737-700/CFM56-7B22 Landing
FAA Category A Brakes
737 Flight Crew Operations Manual
Quick Turnaround Limit Weight - High Altitudes Flaps 40
OAT (°C) LIMIT WEIGHT (1000 KG)
AIRPORT PRESSURE ALTITUDE (FT)
10000 11000 12000 13000 13500
30 25 20 60.8 61.3 61.8 59.5 60.0 60.5 58.2 58.7 59.2 57.4 57.9 56.8 57.3
15 10 5 62.4 62.9 63.5 61.0 61.6 62.1 59.7 60.3 60.8 58.5 59.0 59.5 57.8 58.3 58.9
0 -5 -10 64.1 64.6 65.3 62.7 63.3 63.9 61.4 62.0 62.5 60.1 60.6 61.2 59.4 60.0 60.5
-15 -20 -25 65.9 66.6 67.3 64.5 65.1 65.8 63.1 63.8 64.4 61.8 62.4 63.0 61.1 61.7 62.3
-30 -35 -40 68.0 68.8 69.6 66.5 67.3 68.0 65.0 65.8 66.5 63.7 64.3 65.0 63.0 63.6 64.3
-45 -50 -54 70.4 71.2 71.8 68.8 69.6 70.2 67.2 68.0 68.7 65.7 66.5 67.1 65.0 65.7 66.3
Increase weight by 600 kg per 1% uphill slope. Decrease weight by 900 kg per 1% downhill slope. Increase weight by 1450 kg per 10 knots headwind. Decrease weight by 6350 kg per 10 knots tailwind.
After landing at weights exceeding those shown above, adjusted for slope and wind, wait at least 62 minutes and check that wheel thermal plugs have not melted before executing a subsequent takeoff.
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 62 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 62 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.
737-700/CFM56-7B22 FAA Category A 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.
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