Beechcraft C-12C Operator And Technical Reference Manual page 743

NOTE: 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 -14 -21
20,000 -18 -25
22,000 -21 -29
24,000 -26 -33
26,000 -30 -37
28,000 -34 -41
29,000 -36 -42
31,000 -40 -46
33,000 -45 -50
35,000 – – – – – –
NORMAL 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
96 742
92 706
87 672
82 628
76 580
70 534
67 512
61 472
56 432 – – –
– – – – – – – – –
Figure 7A-37. Normal Cruise Power, 1700 RPM, ISA
ISA
AIRSPEED
13,000 LB 12,000 LB
IAS TAS IAS TAS
235 236 236 237
232 240 234 241
230 245 231 246
228 249 229 251
225 254 226 255
223 259 224 260
220 264 222 266
218 269 220 271
215 274 216 276
208 274 210 276
202 274 204 277
195 274 197 277
187 271 189 275
177 267 181 272
167 261 171 267
161 256 166 264
149 246 156 256
– – – 143 245
– – – – – – – – –
TM 1-1510-218-10
~
KNOTS
11,000 LB 10,000 LB
IAS TAS IAS TAS
237 238 238
235 242 235
232 247 233
230 252 231
228 257 228
225 262 226
223 267 224
221 272 222
218 277 219
212 279 213
206 279 207
199 280 201
192 278 194
183 276 186
175 272 177
170 269 173
160 264 164
150 155 155
– – – – – – – – – – – –
239
243
248
253
258
263
286
274
279
280
281
282
281
279
276
274
270
265
7A-41