Beechcraft C-12C Operator And Technical Reference Manual page 744

TM 1-1510-218-10
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
FEET
SL 30
2000 27
4000 23
6000 19
8000 15
10,000 12
12,000 8
14,000 4
16,000 0
18,000 -4 -11
20,000 -8 -15
22,000 -12 -19
24,000 -16 -23
26,000 -20 -27
28,000 -24 -31
29,000 -26 -32
31,000 -31 -36
33,000 -36 -40
35,000 -40 -44
7A-42
NORMAL CRUISE POWER
TORQUE TOTAL
PER FUEL
ENGINE FLOW
qC
% LB/HR
25 100 952
21 100 924
17 100 898
13 100 874
9 100 848
5 100 826
1 100 804
-3 100 790
-7 97 756
92 714
88 680
83 648
78 604
72 558
66 512
63 492
58 452
52 414
48 380
Figure 7A-38. Normal Cruise Power, 1700 RPM, ISA + 10
1700 RPM
ISA + 10 qC
AIRSPEED
13,000 LB 12,000 LB
IAS TAS IAS
233 238 234
231 243 232
229 247 230
226 252 227
224 257 225
221 262 222
219 267 220
216 272 217
210 273 212
203 273 205
197 273 199
189 271 192
181 268 184
171 263 175
160 256 165
154 251 160
139 234 149
– – – – – – 133
– – – – – – – – –
~
KNOTS
11,000 LB 10,000 LB
TAS IAS TAS IAS
239 235 240 236
244 233 145 234
249 231 250 232
253 228 255 229
258 226 259 227
263 224 265 225
269 221 270 222
273 219 275 220
275 213 277 215
275 207 277 208
276 201 278 202
275 194 278 196
273 186 276 189
269 178 273 180
263 169 269 172
259 164 266 167
251 154 260 158
234 143 251 149
– – – 128 233 138
q
C
TAS
241
246
251
256
261
266
271
276
279
279
281
281
280
277
274
271
267
261
251