Beechcraft C-12C Operator And Technical Reference Manual page 680

TM 1-1510-218-10
NOTE: TO OBTAIN FUEL FLOW PER ENGINE, DIVIDE THE TOTAL FUEL FLOW VALUE FOR THE
CORRESPONDING ALTITUDE BY TWO.
PRESSURE IOAT OAT TORQUE
ALT
qC
FEET
SL 31
27
2,000
4,000 23
6,000 20
16
8,000
10,000 12
12,000 8
14,000 5
16,000 1
18,000 -3
20,000 -8
22,000 -12
24,000 -16
26,000 -20
-24
28,000
29,000 -29
31,000 -30
33,000 -35
35,000 -40
7-68
MAXIMUM CRUISE POWER
FUEL FLOW
PER TOTAL
ENGINE
qC
% LB/HR
25 100 1024
21 100
17 100
13 100
9 100
5 100
1 99
-3 93
-7 88
-11 82
-15 77
-18 72
-22 66
-26 61
-30 56
-32 54
-36 49
-40 45
-44 38
Figure 7-64. Maximum Cruise Power, 1900 RPM - ISA + 10
1900 RPM
ISA + 10 qC
@12,000 LB
IAS TAS
244 250
998 242 254
972 240 259
948 237 264
926 235 270
908 233 275
882 229 279
830 222 279
778 214 278
730 206 277
682 198 275
238 189 272
592 180 268
550 171 263
512 161 257
492 155 253
454 144 242
418 126 221
380 --- ---
AIRSPEED ~ KNOTS
@11,000 LB
IAS TAS
245 251
243 255
241 260
238 265
236 271
234 276
230 280
223 280
216 280
208 279
200 277
192 275
183 272
174 268
165 263
160 260
150 253
138 242
121 222
q
C
@10,000 LB
IAS TAS
246 251
244 256
241 261
239 266
237 272
235 277
231 282
224 282
217 281
209 281
202 280
194 278
186 275
177 272
169 269
164 266
155 261
147 254
133 243