Boeing 737 - 600/700/800/900. Operations Manual (1997 year) - page 19
Performance Dispatch
Enroute
FAA
Category C Brakes
Boeing 737 Operations Manual
Enroute
Long Range Cruise Step Climb
Ground to Air Miles Conversion
AIR DISTANCE (NM)
GROUND
AIR DISTANCE (NM)
HEADWIND COMPONENT (KTS)
DISTANCE
TAILWIND COMPONENT (KTS)
100
80
60
40
20
(NM)
20
40
60
80
100
1316
1237
1168
1106
1050
1000
954
912
874
839
807
1830
1724
1630
1545
1469
1400
1337
1280
1227
1179
1134
2343
2210
2091
1984
1888
1800
1720
1647
1580
1518
1461
2856
2695
2552
2423
2306
2200
2103
2015
1933
1858
1789
3369
3181
3013
2861
2724
2600
2486
2382
2287
2198
2117
3882
3666
3474
3300
3143
3000
2870
2750
2640
2539
2445
4395
4152
3934
3738
3561
3400
3253
3118
2993
2879
2772
4907
4637
4395
4177
3980
3800
3636
3485
3347
3219
3100
5420
5123
4856
4616
4398
4200
4019
3853
3700
3559
3428
5933
5608
5317
5054
4816
4600
4402
4221
4054
3899
3756
6447
6094
5778
5493
5235
5000
4785
4588
4407
4239
4084
Trip Fuel and Time Required
TRIP FUEL (1000 KG)
AIR DIST
TIME
LANDING WEIGHT (1000 KG)
(NM)
(HRS:MIN)
40
45
50
55
60
65
70
1000
4.5
4.8
5.2
5.6
5.9
6.4
6.7
2:24
1400
6.2
6.5
7.1
7.7
8.2
8.8
9.2
3:17
1800
7.8
8.3
9.1
9.8
10.5
11.2
11.9
4:10
2200
9.5
10.2
11.1
12.0
12.8
13.7
14.6
5:03
2600
11.3
12.1
13.2
14.2
15.3
16.3
17.4
5:56
3000
13.0
14.1
15.3
16.6
17.8
19.0
20.2
6:49
3400
14.9
16.1
17.5
19.0
20.3
21.8
23.2
7:42
3800
16.8
18.2
19.8
21.4
23.0
24.6
26.2
8:34
4200
18.8
20.4
22.2
24.0
25.7
27.6
9:27
4600
20.8
22.6
24.6
26.6
28.6
30.6
10:20
5000
22.9
24.9
27.0
29.3
31.5
33.7
11:13
Based on 280/.78 climb, Long Range Cruise or .78 and .78/280/250 descent.
Valid for all pressure altitudes with 4000 ft step climb to 2000 ft above optimum altitude.
PD.31.4
Performance Dispatch
FAA
Enroute
Category C Brakes
Boeing 737 Operations Manual
Enroute
Short Trip Fuel and Time
Ground to Air Miles Conversion
AIR DISTANCE (NM)
GROUND
AIR DISTANCE (NM)
HEADWIND COMPONENT (KTS)
DISTANCE
TAILWIND COMPONENT (KTS)
100
80
60
40
20
(NM)
20
40
60
80
100
93
80
69
61
55
50
46
42
39
36
34
160
143
129
118
108
100
93
87
82
77
73
225
205
188
173
161
150
141
132
125
118
112
290
266
246
228
213
200
188
178
169
160
153
353
326
303
283
265
250
236
224
213
203
194
416
386
360
338
318
300
284
270
257
245
235
478
446
417
392
370
350
332
316
301
288
276
542
506
474
447
422
400
380
362
346
331
317
606
567
532
502
474
450
428
408
390
373
358
672
629
591
557
527
500
476
454
434
415
398
Trip Fuel and Time Required
LANDING WEIGHT (1000 KG)
TIME
AIR DIST (NM)
40
45
50
55
60
65
70
(HRS:MIN)
FUEL (1000 KG)
0.5
0.5
0.6
0.6
0.7
0.7
0.7
50
0:14
ALT (FT)
12000
12000
11000
11000
9000
9000
8000
FUEL (1000 KG)
0.8
0.9
0.9
1.0
1.0
1.1
1.1
100
0:22
ALT (FT)
19000
18000
18000
18000
17000
17000
17000
FUEL (1000 KG)
1.1
1.1
1.2
1.3
1.3
1.4
1.5
150
0:30
ALT (FT)
26000
25000
25000
24000
23000
22000
22000
FUEL (1000 KG)
1.3
1.4
1.5
1.6
1.6
1.7
1.8
200
0:37
ALT (FT)
35000
30000
28000
27000
26000
26000
26000
FUEL (1000 KG)
1.5
1.6
1.7
1.8
1.9
2.0
2.1
250
0:44
ALT (FT)
40000
37000
36000
35000
34000
31000
30000
FUEL (1000 KG)
1.7
1.8
1.9
2.1
2.2
2.3
2.4
300
0:50
ALT (FT)
41000
40000
39000
37000
35000
34000
32000
FUEL (1000 KG)
1.9
2.0
2.2
2.3
2.4
2.6
2.7
350
0:56
ALT (FT)
41000
40000
40000
38000
36000
35000
33000
FUEL (1000 KG)
2.1
2.2
2.4
2.5
2.7
2.9
3.0
400
1:03
ALT (FT)
41000
40000
40000
38000
36000
35000
33000
FUEL (1000 KG)
2.3
2.5
2.6
2.8
3.0
3.1
3.3
450
1:10
ALT (FT)
41000
41000
40000
38000
36000
35000
34000
FUEL (1000 KG)
2.5
2.7
2.8
3.0
3.2
3.4
3.6
500
1:17
ALT (FT)
41000
41000
40000
38000
36000
35000
34000
Based on 280/.78 climb, Long Range Cruise and .78/280/250 descent.
