TM 1-1510-218-10
7-65
MAXIMUM CRUISE POWER
1900 RPM
ISA – 20 °C
NOTE:
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
FUEL FLOW
TOTAL
@12,000 LB
@11,000 LB
@10,000 LB
FEET
° C
° C
%
LB/HR
IAS
TAS
IAS
TAS
IAS
TAS
SL
0
-5
100
1006
249
241
250
242
251
243
2,000
-3
-9
100
980
247
246
248
247
249
247
4,000
-7
-13
100
956
245
251
246
252
246
252
6,000
-11
-17
100
934
242
255
243
256
244
257
8,000
-15
-21
100
918
240
260
241
261
242
262
10,000
-18
-25
100
900
238
265
239
266
240
267
12,000
-22
-29
100
886
235
271
236
272
237
273
14,000
-26
-33
100
878
233
276
234
277
235
278
16,000
-29
-37
100
870
231
282
232
283
233
284
18,000
-33
-41
95
826
224
282
225
284
226
285
20,000
-37
-45
88
766
215
280
217
282
218
284
22,000
-41
-48
82
716
207
278
209
280
210
282
24,000
-45
-52
76
664
198
275
200
278
202
280
26,000
---
---
---
---
---
---
---
---
---
---
28,000
---
---
---
---
---
---
---
---
---
---
29,000
---
---
---
---
---
---
---
---
---
---
31,000
---
---
---
---
---
---
---
---
---
---
33,000
---
---
---
---
---
---
---
---
---
---
35,000
---
---
---
---
---
---
---
---
---
---
Figure 7-61. Maximum Cruise Power, 1900 RPM, ISA – 20 °C
