2-6 FAA-Furnished Weight and Balance  Information  Empty Weight CG Range (EWCG) Number of Seats Maximum Weights Maximum Baggage  Fuel Capacity CG Range Oil Capacity (Wet Sump) The position of the fore and aft CG limits is measured as a  percentage of MAC from the MAC leading edge. Usually for  a single or two-seat aircraft, the most forward position would  be forward of 30–35 percent MAC. Thus, the allowable CG  range in a light aircraft should not exceed 20 percent MAC. Aft Limits: 144.6 in at 2,110 lb, with straight line taper to  147.4 in at 2,570 lb, and to 148.1 in at 2,900 lb, and 148.0  in at 3,000 lb Note: For a rectangular width of constant airfoil section  dimensions, MAC is just the chord. For a symmetrically- tapered wing, it is the average of the root chord and the tip  chord. S/N 1878, 1886 and Subsequent: Forward Limits: 137.8 in at 2,100 lb with a straight line taper  to 139.1 in at 2,700 lb, and to 140.7 in at 3,050 lb Aft Limits: 148.1 in at 2,100 lb, with straight line to 148.1  in at 3,050 lb The information discussed to this point can be readily applied  to any aircraft weight and balance problem. To apply the  techniques, certain elements of information are required.  This information is obtained from both FAA documents and  manufacturer provided data.  When all of the seats and baggage compartments are located  close together, it is not possible (as long as the EWCG is  located within the EWCG range) to legally load the aircraft  so that its operational CG falls outside this allowable range.  If the seats and baggage areas extend over a wide range, the  EWCG range is listed as “None.” Before an aircraft CG can be computed, certain information  must be known. This information, furnished by the FAA  for every certificated aircraft in the Type Certificate Data  Sheets (TCDS) or Aircraft Specifications, can be accessed  at www.faa.gov. When the design of an aircraft is approved  by the FAA, an Approved Type Certificate and TCDS are  issued. The TCDS includes all of the pertinent specification for the aircraft; at each annual or 100-hour inspection, it is  the responsibility of the inspecting mechanic or repairman  to ensure that the aircraft adheres to them. A note about the  TCDS: aircraft certifi ated before January 1, 1958, were  issued Aircraft Specifica ions under the Civil Air Regulations  (CARs), but when the Civil Aeronautical Administration  (CAA) was replaced by the FAA, Aircraft Specification were replaced by the TCDS. The maximum allowable takeoff and landing weights and  the maximum allowable ramp weight are given. This basic  information may be altered by a note. Notes are found in data  pertinent to all models. An example would be Note 6 at the  end of  Figure 2-15. The number of seats and their arms are given in such terms  as: 4 (2 at 143.5 aft of datum, 2 at 180 aft of datum). The weight and balance information on a TCDS includes CG  range, empty weight CG range (EWCG), maximum weights,  number of seats, maximum baggage, fuel capacity, oil  capacity, and datum location. Data pertinent to an individual  model is located in its respective section of the TCDS. Use  the TCDS excerpts in  Figure 2-15  to verify the following for  a Cirrus Design Corporation SR 20 normal category: Maximum baggage for this model is 130 pounds at 208  inches. This important information is given in such terms as: 60.5  gal at 153.75 in. Usable: 56 gal (See Note 1). Notes can be  found in data pertinent to all models. The quantity of the full oil supply and its arm are given: 8  quarts at 76.2 in. Aft Limits: 144.6 in at 2,110 lb, with straight line taper to  147.4 in at 2,570 lb, and to 147.9 in at 2,745 lb, and 148.2  in at 2,900 lb S/N 1005 through 1147: Forward Limits: 138.7 inches at 2,110 lb with a straight line  taper to 141.0 in at 2,694 lb and 143.0 in at 2,900 lb S/N 1148 through 1877, 1879 through 1885, and S/N 1005  through 1147 if Cirrus Service Bulletin SB 20-01-00 is  complied with: Forward Limits: 138.7 in at 2,110 lb with a straight line taper  to 141.0 in at 2,694 lb and 144.1 in at 3,000 lb