Holding Planning
Flaps Up
TOTAL FUEL FLOW (KG/HR)
WEIGHT
PRESSURE ALTITUDE (FT)
(1000 KG)
1500
5000
10000
15000
20000
25000
30000
35000
41000
85
3080
3030
3020
2990
2970
2980
3080
80
2910
2870
2840
2830
2780
2790
2860
3130
75
2750
2700
2670
2650
2600
2600
2660
2800
70
2590
2540
2500
2480
2430
2420
2470
2550
65
2420
2370
2340
2310
2270
2230
2280
2330
60
2260
2210
2180
2140
2110
2050
2090
2130
55
2100
2050
2010
1980
1940
1890
1910
1940
2110
50
1950
1890
1850
1810
1780
1730
1750
1770
1890
45
1790
1730
1690
1680
1640
1610
1590
1590
1670
40
1670
1620
1560
1520
1480
1450
1440
1420
1480
This table includes 5% additional fuel for holding in a racetrack pattern.
PD.31.5
Performance Dispatch
Enroute
FAA
Category C Brakes
Boeing 737 Operations Manual
Enroute
Crew Oxygen Requirements
Required Pressure (PSI) for 76 Cu. Ft. Cylinder
BOTTLE
NUMBER OF CREW USING OXYGEN
TEMPERATURE
°C
°F
2
3
4
50
122
735
1055
1360
45
113
725
1040
1340
40
104
715
1020
1320
35
92
700
1005
1300
30
86
690
990
1280
25
77
680
975
1255
20
68
670
960
1240
15
59
655
940
1215
10
50
645
925
1195
5
41
635
910
1175
0
32
620
890
1150
-5
23
610
875
1130
-10
14
600
860
1110
Required Pressure (PSI) for 114/115 Cu. Ft. Cylinder
BOTTLE
NUMBER OF CREW USING OXYGEN
TEMPERATURE
°C
°F
2
3
4
50
122
530
735
945
45
113
520
725
930
40
104
510
715
915
35
92
505
700
900
30
86
495
690
885
25
77
485
680
870
20
68
480
670
860
15
59
470
655
840
10
50
460
645
830
5
41
455
635
815
0
32
445
620
800
-5
23
440
610
785
-10
14
430
600
770
PD.31.6
Performance Dispatch
FAA
Enroute
Category C Brakes
Boeing 737 Operations Manual
ENGINE INOP
MAX CONTINUOUS THRUST
Net Level Off Weight
PRESSURE ALTITUDE
LEVEL OFF WEIGHT (1000 KG)
(1000 FT)
ISA + 10°C & BELOW
ISA + 15°C
ISA + 20°C
30
42.5
41.3
28
46.3
44.9
43.5
26
50.3
48.8
47.3
24
54.7
52.9
51.3
22
59.4
57.4
55.5
20
64.4
62.2
60.1
18
69.4
66.9
64.4
16
74.2
71.8
69.4
14
78.1
76.3
74.3
12
83.4
81.1
78.2
10
86.1
85.4
81.8
Anti-Ice Adjustments
LEVEL OFF WEIGHT ADJUSTMENT (1000 KG)
ANTI-ICE
PRESSURE ALTITUDE (1000 FT)
CONFIGURATION
10
12
14
16
18
20
22
24
26
28
30
ENGINE ONLY
-2.9
-2.5
-1.7
-1.6
-1.5
-1.4
-1.3
-1.2
-1.1
ENGINE AND WING
-5.3
-7.8
-6.4
-6.6
-6.3
-5.8
-5.5
-5.1
-4.7
-4.4
PD.31.7
Performance Dispatch
Enroute
FAA
Category C Brakes
Boeing 737 Operations Manual
ALL ENGINES
Long Range Cruise Critical Fuel Reserves
Ground to Air Miles Conversion
AIR DISTANCE (NM)
GROUND
AIR DISTANCE (NM)
HEADWIND COMPONENT (KTS)
DISTANCE
TAILWIND COMPONENT (KTS)
100
80
60
40
20
(NM)
20
40
60
80
100
287
264
245
228
213
200
189
178
169
161
153
585
535
494
458
427
400
376
355
336
319
304
882
806
742
688
641
600
564
532
503
478
455
1180
1077
991
918
855
800
752
709
671
636
605
1477
1348
1240
1148
1069
1000
939
886
838
795
756
1774
1619
1489
1379
1283
1200
1127
1062
1005
953
907
2072
1890
1738
1609
1497
1400
1315
1239
1172
1112
1057
2369
2161
1987
1839
1711
1600
1502
1416
1339
1270
1208
2667
2432
2236
2069
1925
1800
1690
1593
1506
1429
1358
Critical Fuel (1000 KG)
AIR DIST
WEIGHT AT CRITICAL POINT (1000 KG)
(NM)
45
50
55
60
65
70
75
80
85
200
1.8
1.9
2.0
2.1
2.1
2.2
2.3
2.4
2.4
300
2.6
2.7
2.8
2.9
3.0
3.1
3.2
3.3
3.4
400
3.4
3.5
3.6
3.7
3.9
4.0
4.1
4.3
4.4
500
4.1
4.3
4.4
4.6
4.7
4.9
5.0
5.2
5.4
600
4.9
5.1
5.2
5.4
5.6
5.8
6.0
6.2
6.3
700
5.6
5.8
6.0
6.2
6.4
6.6
6.8
7.1
7.3
800
6.4
6.6
6.8
7.0
7.3
7.5
7.7
8.0
8.2
900
7.2
7.4
7.6
7.9
8.1
8.4
8.6
8.9
9.2
1000
7.9
8.1
8.4
8.7
8.9
9.2
9.5
9.8
10.1
1100
8.7
8.9
9.2
9.5
9.8
10.1
10.4
10.7
11.1
1200
9.4
9.6
10.0
10.3
10.6
10.9
11.3
11.6
12.0
1300
10.2
10.4
10.7
11.1
11.4
11.8
12.1
12.5
12.9
1400
10.9
11.1
11.5
11.9
12.2
12.6
13.0
13.4
13.8
1500
11.7
11.9
12.3
12.7
13.1
13.5
13.9
14.3
14.7
1600
12.5
12.7
13.0
13.4
13.9
14.3
14.7
15.2
15.7
1700
13.2
13.4
13.8
14.2
14.7
15.1
15.6
16.1
16.6
1800
14.0
14.2
14.5
15.0
15.5
16.0
16.4
16.9
17.5
Based on: Emergency descent to 10000 ft. Level cruise at 10000 ft. 250 KIAS descent to 1500 ft. 15 minutes
hold at 1500 ft. One missed approach; approach and land. 5% allowance for wind errors.
