Sec. 5 Page 94 737
Rev. 11/15/02 #41 Continental Flight Manual
MANUAL CALCULATION OF LANDING DATA
In the absence of ACCULOAD the maximum dispatch Landing Limit Weight
for a specific runway may be determined manually by flight crews using the
following procedures:
1. Determine the maximum Structural Landing Weight for the series aircraft
being flown from the Flight Manual, Chapter 1, Limitations.
2. Calculate the Approach Climb Limit Weight as described below.
3. Calculate the Runway Limit Landing Weight as described below.
4. Select the lesser of these three as the Landing Limit Weight.
Under normal circumstances the landing weight of the B737 is limited by the
maximum structural landing weight. Only in non-normal cases with very high
temperatures, extremely short runways, or with the anti-skid inoperative, will
the maximum dispatch landing weight be below the maximum structural landing
weight.
Approach Climb Limit
If ACCULOAD is not available, determine the Approach Climb Limit in the
following manner:
1. Enter the Approach Climb Limit chart for the appropriate aircraft type and
planned flap setting at the forecast ambient temperature, rounded up to the
next 10 degree increment, and follow that temperature to the appropriate
pressure altitude column. This is the normal Approach Climb Limit
weight.
2. Review the notes below the chart and adjust the weight appropriately to
derive the Approach Climb Limit Weight for the planned non-normal
conditions.
Note: Interpolation is authorized between pressure altitude and temperature
when absolute maximum weight is necessary.
737 Sec. 5 Page 95
Flight Manual Continental Rev. 11/15/02 #41
>> Approach Climb Limit Weight
APPROACH CLIMB LIMIT WEIGHT, LB. X 100
LANDING FLAPS 30
°F PRESSURE ALTITUDE
S.L. 1000 2000 3000 4000 5000 5300 6000 7000 8000
-20
0
20
40
60
70
80
90
100
110
120
1358
1356
1355
1351
1345
1344
1340
1320
1273
1220
1161
1340
1339
1336
1333
1328
1325
1323
1292
1251
1194
1136
1322
1320
1317
1314
1310
1305
1302
1260
1216
1170
1120
1313
1311
1308
1304
1300
1296
1287
1265
1216
1170
1120
1316
1314
1311
1306
1304
1300
1296
1264
1205
1153
1091
1285
1282
1280
1275
1271
1270
1265
1222
1165
1113
1030
1275
1272
1270
1266
1261
1260
1252
1207
1151
1099
1015
1254
1251
1249
1245
1240
1237
1224
1175
1120
1069
983
1211
1208
1205
1203
1200
1195
1158
1110
1061
1010
NA
1173
1170
1169
1165
1157
1146
1100
1045
1012
953
NA
APPROACH CLIMB LIMIT WEIGHT, LB. X 100
LANDING FLAPS 40
°F PRESSURE ALTITUDE
S.L. 1000 2000 3000 4000 5000 5300 6000 7000 8000
-20
0
20
40
60
70
80
90
100
110
120
1325
1323
1320
1316
1313
1310
1307
1284
1230
1175
1117
1307
1305
1304
1300
1295
1292
1288
1253
1214
1150
1092
1288
1285
1283
1279
1274
1270
1263
1218
1175
1125
1075
1278
1276
1272
1269
1264
1260
1251
1228
1175
1125
1075
1281
1279
1275
1272
1267
1264
1260
1228
1165
1106
1045
1247
1245
1243
1238
1234
1231
1228
1180
1112
1068
990
1235
1232
1230
1225
1221
1218
1212
1152
1105
1050
967
1212
1210
1208
1204
1200
1196
1182
1130
1075
1024
944
1167
1165
1162
1159
1156
1150
1113
1065
1018
972
NA
1129
1126
1124
1120
1115
1104
1055
1004
972
913
NA
· When icing conditions are forecast during any part of the flight, and the
　
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