TM 1-1510-218-10
7A-52
MAXIMUM CRUISE POWER
1700 RPM
ISA 10 C
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.
AIRSPEED ~ KNOTS
PRESSURE
ALT
IOAT
OAT
TORQUE
PER
ENGINE
TOTAL
FUEL
FLOW
13,000 LB
12,000 LB
11,000 LB
10,000 LB
FEET
C
C
%
LB/HR
IAS
TAS
IAS
TAS
IAS
TAS
IAS
TAS
SL
10
5
100
940
236
233
237
234
238
235
239
236
2000
6
1
100
914
234
238
235
239
236
240
237
240
4000
3
-3
100
888
232
242
233
243
234
244
235
245
6000
-1
-7
100
862
229
247
231
248
232
249
232
250
8000
-5
-11
100
840
227
251
228
253
229
254
230
255
10,000
-9
-15
100
818
225
256
226
257
227
259
228
260
12,000
-12
-19
100
800
222
261
223
262
225
264
226
265
14,000
-16
-23
100
786
220
266
221
268
222
269
223
270
16,000
-20
-27
100
776
217
271
218
273
220
274
221
276
18,000
-24
-31
100
768
214
276
216
278
217
279
218
281
20,000
-27
-35
100
762
211
281
213
283
214
285
215
286
22,000
-31
-39
95
724
204
280
206
283
208
286
210
288
24,000
-35
-43
90
680
196
279
199
282
201
285
202
287
26,000
-40
-47
83
630
187
275
190
279
192
283
195
286
28,000
-44
-51
77
580
177
270
181
275
184
279
186
283
29,000
-46
-52
73
556
172
266
175
272
179
277
181
281
31,000
33,000
35,000
Figure 7A-48. Maximum Cruise Power, 1700 RPM, ISA 10 C