Increase fuel required 0.5% for each 10°C hotter than ISA conditions.
If icing conditions exist, increase fuel by 15% to account for engine and wing anti-ice on and ice accumulation
on unheated surfaces.
Allowance for performance deterioration not included.
Compare the fuel required from this chart with critical fuel reserves for one engine inoperative.
Use the higher of the two.
PD.31.8
Performance Dispatch
FAA
Enroute
Category C Brakes
Boeing 737 Operations Manual
ENGINE INOP
Long Range Cruise Critical Fuel Reserves
Ground to Air Miles Conversion
AIR DISTANCE (NM)
GROUND
AIR DISTANCE (NM)
HEADWIND COMPONENT (KTS)
DISTANCE
TAILWIND COMPONENT (KTS)
100
80
60
40
20
(NM)
20
40
60
80
100
292
267
246
229
213
200
188
178
168
160
152
595
542
498
460
428
400
375
354
334
317
301
898
817
749
692
643
600
563
530
500
474
451
1201
1092
1000
923
857
800
750
706
666
631
600
1504
1366
1252
1155
1072
1000
937
882
833
789
749
1808
1641
1503
1386
1286
1200
1124
1058
999
946
898
2111
1916
1754
1618
1501
1400
1312
1234
1165
1103
1047
2414
2191
2006
1849
1716
1600
1499
1410
1331
1260
1197
2717
2466
2257
2081
1930
1800
1686
1586
1497
1417
1346
Critical Fuel (1000 KG)
AIR DIST
WEIGHT AT CRITICAL POINT (1000 KG)
(NM)
45
50
55
60
65
70
75
80
85
200
1.7
1.7
1.8
1.9
2.0
2.1
2.1
2.2
2.3
300
2.3
2.4
2.5
2.7
2.8
2.9
3.0
3.1
3.2
400
3.0
3.1
3.3
3.4
3.6
3.7
3.8
4.0
4.1
500
3.7
3.8
4.0
4.2
4.4
4.5
4.7
4.9
5.1
600
4.3
4.5
4.7
4.9
5.1
5.4
5.6
5.8
6.0
700
5.0
5.2
5.5
5.7
5.9
6.2
6.4
6.6
6.9
800
5.7
5.9
6.2
6.4
6.7
7.0
7.2
7.5
7.8
900
6.4
6.6
6.9
7.2
7.5
7.8
8.1
8.4
8.7
1000
7.0
7.3
7.6
7.9
8.2
8.6
8.9
9.2
9.6
1100
7.7
7.9
8.3
8.6
9.0
9.4
9.7
10.1
10.4
1200
8.4
8.6
9.0
9.4
9.8
10.2
10.5
10.9
11.3
1300
9.0
9.3
9.7
10.1
10.5
10.9
11.4
11.8
12.2
1400
9.7
10.0
10.4
10.8
11.3
11.7
12.2
12.6
13.0
1500
10.4
10.6
11.1
11.5
12.0
12.5
12.9
13.4
13.9
1600
11.1
11.3
11.7
12.2
12.7
13.2
13.7
14.3
14.8
1700
11.7
12.0
12.4
12.9
13.5
14.0
14.5
15.1
15.6
1800
12.4
12.6
13.1
13.6
14.2
14.8
15.3
15.9
16.5
Based on: Emergency descent to 10000 ft. Level cruise at 10000 ft. 250 KIAS descent to 1500 ft. 15 minutes
hold at 1500 ft. One missed approach; approach and land. 5% allowance for wind errors.
Increase fuel required 0.5% for each 10°C hotter than ISA conditions.
If icing conditions exist, increase fuel by 15% to account for engine and wing anti-ice on and ice accumulation
on unheated surfaces.
Allowance for performance deterioration not included.
Compare the fuel required from this chart with critical fuel reserves for all engines operative.
Use the higher of the two.
