Beechcraft C-12C Operator And Technical Reference Manual page 768

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
31
2000
27
4000
23
6000
19
8000
16
10,000
12
12,000
8
14,000
4
16,000
0
18,000
-4 -11
20,000
-7 -15
22,000
-11 -19
24,000
-15 -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-66
NORMAL CRUISE POWER
TORQUE TOTAL
PER FUEL
ENGINE FLOW
qC
% LB/HR
25 100 990
21 100 962
17 100 936
13 100 910
9 100 886
5 100 862
1 100 840
-3 97 802
-7 92 756
88 714
84 682
80 648
75 606
69 560
63 514
61 494
55 454
50 414
46 380
Figure 7A-62. Normal Cruise Power, 1800 RPM, ISA + 10
1800 RPM
ISA + 10 qC
AIRSPEED
13,000 LB 12,000 LB
IAS TAS IAS
238 244 239
236 248 237
234 253 235
231 258 232
229 263 230
226 268 228
224 273 225
218 275 220
212 275 213
205 275 207
199 275 201
191 275 194
183 272 186
174 267 177
163 260 167
149 247 162
133 229 150
– – – – – – 135
– – – – – – – – –
~
KNOTS
11,000 LB 10,000 LB
TAS IAS TAS IAS
245 240 246 241
249 238 250 239
254 236 255 237
259 233 260 234
264 231 265 232
269 229 270 230
275 226 276 227
277 221 278 222
277 215 279 216
277 208 280 210
278 203 281 204
278 196 281 198
276 188 279 191
272 180 277 183
267 171 272 174
263 166 270 170
253 156 263 161
237 145 254 151
– – – 130 237 140
q
C
TAS
246
251
256
261
266
272
277
280
281
281
283
283
282
280
277
275
270
264
254