TM 1-1510-224-10
MAXIMUM CRUISE POWER
1700 RPM
ISA +37°C
WEIGHT®
12,000 POUNDS
10,000 POUNDS
PRESSURE
ALTITUDE
IOAT
OAT
TORQUE
PER
ENGINE
FUEL
FLOW
PER
ENGINE
TOTAL
FUEL
FLOW
IAS
TAS
TORQUE
PER
ENGINE
FUEL
FLOW
PER
ENGINE
TOTAL
FUEL
FLOW
IAS
TAS
FEET
°C
°C
PERCENT
LBS/HR
LBS/HR
KTS
KTS
PERCENT
LBS/HR
LBS/HR
KTS
KTS
0
57
52
74
607
1214
217
232
74
607
1214
218
234
2000
53
48
72
577
1154
213
235
72
577
1154
215
237
4000
49
44
70
549
1098
209
238
70
549
1098
211
239
6000
45
40
68
522
1044
205
240
69
522
1044
206
242
8000
42
36
66
496
992
200
242
67
496
992
202
244
10,000
38
32
64
469
938
195
243
64
469
938
197
246
12,000
34
28
60
437
874
189
243
61
438
876
191
246
14,000
30
24
57
408
816
182
243
57
409
818
185
246
16,000
26
20
53
380
760
175
241
54
380
760
178
245
18,000
22
16
49
351
702
167
229
49
352
704
170
243
20,000
18
12
45
326
652
159
235
46
326
652
163
241
22,000
13
8
42
305
610
151
232
43
306
612
156
239
24,000
9
4
39
284
568
143
228
39
285
570
149
236
26,000
5
0
37
267
534
136
225
37
268
536
142
235
28,000
1
-3
35
254
508
129
222
35
255
510
137
235
29,000
-1
-5
34
247
494
125
221
34
249
498
134
235
31,000
-5
-9
32
231
462
116
212
32
233
466
127
232
33,000
-9
-13
- - -
- - -
- - -
- - -
- - -
29
215
430
118
224
35,000
-13
-17
- - -
- - -
- - -
- - -
- - -
26
196
392
106
212
BT05213
NOTE
During operations with ice vanes extended, torque will decrease approximately
12%, fuel flow will decrease approximately 8%, and true airspeed will be reduced
by approximately 15 knots.
Figure 7-47. Maximum Cruise Power at 1700 RPM - ISA +37°C (Sheet 2 of 2)
7-73