737-700/CFM56-7B22 Landing
FAA Category A Brakes
737 Flight Crew Operations Manual

ADVISORY INFORMATION
Go-Around Climb Gradient - High Altitudes Flaps 15 Based on engine bleed for packs on and anti-ice off
OAT (°C)  REFERENCE GO-AROUND GRADIENT (%) 
PRESSURE ALTITUDE (FT) 
10000  12000  14000 
34 30 26  0.43 0.88 1.31  0.40 
22 18 14  1.75 2.19 2.68  0.79 1.20 1.64  0.30 0.71 
10 6 2 -2  3.26 3.27 3.28 3.28  2.09 2.49 2.50 2.50  1.13 1.51 1.80 1.81 

Gradient Adjustment for Weight (%)
WEIGHT  REFERENCE GO-AROUND GRADIENT (%) 
(1000 KG)  0  1  2  3  4 
70 65 60  -2.79 -2.27 -1.66  -3.14 -2.56 -1.86  -3.51 -2.85 -2.08  -3.87 -3.14 -2.28  -4.19 -3.39 -2.46 
55 50 45 40  -0.91 0.00 1.11 2.54  -1.02 0.00 1.22 2.79  -1.14 0.00 1.35 3.07  -1.25 0.00 1.49 3.39  -1.35 0.00 1.63 3.70 

Gradient Adjustment for Speed (%)
SPEED  WEIGHT ADJUSTED GO-AROUND GRADIENT (%) 
(KIAS)  0  1  2  3  4  5  6  7 
VREF VREF+5 VREF+10  -0.34 0.00 0.20  -0.36 0.00 0.20  -0.38 0.00 0.21  -0.39 0.00 0.21  -0.40 0.00 0.21  -0.40 0.00 0.21  -0.40 0.00 0.21  -0.39 0.00 0.20 
VREF+15 VREF+20 VREF+25 VREF+30  0.32 0.38 0.36 0.27  0.33 0.37 0.33 0.21  0.34 0.35 0.29 0.14  0.33 0.34 0.25 0.08  0.33 0.32 0.21 0.03  0.32 0.30 0.19 0.00  0.31 0.29 0.17 -0.03  0.30 0.27 0.15 -0.05 

With engine bleed for packs off, increase gradient by 0.3%.
With engine anti-ice on, decrease gradient by 0.1% for altitudes up to 10000 ft and by 0.5% for altitudes
above 10000 ft.
With engine and wing anti-ice on, decrease gradient by 0.3% for altitudes up to 10000 ft and by 0.7% for
altitudes above 10000 ft.
When operating in icing conditions during any part of the flight with forecast landing temperatures below
10°C decrease gradient by 0.9%.

Copyright . The Boeing Company. See title page for details.
737-700/CFM56-7B22

Performance Dispatch
FAA
Landing
Category A Brakes
737 Flight Crew Operations Manual
Quick Turnaround Limit Weight Flaps 40
OAT (°C)  LIMIT WEIGHT (1000 KG) 
AIRPORT PRESSURE ALTITUDE (FT) 
0  2000  4000  6000  8000  10000 
54 50 45  71.8 72.3 72.9  69.4 70.0  67.1 
40 35 30  73.5 74.2 74.9  70.6 71.2 71.8  67.7 68.3 68.9  64.9 65.5 66.0  62.8 63.4  60.8 
25 20 15  75.6 76.3 77.0  72.5 73.1 73.8  69.5 70.1 70.8  66.6 67.2 67.8  63.9 64.4 65.0  61.3 61.8 62.4 
10 5 0  77.7 78.4 79.1  74.5 75.2 76.0  71.4 72.1 72.8  68.5 69.1 69.8  65.6 66.2 66.9  62.9 63.5 64.1 
-5 -10 -15  79.9 80.6 81.4  76.7 77.5 78.3  73.5 74.3 75.1  70.5 71.2 71.9  67.5 68.2 68.9  64.6 65.3 65.9 
-20 -30 -40  81.6 81.6 81.6  79.0 80.7 81.6  75.9 77.5 79.2  72.7 74.2 75.9  69.6 71.1 72.7  66.6 68.0 69.6 
-50 -54  81.6 81.6  81.6 81.6  80.9 81.6  77.7 78.4  74.4 75.1  71.2 71.8 

Increase weight by 650 kg per 1% uphill slope.  Decrease weight by 1150 kg per 1% downhill slope. Increase weight by 1600 kg per 10 knots headwind.  Decrease weight by 8000 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.
　
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