NOTES: IOAT, TORQUE, AND FUEL FLOW BASED ON 12,000 POUNDS.
TO OBTAIN FUEL FLOW PER ENGINE, DIVIDE THE TOTAL FUEL FLOW VALUE FOR THE
CORRESPONDING ALTITUDE BY TWO.
PRESSURE
IOAT OAT
ALT
qC
qC
FEET
SL
58
52
2000
54
48
4000
50
44
6000
46
40
8000
43
36
10,000
39
32
12,000
35
28
14,000
31
24
16,000
27
20
18,000
23
16
20,000
19
12
22,000
15
8
24,000
11
4
26,000
7
0
28,000
3
-4
29,000
1
-5
31,000
-5
-9
33,000
-9
-13
35,000
– – – – – –
NORMAL CRUISE POWER
ISA + 37 qC
TORQUE
TOTAL
PER
FUEL
ENGINE
FLOW
%
LB/HR
100
1002
99
968
97
930
94
886
91
838
88
792
83
738
80
700
77
664
74
630
72
606
70
584
65
544
61
502
55
460
53
440
47
400
44
370
– – –
– – –
Figure 7A-65. Normal Cruise Power, 1800 RPM, ISA + 37
1800 RPM
AIRSPEED
13,000 LB
12,000 LB
IAS
TAS
IAS
234
250
236
231
254
232
227
257
228
222
259
224
217
260
218
211
262
213
204
261
206
198
262
200
192
262
194
186
263
189
181
265
184
176
266
179
167
262
171
156
254
162
142
240
151
130
223
143
– – –
– – –
125
– – –
– – –
– – –
– – –
– – –
– – –
TM 1-1510-218-10
~
KNOTS
11,000 LB
TAS
IAS
TAS
251
236
252
255
233
256
258
229
260
261
225
262
262
220
264
264
214
266
264
208
266
265
202
267
265
196
268
266
191
269
269
186
272
271
182
274
268
174
273
263
166
269
254
156
263
247
151
259
223
139
247
– – –
121
225
– – –
– – –
– – –
– – –
q
C
10,000 LB
IAS
TAS
237
253
236
257
231
261
226
263
221
265
215
267
209
268
203
269
198
270
193
272
188
275
184
278
177
277
169
274
160
270
156
267
146
260
134
249
– – –
7A-69
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