PD.31.9
Performance Dispatch
Enroute
FAA
Category C Brakes
Boeing 737 Operations Manual
Intentionally
Blank
PD.31.10
FAA
Category C Brakes
Boeing 737 Operations Manual
Performance Dispatch
Chapter PD
Landing
Section 32
Landing
Landing Field Limit Weight
Flaps 40
Wind Corrected Field Length (M)
FIELD LENGTH
WIND COMPONENT (KTS)
AVAILABLE
(M)
-15
-10
-5
0
10
20
30
40
1000
810
900
1000
1060
1130
1200
1270
1200
900
1000
1100
1200
1270
1340
1420
1500
1400
1080
1180
1290
1400
1470
1560
1640
1720
1600
1250
1360
1480
1600
1680
1770
1850
1940
1800
1430
1550
1670
1800
1890
1980
2070
2170
2000
1610
1730
1860
2000
2090
2190
2290
2390
2200
1790
1920
2050
2200
2300
2400
2510
2620
2400
1970
2100
2250
2400
2510
2610
2720
2600
2140
2290
2440
2600
2720
2800
2320
2470
2630
2800
3000
2500
2650
3200
2680
Field Limit Weight (1000 KG)
WIND CORR’D
AIRPORT PRESSURE ALTITUDE (FT)
FIELD LENGTH
0
2000
4000
6000
8000
10000
(M)
DRY
WET
DRY
WET
DRY
WET
DRY
WET
DRY
WET
DRY
WET
1000
36.0
1200
46.0
38.2
43.4
36.0
40.9
38.5
36.2
1400
55.7
46.9
52.9
44.2
49.9
41.7
47.1
39.2
44.3
36.9
41.6
1600
63.7
55.4
60.8
52.5
58.1
49.5
55.4
46.7
52.4
43.9
49.3
41.3
1800
72.3
62.3
68.7
59.5
65.2
56.8
62.2
54.1
59.3
51.0
56.5
48.0
2000
81.3
69.6
77.1
66.1
73.2
63.0
69.4
60.2
65.8
57.4
62.6
54.7
2200
88.5
77.4
85.3
73.4
81.2
69.7
77.0
66.1
72.9
62.9
69.0
60.0
2400
85.0
80.8
87.8
76.7
84.5
72.7
80.1
68.8
75.7
65.2
2600
90.4
87.1
83.7
89.8
79.3
85.6
75.1
81.7
71.0
2800
88.8
85.5
88.4
81.3
84.8
76.8
3000
90.1
85.7
87.1
81.8
3200
88.2
89.4
84.6
3400
90.6
86.6
3600
88.6
3800
90.6
Decrease field limit weight 4300 kg when using manual speedbrakes.
PD.32.1
Performance Dispatch
Landing
FAA
Category C Brakes
Boeing 737 Operations Manual
Landing
Landing Climb Limit Weight
Valid for approach with Flaps 15 and landing with Flaps 30 or 40
Based on engine bleed for packs on and anti-ice off
LANDING CLIMB LIMIT WEIGHT (1000 KG)
AIRPORT OAT
AIRPORT PRESSURE ALTITUDE (FT)
°C
°F
0
2000
4000
6000
8000
10000
50
122
66.4
61.4
48
118
67.8
62.9
46
115
69.0
64.4
59.4
44
111
70.2
65.6
60.8
42
108
71.5
66.8
62.2
57.1
40
104
72.7
68.0
63.4
58.4
38
100
74.0
69.1
64.5
59.7
54.4
36
97
75.3
70.4
65.7
60.8
55.3
34
93
76.7
71.7
66.9
61.9
56.3
51.5
32
90
78.1
72.9
68.0
62.9
57.3
52.7
30
86
79.4
74.0
68.8
63.8
58.3
53.7
28
82
79.5
75.0
69.6
64.6
59.2
54.5
26
79
79.5
75.9
70.3
65.2
60.1
55.5
24
75
79.6
75.9
70.9
65.7
60.9
56.0
22
72
79.7
76.0
71.4
66.1
61.3
56.6
20
68
79.7
76.0
71.4
66.7
61.7
57.1
18
64
79.8
76.1
71.5
67.1
62.1
57.3
16
61
79.9
76.1
71.5
67.1
62.5
57.8
14
57
79.9
76.2
71.6
67.2
62.9
58.1
12
54
80.0
76.2
71.6
67.2
62.9
58.4
10
50
80.0
76.3
71.6
67.2
62.9
58.8
-40
-40
80.6
76.8
72.1
67.7
63.3
59.3
With engine bleeds for packs off, increase weight by 1200 kg.
With engine anti-ice on, decrease weight by 300 kg.
With engine and wing anti-ice on, decrease weight by 1400 kg.
When operating in icing conditions during any part of the flight when forecast landing temperature is below
10°C, decrease weight by 5500 kg.
PD.32.2
Performance Dispatch
FAA
Landing
Category C Brakes
Boeing 737 Operations Manual
Quick Turnaround Limit Weight
Flaps 40
LIMIT WEIGHT (1000 KG)
AIRPORT OAT
AIRPORT PRESSURE ALTITUDE (FT)
°C
°F
0
1000
2000
3000
50
122
80.2
78.7
77.2
40
104
81.6
80.1
78.5
77.0
30
86
83.1
81.5
79.9
78.3
20
68
84.6
83.0
81.4
79.8
10
50
86.2
84.5
82.9
81.3
0
32
86.2
86.1
84.5
82.8
-10
14
86.2
86.2
86.2
84.5
-20
-4
86.2
86.2
86.2
86.1
-30
-22
86.2
86.2
86.2
86.2
-40
-40
86.2
86.2
86.2
86.2
Increase weight by 750 kg per 1% uphill slope. Decrease weight by 1200 kg per 1% downhill slope.
