Beechcraft C-12C Operator And Technical Reference Manual page 770

TM 1-1510-218-10
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
FEET
SL
51
2000
47
4000
43
6000
40
8000
36
10,000
32
12,000
28
14,000
24
16,000
20
18,000
16
20,000
12
22,000
8
24,000
4
26,000
0
28,000
-4 -11
29,000
-7 -12
31,000
-12 -16
33,000
-16 -20
35,000
-20 -24
7A-68
NORMAL CRUISE POWER
TORQUE TOTAL
PER FUEL
ENGINE FLOW
qC
% LB/HR
45 100 1000
41 100 972
37 100 944
33 100 916
29 96 868
25 92 818
21 88 766
17 84 724
13 81 686
9 77 652
5 75 626
1 73 602
-3 68 560
-7 63 516
58 474
55 454
50 414
45 384
41 352
Figure 7A-64. Normal Cruise Power, 1800 RPM, ISA + 30
1800 RPM
ISA + 30 qC
AIRSPEED
13,000 LB 12,000 LB
IAS TAS IAS
235 249 237
233 253 234
231 258 232
228 263 229
222 264 224
216 265 218
209 265 211
203 265 205
197 266 199
191 267 194
186 269 189
181 270 184
172 266 175
161 259 166
148 247 156
140 237 149
– – – – – – 134
– – – – – – – – –
– – – – – – – – –
~
KNOTS
11,000 LB 10,000 LB
TAS IAS TAS IAS
250 237 251 238
254 235 255 236
259 233 261 234
264 230 265 231
266 225 267 226
267 219 269 220
267 213 269 214
268 207 270 208
269 201 271 203
270 196 273 197
272 191 275 193
274 186 277 188
271 178 275 181
266 170 272 173
259 160 266 164
252 155 263 159
236 144 253 150
– – – 128 235 139
– – – – – – – – – 123
q
C
TAS
251
256
262
267
268
270
271
272
273
275
278
281
279
276
272
270
263
253
234