TM 1-1510-218-10
7-64
MAXIMUM CRUISE POWER
1900 RPM
ISA – 30 °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
-10
-15
100
1000
251
238
252
239
252
240
2,000
-14
-19
100
976
249
243
249
244
250
244
4,000
-17
-23
100
954
247
248
247
248
248
249
6,000
-21
-27
100
932
244
252
245
253
246
254
8,000
-25
-31
100
914
242
257
243
258
244
259
10,000
-28
-35
100
898
240
262
241
263
241
264
12,000
-32
-39
100
884
237
267
238
268
239
269
14,000
-36
-43
100
874
235
272
236
274
237
275
16,000
-40
-47
100
866
233
278
234
279
235
280
18,000
-43
-51
99
856
230
286
231
284
232
286
20,000
---
---
---
---
---
---
---
---
---
---
22,000
---
---
---
---
---
---
---
---
---
---
24,000
---
---
---
---
---
---
---
---
---
---
26,000
---
---
---
---
---
---
---
---
---
---
28,000
---
---
---
---
---
---
---
---
---
---
29,000
---
---
---
---
---
---
---
---
---
---
31,000
---
---
---
---
---
---
---
---
---
---
33,000
---
---
---
---
---
---
---
---
---
---
35,000
---
---
---
---
---
---
---
---
---
---
Figure 7-60. Maximum Cruise Power, 1900 RPM, ISA – 30 °C