Increase weight by 1750 kg per 10 knots headwind. Decrease weight by 7750 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 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.
PD.32.3
Performance Dispatch
Landing
FAA
Category C Brakes
Boeing 737 Operations Manual
Intentionally
Blank
PD.32.4
FAA
Category C Brakes
Boeing 737 Operations Manual
Performance Dispatch
Chapter PD
Text
Section 33
Text
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.
PD.33.1
Performance Dispatch
Text
FAA
Category C Brakes
Boeing 737 Operations Manual
Obstacle Limit Weight
The Reference Obstacle Limit Weight table provides obstacle limit
weights for reference airport conditions based on obstacle height above the
runway surface and distance from brake release. Enter the adjustment
tables to adjust the reference Obstacle Limit Weight for the effects of
OAT, pressure altitude and wind as indicated. In the case of multiple
obstacles, enter the tables successively with each obstacle and determine
the most limiting weight.
Enroute
Long Range Cruise Maximum Operating Altitude
These tables provide the maximum operating altitude in the same manner
as the FMC. Maximum altitudes are shown for a given cruise weight and
maneuver capability. Note that this table considers both thrust and buffet
limits, providing the more limiting of the two. Any data that is thrust
limited is denoted by an asterisk and represents only a thrust limited
condition in level flight with 100 ft/min residual rate of climb. Flying
above these altitudes with sustained banks in excess of approximately 15°
may cause the airplane to lose speed and/or altitude. The altitudes shown
in the table are limited to the maximum certified altitude of 41000 ft.
Long Range Cruise Trip Fuel and Time
Long Range Cruise Trip Fuel and Time tables are provided to determine
trip time and fuel required to destination.
To determine trip fuel and time for a constant altitude cruise, first enter the
Ground to Air Miles Conversion table to convert ground distance and
enroute wind to an equivalent still air distance for use with the Reference
Fuel and Time tables. Next, enter the Reference Fuel and Time table with
air distance from the Ground to Air Miles Conversion table and the desired
altitude and read Reference Fuel and Time Required. Lastly, enter the Fuel
Required Adjustment table with the Reference Fuel and the planned
landing weight to obtain the adjustment to the fuel required at the planned
landing weight.
Long Range Cruise Step Climb Trip Fuel and Time
The Long Range Cruise Step Climb Trip Fuel and Time tables are provided
to determine trip time and fuel required to destination when flying a step
climb profile. Step climb profiles are based on 4000 ft step climbs to keep
the flight within 2000 ft of the optimum altitude for the current cruise
weight. To determine trip fuel and time, enter the Ground to Air Miles
PD.33.2
Performance Dispatch
FAA
Text
Category C Brakes
Boeing 737 Operations Manual
Conversion table and determine air distance as discussed above. Then
enter the Trip Fuel and Time Required table with air distance and planned
landing weight to read trip fuel. Continue across the table to read trip time.
Short Trip Fuel and Time
These tables are provided to determine trip fuel and time for short
distances or alternates. Obtain air distance from the table using the ground
distance and wind component to the alternate. Enter the Trip Fuel and Time
Required table with air distance and read trip fuel required for the expected
landing weight, together with time to alternate at right. For distances
greater than shown or other altitudes, use the Long Range Cruise Trip Fuel
and Time tables.
Holding Planning
This table provides total fuel flow information necessary for planning flaps
up holding and reserve fuel requirements. Data is based on the FMC
holding speed schedule which is the higher of the maximum endurance and
flaps up maneuver speeds. As noted, the fuel flow is based on flight in a
racetrack holding pattern. For holding in straight and level flight, reduce
table values by 5%.
Crew Oxygen Requirements
Tables are provided to determine the minimum dispatch oxygen pressure
for protective breathing equipment used by the flight crew. Enter the
number of crew plus observers using oxygen and read the minimum
cylinder pressure required for the appropriate bottle temperature and size.
These pressures provide sufficient oxygen for 15 minutes of protective
breathing for each flight crew member plus 10% contingency at 8000 ft
cabin pressure altitude. Route specific analysis is necessary to determine
if additional oxygen pressure is needed to meet supplemental oxygen
requirements.
Net Level Off Weight
The Net Level Off Weight table is provided to determine terrain clearance
capability in straight and level flight following an engine failure.
Regulations require terrain clearance planning based on net performance
which is the gross (or actual) gradient performance degraded by 1.1%. In
addition, the net level off pressure altitude must clear the terrain by
1000 ft.
To determine the maximum weight for terrain clearance, enter the table
with required net level off pressure altitude and expected ISA deviation to
obtain weight. Adjust weight for anti-ice operation as noted below the
table.
PD.33.3
Performance Dispatch
Text
FAA
Category C Brakes
Boeing 737 Operations Manual
Extended Range Operations
Regulations require that flights conducted over a route that contains a
point further than one hour’s time at
“normal one engine inoperative
speed” from an adequate diversion airport comply with rules set up
specifically for “Extended Range Operation with Two Engine airplanes.”
This section provides reserve fuel planning information for the "Critical
Fuel Scenario" based on two engine operation at Long Range Cruise as
well as single engine operation at Long Range Cruise.
