With engine bleed for packs off, increase gradient by 0.3%.
With engine anti-ice on, decrease gradient by 0.1%.
With engine and wing anti-ice on, decrease gradient by 0.3%.
Decrease gradient by 0.6% for ice accumulation when operating in icing conditions during any part of the
flight with forecast landing temperatures below 10°C.

Copyright . The Boeing Company. See title page for details.
737-900/CFM56-7B26

Performance Dispatch
FAA
Landing
Category G Brakes
737 Flight Crew Operations Manual
Quick Turnaround Limit Weight Flaps 40
OAT (°C)  AIRPORT PRESSURE ALTITUDE (FT) 
0  2000  4000  6000  8000  10000 
54 50 45  80.1 80.6 81.3  77.6 78.3  75.3 
40 35 30  81.9 82.7 83.4  78.9 79.6 80.3  75.9 76.6 77.2  73.1 73.7 74.3  70.8 71.4  68.6 
25 20 15  84.1 84.8 85.6  81.0 81.7 82.4  77.9 78.6 79.3  75.0 75.6 76.3  72.0 72.7 73.3  69.2 69.8 70.4 
10 5 0  86.1 86.1 86.1  83.2 83.9 84.7  80.0 80.8 81.5  77.0 77.7 78.5  74.0 74.7 75.4  71.1 71.8 72.4 
-5 -10 -15  86.1 86.1 86.1  85.6 86.1 86.1  82.3 83.1 84.0  79.2 80.0 80.8  76.1 76.9 77.7  73.1 73.9 74.6 
-20 -30 -40  86.1 86.1 86.1  86.1 86.1 86.1  84.8 86.1 86.1  81.6 83.3 85.2  78.5 80.1 81.9  75.4 77.0 78.6 
-50 -54  86.1 86.1  86.1 86.1  86.1 86.1  86.1 86.1  83.8 84.5  80.5 81.2 

Increase weight by 700 kg per 1% uphill slope.  Decrease weight by 1400 kg per 1% downhill slope. Increase weight by 1800 kg per 10 knots headwind.  Decrease weight by 7500 kg per 10 knots tailwind.
After landing at weights exceeding those shown above, adjusted for slope and wind, wait at least 67 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 temperature, without artificial cooling, 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 subsequent 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.
March 28, 2005  PD.62.5
Performance Dispatch

737-900/CFM56-7B26 Landing
FAA Category G Brakes
737 Flight Crew Operations Manual
Intentionally
Blank

Copyright . The Boeing Company. See title page for details.
737-900/CFM56-7B26 FAA Category G 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, Obstacle, Brake Energy and Tire Speed Limit Weights as determined from the tables shown.
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.
　
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