuel, not fuel required to fill the lines or that which remains trapped in the tank sumps. 

• Licensed empty weight—the empty weight that consists of the airframe, engine(s), unusable fuel, and undrainable oil plus standard and optional equipment as specified in the equipment list. Some manufacturers used this term prior to GAMA standardization. 

• Maximum landing weight—the greatest weight that an aircraft is normally allowed to have at landing. 

• Maximum ramp weight—the total weight of a loaded aircraft including all fuel. It is greater than the takeoff weight due to the fuel that will be burned during the taxi and run-up operations. Ramp weight may also be referred to as taxi weight. 

• Maximum takeoff weight—the maximum allowable weight for takeoff. 

• Maximum weight—the maximum authorized weight of the aircraft and all of its equipment as specified in the TCDS for the aircraft. 

• Maximum zero fuel weight (GAMA)—the maximum weight, exclusive of usable fuel. 

• Mean aerodynamic chord (MAC)—the average distance from the leading edge to the trailing edge of the wing. 

• Moment—the product of the weight of an item multiplied by its arm. Moments are expressed in pound-inches (in-lb). Total moment is the weight of the airplane multiplied by the distance between the datum and the CG. 

• Moment index (or index)—a moment divided by a constant such as 100, 1,000, or 10,000. The purpose of using a moment index is to simplify weight and balance computations of aircraft where heavy items and long arms result in large, unmanageable numbers. 

• Payload (GAMA)—the weight of occupants, cargo, and baggage. 

• Standard empty weight (GAMA)—aircraft weight that consists of the airframe, engines, and all items of operating equipment that have fixed locations and are permanently installed in the aircraft, including fixed ballast, hydraulic fluid, unusable fuel, and full engine oil. 

• Standard weights—established weights for numerous items involved in weight and balance computations. These weights should not be used if actual weights are available. Some of the standard weights are: 

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• Station—a location in the aircraft that is identified by a number designating its distance in inches from the datum. The datum is, therefore, identified as station zero. An item located at station +50 would have an arm of 50 inches. 

• Useful load—the weight of the pilot, copilot, passengers, baggage, usable fuel, and drainable oil. It is the basic empty weight subtracted from the maximum allowable gross weight. This term applies to general aviation (GA) aircraft only. 

## Principles of Weight and Balance Computations 

It is imperative that all pilots understand the basic principles of weight and balance determination. The following methods of computation can be applied to any object or vehicle for which weight and balance information is essential. 

By determining the weight of the empty aircraft and adding the weight of everything loaded on the aircraft, a total weight can be determined—a simple concept. A greater problem, particularly if the basic principles of weight and balance are not understood, is distributing this weight in such a manner that the entire mass of the loaded aircraft is balanced around a point (CG) that must be located within specified limits. 

The point at which an aircraft balances can be determined by locating the CG, which is, as stated in the definitions of terms, 