Long Range Cruise Critical Fuel Reserves
Enter the Ground to Air Miles Conversion table with forecast wind and
ground distance to diversion airport from critical point to obtain air
distance. Now enter the Critical Fuel table with air distance and expected
weight at the critical point and read required fuel. Apply the noted fuel
adjustments as necessary. Regulations require a
5% allowance for
performance deterioration unless a value has been established by the
operator for inservice deterioration.
As noted below each table, the fuel required is the greater of the two engine
fuel and the single engine fuel. This fuel is compared to the amount of fuel
normally onboard the airplane at that point in the route. If the fuel required
by the critical fuel reserves exceeds the amount of fuel normally expected,
the fuel load must be adjusted accordingly.
Landing
Tables are provided for determining the maximum landing weight as
limited by field length or climb requirements for a single landing flap.
Maximum landing weight is the lowest of the field length limit weight,
climb limit weight, or maximum certified landing weight.
Landing Field Limit Weight
Obtain wind corrected field length by entering the Wind Corrected Field
Length table with field length available and wind component along the
runway. Now enter the Field Limit Weight table with wind corrected field
length and pressure altitude to read field limit weight for the expected
runway condition.
Landing Climb Limit Weight
Enter the table with airport OAT and pressure altitude to read landing
climb limit weight. Apply the noted adjustments as required.
PD.33.4
Performance Dispatch
FAA
Text
Category C Brakes
Boeing 737 Operations Manual
Quick Turnaround Limit Weight
Enter the table with airport pressure altitude and OAT to read maximum
quick turnaround weight. Apply the noted adjustments as required.
If the landing weight exceeds the maximum quick turnaround weight, wait
the specified time and then check that the wheel thermal plugs have not
melted before executing a subsequent takeoff, or ensure the brake
temperature is within limits using the alternate procedure described on the
page.
PD.33.5
Performance Dispatch
Text
FAA
Category C Brakes
Boeing 737 Operations Manual
Intentionally
Blank
PD.33.6
FAA
Category G Brakes
Boeing 737 Operations Manual
Performance Dispatch
Chapter PD
Takeoff
Section 40
Takeoff
Takeoff Field Corrections -ff
Dry Runway
Slope Corrections
FIELD LENGTH
SLOPE CORRECTED FIELD LENGTH (FT)
AVAILABLE
RUNWAY SLOPE (%)
(FT)
-2.0
-1.5
-1.0
-0.5
0.0
0.5
1.0
1.5
2.0
4200
4280
4260
4240
4220
4200
4150
4100
4050
4000
4600
4710
4680
4650
4630
4600
4520
4450
4370
4300
5000
5130
5100
5070
5030
5000
4900
4800
4700
4600
5400
5560
5520
5480
5440
5400
5270
5150
5020
4900
5800
5990
5940
5890
5850
5800
5650
5500
5350
5200
6200
6420
6370
6310
6260
6200
6030
5850
5680
5500
6600
6870
6800
6730
6670
6600
6400
6200
6000
5800
7000
7310
7230
7160
7080
7000
6780
6550
6330
6100
7400
7760
7670
7580
7490
7400
7150
6900
6650
6400
7800
8200
8100
8000
7900
7800
7530
7250
6980
6700
8200
8650
8540
8420
8310
8200
7900
7600
7300
7000
8600
9090
8970
8850
8720
8600
8280
7950
7630
7300
9000
9540
9400
9270
9130
9000
8650
8300
7950
7600
9400
9980
9840
9690
9550
9400
9030
8650
8280
7900
9800
10430
10270
10110
9960
9800
9400
9000
8600
8200
10200
10890
10710
10540
10370
10200
9780
9350
8930
8500
10600
11360
11170
10980
10790
10600
10150
9700
9250
8810
11000
11830
11620
11420
11210
11000
10530
10050
9580
9110
11400
12300
12080
11850
11630
11400
10900
10400
9900
9410
11800
12770
12530
12290
12040
11800
11280
10750
10230
9710
Wind Corrections
SLOPE CORR'D
SLOPE & WIND CORRECTED FIELD LENGTH (FT)
FIELD LENGTH
WIND COMPONENT (KTS)
(FT)
-15
-10
-5
0
10
20
30
40
4200
3130
3490
3840
4200
4430
4670
4900
5140
4600
3460
3840
4220
4600
4840
5090
5340
5590
5000
3800
4200
4600
5000
5250
5510
5770
6040
5400
4130
4550
4980
5400
5670
5930
6210
6480
5800
4470
4910
5360
5800
6080
6360
6640
6930
6200
4800
5270
5730
6200
6490
6780
7080
7380
6600
5130
5620
6110
6600
6900
7200
7510
7820
7000
5470
5980
