Gradient Adjustment for Weight (%)
WEIGHT REFERENCE GO-AROUND GRADIENT (%)
(1000 KG) 0 1 2 3 4 5
70 65 60 -2.87 -2.33 -1.71 -3.26 -2.65 -1.94 -3.56 -2.89 -2.11 -3.87 -3.14 -2.29 -4.18 -3.39 -2.47 -4.48 -3.63 -2.64
55 50 45 40 -0.94 0.00 1.14 2.61 -1.06 0.00 1.26 2.87 -1.15 0.00 1.38 3.14 -1.25 0.00 1.51 3.42 -1.35 0.00 1.64 3.72 -1.44 0.00 1.77 4.02
Gradient Adjustment for Speed (%)
SPEED WEIGHT ADJUSTED GO-AROUND GRADIENT (%)
(KIAS) 0 1 2 3 4 5 6 7 8 9 10
VREF40 -0.35 -0.37 -0.38 -0.38 -0.39 -0.39 -0.39 -0.39 -0.39 -0.39 -0.39
VREF40+5 0.00 0.00 0.00 0.00 0.00 0.00 0.00 0.00 0.00 0.00 0.00
VREF40+10 0.20 0.21 0.21 0.21 0.21 0.21 0.21 0.21 0.21 0.21 0.21
VREF40+15 0.33 0.33 0.33 0.33 0.32 0.31 0.30 0.30 0.29 0.28 0.28
VREF40+20 0.39 0.37 0.36 0.34 0.32 0.30 0.28 0.27 0.26 0.25 0.23
VREF40+25 0.39 0.34 0.29 0.25 0.22 0.19 0.16 0.14 0.13 0.11 0.09
VREF40+30 0.31 0.22 0.14 0.08 0.03 -0.01 -0.04 -0.06 -0.08 -0.10 -0.13
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 0.2%.
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.
PD.12.6 September 27, 2004
737-700/CFM56-7B20
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.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737NG机组操作手册Flight Crew Operations Manual FCOM 1(117)
