Floor Load = Loaded weight Pallet area 857.5 11.28 = 76.0 pounds/square foot = Max limit 138,000 Zero fuel weight – BOW Payload (pounds) Trip limit 128,000 –100,500 27,500 Max limit 142,000 184,200 Landing weight + trip fuel Takeoff weight Trip limit 142,000 + 40,000 182,000 Max limit 184,200 138,000 Landing weight – fuel load Zero fuel weight Trip limit 182,000 – 54,000 128,000 Figure 9-30.  Finding the maximum takeoff weight. Figure 9-31.  Determining zero fuel weight with lower trip limits. Figure 9-32.  Finding maximum payload with lower trip limits. Figure 9-29.  Determining the load imposed on the floor by the  loaded pallet. Determining the Maximum Amount of Payload  That Can Be Carried Determining the Landing Weight Under these conditions, 27,500 pounds of payload may be  carried. It is important to know the landing weight of the aircraft in  order to set up the landing parameters and to be certain the  aircraft is able to land safely at the intended destination. In this example of a four-engine turboprop airplane,  determine the airplane weight at the end of 4.0 hours of cruise  under these conditions: The primary function of a transport or cargo aircraft is to carry  payload, which is the portion of the useful load, passengers,  or cargo that produces revenue. To determine the maximum  amount of payload that can be carried, both the maximum  limits for the aircraft and the trip limits imposed by particular trip must be considered. In each of the following  steps, the trip limit must be less than the maximum limit. If  it is not, the maximum limit must be used. These are the specifications for the aircraft in this example Refer to the U.S. Standard Atmosphere Table in  Figure 9-33  and the gross weight table in  Figure 9-34  when  completing the following steps: 3.  The trip limit is again lower than the maximum takeoff  weight, so use it to compute the maximum payload  for this trip.  [Figure 9-32] 1.  Compute the maximum takeoff weight for this trip.  This is the maximum landing weight plus the trip fuel.  [Figure 9-30] 1.  Use the U.S. Standard Atmosphere Table to  determine the standard temperature for 16,000 feet  (–16.7 °C).  2.  The ambient temperature is –32 °C, which is a  deviation from standard of 15.3 °C. (–32° – (–16.7°)  = –15.3°). It is below standard. 3.  In the gross weight table, follow the vertical line  representing 140,000 pounds gross weight upward  until it intersects the diagonal line for 16,000 feet  pressure altitude. 4.  From this intersection, draw a horizontal line to the left  to the temperature deviation index (0 °C deviation). 5.  Draw a diagonal line parallel to the dashed lines for  Below Standard from the intersection of the horizontal  line and the Temperature Deviation Index. 6.  Draw a vertical line upward from the 15.3 °C  Temperature Deviation From Standard. 2.  The trip limit is lower than the maximum takeoff  weight, so it is used to determine the zero fuel weight.  [Figure 9-31] Basic operating weight (BOW) ..................... 100,500 lb Maximum zero fuel weight............................ 138,000 lb Maximum landing weight.............................. 142,000 lb Maximum takeoff weight .............................. 184,200 lb Fuel tank load ................................................. 54,000 lb Estimated fuel burn en route............................ 40,000 lb Takeoff weight............................................... 140,000 lb Pressure altitude during cruise..........................16,000 ft Ambient temperature during cruise .....................–32 °C Fuel burned during descent and landing............ 1,350 lb 9-10