6490
7000
7310
7630
7950
8270
7400
5800
6340
6870
7400
7720
8050
8380
8720
7800
6140
6690
7250
7800
8130
8470
8820
9160
8200
6470
7050
7620
8200
8540
8890
9250
9610
8600
6810
7400
8000
8600
8960
9320
9680
10060
9000
7140
7760
8380
9000
9370
9740
10120
10500
9400
7470
8120
8760
9400
9780
10160
10550
10950
9800
7810
8470
9140
9800
10190
10590
10990
11400
10200
8140
8830
9510
10200
10600
11010
11420
11850
10600
8480
9180
9890
10600
11010
11430
11860
12290
11000
8810
9540
10270
11000
11420
11850
12290
12740
11400
9140
9900
10650
11400
11830
12280
12730
13190
11800
9480
10250
11030
11800
12250
12700
13160
13630
PD.40.1
Performance Dispatch
Takeoff
FAA
Category G Brakes
Boeing 737 Operations Manual
Takeoff
Takeoff Field & Climb Limit Weights - Dry Runway
Flaps 5
Sea Level Pressure Altitude
FIELD LIMIT WEIGHT (1000 LB)
CORR'D FIELD
OAT (°C)
LENGTH (FT)
-40
0
11
14
18
22
26
30
35
40
50
4000
123.5
115.5
113.4
112.8
112.0
111.2
110.5
109.7
106.5
103.4
97.1
4200
127.2
119.0
116.8
116.2
115.4
114.6
113.8
113.0
109.8
106.5
100.0
4600
134.4
125.8
123.4
122.8
122.0
121.1
120.3
119.5
116.1
112.7
105.9
5000
141.2
132.2
129.7
129.1
128.2
127.4
126.5
125.7
122.1
118.5
111.4
5400
147.6
138.2
135.6
135.0
134.1
133.2
132.3
131.4
127.6
123.9
116.5
5800
153.8
144.0
141.3
140.6
139.7
138.7
137.8
136.9
133.0
129.1
121.4
6200
159.7
149.5
146.8
146.0
145.0
144.1
143.1
142.1
138.1
134.1
126.0
6600
165.4
154.9
152.0
151.2
150.2
149.2
148.2
147.2
143.0
138.8
130.5
7000
170.9
160.0
157.0
156.2
155.2
154.1
153.1
152.1
147.7
143.4
134.8
7400
176.2
165.0
161.9
161.1
160.0
158.9
157.9
156.8
152.3
147.9
139.0
7800
181.3
169.7
166.5
165.7
164.6
163.5
162.4
161.3
156.7
152.1
142.9
8200
186.2
174.3
171.1
170.2
169.1
167.9
166.8
165.7
160.9
156.3
146.9
8600
189.9
178.7
175.4
174.5
173.3
172.2
171.1
169.9
165.0
160.3
150.6
9000
189.9
182.8
179.4
178.4
177.2
176.1
174.9
173.7
168.8
163.9
154.0
9400
189.9
186.3
182.9
181.9
180.7
179.5
178.3
177.1
172.1
167.1
157.0
9800
189.9
189.7
186.2
185.3
184.0
182.8
181.6
180.3
175.2
170.1
159.8
10200
189.9
189.9
189.3
188.3
187.1
185.8
184.6
183.3
178.1
172.9
162.4
10600
189.9
189.9
189.9
189.9
189.9
188.7
187.4
186.2
180.8
175.6
165.0
CLIMB LIMIT
188.1
187.4
186.8
186.6
186.4
186.1
185.8
185.4
177.7
170.3
155.9
WT (1000 LB)
2000 FT Pressure Altitude
FIELD LIMIT WEIGHT (1000 LB)
CORR'D FIELD
OAT (°C)
LENGTH (FT)
-40
0
11
14
18
22
26
30
35
40
50
4000
116.9
108.9
106.9
106.3
105.6
104.9
104.3
102.4
99.5
96.4
90.4
4200
120.4
112.2
110.1
109.6
108.8
108.1
107.4
105.5
102.5
99.4
93.2
4600
127.2
118.6
116.5
115.9
115.1
114.4
113.6
111.6
108.5
105.2
98.7
5000
133.7
124.7
122.5
121.9
121.1
120.3
119.5
117.4
114.1
110.6
103.9
5400
139.8
130.4
128.0
127.4
126.6
125.8
124.9
122.8
119.3
115.7
108.6
5800
145.6
135.9
133.4
132.8
131.9
131.0
130.2
127.9
124.4
120.6
113.2
6200
151.2
141.1
138.5
137.8
136.9
136.1
135.2
132.8
129.1
125.2
117.5
6600
156.6
146.1
143.4
142.7
141.8
140.9
140.0
137.5
133.7
129.6
121.7
7000
161.8
150.9
148.2
147.4
146.5
145.5
144.6
142.1
138.1
133.9
125.7
7400
166.8
155.6
152.8
152.0
151.0
150.1
149.1
146.5
142.4
138.0
129.5
7800
171.6
160.1
157.2
156.4
155.4
154.3
153.3
150.7
146.4
142.0
133.3
8200
176.3
164.5
161.5
160.7
159.6
158.6
157.5
154.8
150.5
145.9
136.9
8600
180.8
168.7
165.6
164.8
163.7
162.6
161.6
158.7
154.3
149.6
140.4
9000
184.8
172.4
169.3
168.4
167.3
166.3
165.2
162.3
157.8
153.0
143.6
9400
188.5
175.8
172.6
171.7
170.6
169.5
168.4
165.5
160.8
155.9
146.4
9800
189.9
179.0
175.7
174.9
173.7
172.6
171.5
168.5
163.7
158.7
149.0
10200
189.9
182.0
178.6
177.8
176.6
175.4
174.3
171.2
166.5
161.4
151.4
10600
189.9
184.8
181.4
180.5
179.3
178.1
177.0
173.9
169.0
163.9
153.8
CLIMB LIMIT
179.3
178.6
178.1
178.0
177.8
177.6
177.3
173.1
166.2
159.2
145.8
WT (1000 LB)
With engine bleed for packs off, increase field limit weight by 800 lb and climb limit weight by 3100 lb.
With engine anti-ice on, decrease field limit weight by 500 lb and climb limit weight by 600 lb.
With engine and wing anti-ice on (optional system), decrease field limit weight by 1900 lb and climb limit
weight by 3200 lb.
