Beechcraft C-12C Operator And Technical Reference Manual page 755

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.
PRESSURE
IOAT OAT
ALT
qC qC
FEET
SL 20 15
2000 16 11
4000 13 7
6000 9 3
8000 5 -1
10,000 1 -5
12,000 -2 -9
14,000 -6 -13
16,000 -10 -17
18,000 -13 -21
20,000 -17 -25
22,000 -21 -29
24,000 -25 -33
26,000 -29 -37
28,000 -34 -41
29,000 -36 -42
31,000 -40 -46
33,000 -45 -50
35,000 – – – – – –
MAXIMUM CRUISE POWER
1700 RPM
TORQUE TOTAL
PER FUEL
ENGINE FLOW
% LB/HR
100 946
100 920
100 892
100 866
100 844
100 822
100 800
100 786
100 776
100 772
96 734
91 698
85 652
79 604
73 558
70 536
64 494
59 452
– – – – – –
Figure 7A-49. Maximum Cruise Power, 1700 RPM, ISA
ISA
AIRSPEED
13,000 LB 12,000 LB
IAS TAS IAS TAS
235 236 236
232 240 234
230 245 231
228 249 229
225 254 226
223 259 224
220 264 222
218 269 219
215 274 216
212 278 213
205 279 207
199 274 200
191 276 193
181 272 184
171 266 175
166 263 170
154 253 159
137 235 148
– – – – – – – – – – – –
TM 1-1510-218-10
~
KNOTS
11,000 LB 10,000 LB
IAS TAS IAS
237 237 238 238
241 235 242 235
246 232 247 233
251 230 252 231
255 228 257 228
260 225 262 226
266 223 267 224
271 221 272 222
276 218 277 219
281 215 282 217
281 209 283 210
281 202 284 204
280 195 283 197
277 187 280 189
272 178 277 181
269 173 275 176
262 164 270 167
253 154 262 158
– – – – – – – – –
TAS
239
243
248
253
258
263
286
274
279
284
285
286
286
284
281
279
275
270
– – –
7A-53