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As an alternate procedure, ensure that each brake pressure plate surface temperature, without artificial cool-ing, is less than 218°C as follows:  No sooner than 10 and no later than 15 minutes after parking, measure each brake pressure plate surface temperature at a minimum of two points per brake by an accurate method (using a Doric Microtemp 450 hand held thermometer or equivalent, hold temperature probe in place for 20 seconds or until reading stabilizes).  If each measured temperature is less than 218°C, immediate dispatch is allowed; otherwise the required minimum ground wait period of 67 minutes applies.
If a Brake Temperature Monitoring System (BTMS) is installed:
No sooner than 10 and no later than 15 minutes after parking, check the BRAKE TEMP light. If the BRAKE TEMP light is not on, no ground waiting period is required. If the BRAKE TEMP light is on, do not dispatch until at least 67 minutes after landing, or until all the BTMS readings on the systems Display are below 3.5 and the BRAKE TEMP light is off. Check that wheel thermal plugs have not melted before making a subse-quent takeoff. Note: If any brake temperature display digit is blank or indicates 0.0 or 0.1, then this method cannot be used.
Copyright . The Boeing Company. See title page for details.
737-800/CFM56-7B27 FAA Category C Brakes 737 Flight Crew Operations Manual

Introduction
This chapter contains self dispatch performance data intended primarily for use by flight crews in the event that information cannot be obtained from the airline dispatch office.  The takeoff data provided is for a single takeoff flap at max takeoff thrust. The range of conditions covered is limited to those normally encountered in airline operation. In the event of conflict between the data presented in this chapter and that contained in the approved Airplane Flight Manual, the Flight Manual shall always take precedence.
Takeoff
The maximum allowable takeoff weight will be the least of the Field, Climb and Obstacle Limit Weights as determined from the tables shown. Tire and Brake Energy Limits are not shown as they are not limiting for the range of conditions shown in this chapter.
Field Limit Weight - Slope and Wind Corrections
These tables for dry and wet runways provide corrections to the field length available for the effects of runway slope and wind component along the runway.  Enter the appropriate table with the available field length and runway slope to determine the slope corrected field length.  Next enter the appropriate table with slope corrected field length and wind component to determine the slope and wind corrected field length.
Field and Climb Limit Weight
Tables are presented for selected airport pressure altitudes and runway conditions and show both Field and Climb Limit Weights. Enter the appropriate table for pressure altitude and runway condition with “Slope and Wind Corrected Field Length” determined above and airport OAT to obtain Field Limit Weight.  Also read Climb Limit Weight for the same OAT. Intermediate altitudes may be interpolated or use next higher altitude. When finding a maximum weight for a wet runway, the dry runway limit weight must also be determined and the lower of the two weights used.
Copyright . The Boeing Company. See title page for details.
September 27, 2004  PD.53.1
Performance Dispatch

737-800/CFM56-7B27 Text
FAA Category C Brakes
737 Flight Crew Operations Manual
Obstacle Limit Weight
The Reference Obstacle Limit Weight table provides obstacle limit weights for reference airport conditions based on obstacle height above the runway surface and distance from brake release. Enter the adjustment tables to adjust the reference Obstacle Limit Weight for the effects of OAT, pressure altitude and wind as indicated.  In the case of multiple obstacles, enter the tables successively with each obstacle and determine the most limiting weight.
Enroute Long Range Cruise Maximum Operating Altitude
These tables provide the maximum operating altitude in the same manner as the FMC.  Maximum altitudes are shown for a given cruise weight and maneuver capability. Note that this table considers both thrust and buffet limits, providing the more limiting of the two.  Any data that is thrust limited is denoted by an asterisk and represents only a thrust limited condition in level flight with 100 ft/min residual rate of climb. Flying above these altitudes with sustained banks in excess of approximately 15° may cause the airplane to lose speed and/or altitude. The altitudes shown in the table are limited to the maximum certified altitude of 41000 ft.
Long Range Cruise Trip Fuel and Time
Long Range Cruise Trip Fuel and Time tables are provided to determine
trip time and fuel required to destination. To determine trip fuel and time for a constant altitude cruise, first enter the Ground to Air Miles Conversion table to convert ground distance and enroute wind to an equivalent still air distance for use with the Reference Fuel and Time tables.  Next, enter the Reference Fuel and Time table with air distance from the Ground to Air Miles Conversion table and the desired altitude and read Reference Fuel and Time Required.  Lastly, enter the Fuel Required Adjustment table with the Reference Fuel and the planned landing weight to obtain the adjustment to the fuel required at the planned landing weight.
　
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