PD.40.2
Performance Dispatch
FAA
Takeoff
Category G Brakes
Boeing 737 Operations Manual
Takeoff
Takeoff Field & Climb Limit Weights - Dry Runway
Flaps 5
4000 FT Pressure Altitude
FIELD LIMIT WEIGHT (1000 LB)
CORR'D FIELD
OAT (°C)
LENGTH (FT)
-40
0
11
14
18
22
26
30
35
40
50
4000
109.4
101.9
100.0
99.5
98.8
98.1
96.7
95.1
92.5
89.5
84.3
4200
112.7
105.0
103.1
102.6
101.8
101.1
99.7
98.0
95.3
92.3
86.9
4600
119.2
111.1
109.1
108.5
107.8
107.0
105.5
103.8
101.0
97.8
92.1
5000
125.3
116.9
114.7
114.1
113.4
112.6
111.0
109.2
106.2
102.9
97.0
5400
131.0
122.2
120.0
119.4
118.6
117.7
116.1
114.2
111.1
107.7
101.5
5800
136.5
127.3
125.0
124.4
123.5
122.7
121.0
119.0
115.8
112.2
105.7
6200
141.7
132.2
129.8
129.1
128.3
127.4
125.6
123.5
120.2
116.5
109.8
6600
146.8
136.9
134.4
133.7
132.8
131.9
130.0
127.9
124.4
120.6
113.6
7000
151.6
141.4
138.8
138.1
137.2
136.2
134.3
132.1
128.5
124.5
117.3
7400
156.3
145.8
143.1
142.4
141.4
140.5
138.5
136.2
132.5
128.4
121.0
7800
160.8
150.0
147.2
146.5
145.5
144.5
142.5
140.1
136.3
132.1
124.4
8200
165.2
154.1
151.3
150.5
149.5
148.4
146.4
143.9
140.1
135.7
127.9
8600
169.4
158.0
155.1
154.3
153.3
152.2
150.1
147.6
143.7
139.2
131.2
9000
173.2
161.6
158.6
157.8
156.7
155.7
153.5
150.9
146.9
142.3
134.1
9400
176.6
164.7
161.7
160.9
159.8
158.7
156.5
153.9
149.7
145.1
136.7
9800
179.8
167.7
164.6
163.8
162.7
161.5
159.3
156.6
152.4
147.7
139.1
10200
182.8
170.5
167.3
166.5
165.3
164.2
161.9
159.2
154.9
150.1
141.4
10600
185.6
173.1
169.9
169.1
167.9
166.8
164.4
161.7
157.3
152.4
143.6
CLIMB LIMIT
168.6
167.9
167.5
167.4
167.2
167.0
164.5
161.0
155.2
148.5
136.5
WT (1000 LB)
6000 FT Pressure Altitude
FIELD LIMIT WEIGHT (1000 LB)
CORR'D FIELD
OAT (°C)
LENGTH (FT)
-40
0
11
14
18
22
26
30
35
40
50
4000
102.2
95.0
93.1
92.7
92.0
90.8
89.5
88.0
85.6
83.0
78.1
4200
105.3
97.9
96.0
95.5
94.9
93.6
92.3
90.8
88.3
85.6
80.6
4600
111.4
103.7
101.7
101.2
100.5
99.1
97.8
96.1
93.6
90.7
85.5
5000
117.1
109.1
107.0
106.4
105.7
104.3
102.9
101.2
98.5
95.5
90.1
5400
122.5
114.1
111.9
111.3
110.6
109.1
107.6
105.9
103.1
100.0
94.2
5800
127.6
118.9
116.6
116.0
115.2
113.7
112.2
110.3
107.4
104.2
98.2
6200
132.5
123.4
121.1
120.4
119.6
118.1
116.4
114.5
111.5
108.1
101.9
6600
137.2
127.7
125.3
124.7
123.8
122.2
120.5
118.5
115.4
111.9
105.5
7000
141.7
132.0
129.4
128.8
127.9
126.2
124.5
122.4
119.2
115.6
108.9
7400
146.1
136.1
133.5
132.8
131.9
130.1
128.4
126.2
122.9
119.1
112.3
7800
150.3
139.9
137.3
136.6
135.6
133.9
132.0
129.8
126.4
122.6
115.5
8200
154.4
143.8
141.1
140.3
139.4
137.6
135.7
133.4
129.9
125.9
118.7
8600
158.4
147.5
144.7
143.9
143.0
141.1
139.1
136.8
133.2
129.2
121.8
9000
161.9
150.8
147.9
147.2
146.2
144.3
142.3
139.9
136.2
132.1
124.5
9400
165.1
153.7
150.8
150.0
149.0
147.0
145.0
142.6
138.8
134.6
126.9
9800
168.1
156.5
153.5
152.7
151.7
149.7
147.6
145.2
141.3
137.0
129.2
10200
170.9
159.1
156.0
155.2
154.2
152.1
150.0
147.5
143.6
139.3
131.3
10600
173.5
161.5
158.4
157.6
156.5
154.5
152.4
149.8
145.9
141.4
133.3
CLIMB LIMIT
158.1
157.5
157.2
157.1
156.9
154.8
152.5
149.3
143.6
137.3
126.7
WT (1000 LB)
With engine bleed for packs off, increase field limit weight by 800 lb and climb limit weight by 3100 lb.
With engine anti-ice on, decrease field limit weight by 500 lb and climb limit weight by 600 lb.
With engine and wing anti-ice on (optional system), decrease field limit weight by 1900 lb and climb limit
weight by 3200 lb.
PD.40.3