Beechcraft C-12C Operator And Technical Reference Manual page 778

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
10
2000
6
4000
3
6000
-1
8000
-5 -11
10,000
-9 -15
12,000
-12 -19
14,000
-16 -23
16,000
-20 -27
18,000
-24 -31
20,000
-27 -35
22,000
-31 -39
24,000
-35 -43
26,000
-40 -47
28,000
-44 -51
29,000
-46 -52
31,000
– – – – – –
33,000
– – – – – –
35,000
– – – – – –
7A-76
MAXIMUM CRUISE POWER
TORQUE TOTAL
PER FUEL
ENGINE FLOW
qC
% LB/HR
5 100 978
1 100 950
-3 100 926
-7 100 900
100 878
100 856
100 838
100 824
100 812
100 802
96 764
91 726
86 682
80 632
73 582
70 556
– – – – – –
– – – – – –
– – – – – –
Figure 7A-72. Maximum Cruise Power, 1800 RPM, ISA – 10
1800 RPM
ISA – 10 qC
AIRSPEED
13,000 LB 12,000 LB
IAS TAS IAS
242 238 243
239 243 240
237 247 238
234 252 236
232 257 233
230 262 231
227 267 229
225 272 226
222 278 224
220 283 221
213 284 215
206 284 208
199 282 201
190 279 192
181 274 183
175 271 178
– – – – – – – – –
– – – – – – – – –
– – – – – – – – –
~
KNOTS
11,000 LB 10,000 LB
TAS IAS TAS IAS
239 243 240 244
244 241 245 242
248 239 249 240
253 237 254 237
258 234 259 235
263 232 264 233
268 230 270 231
274 227 275 228
279 225 281 226
285 223 287 223
286 217 288 218
286 210 288 212
285 203 288 204
283 195 286 197
279 186 283 188
276 181 280 184
– – – – – – – – – – – –
– – – – – – – – – – – –
– – – – – – – – – – – –
q
C
TAS
241
246
250
255
260
265
271
276
282
288
289
290
290
288
286
284
– – –
– – –
– – –