Beechcraft C-12C Operator And Technical Reference Manual page 780

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
5
16,000
1
18,000
-3 -11
20,000
-7 -15
22,000
-11 -19
24,000
-15 -23
26,000
-19 -27
28,000
-24 -31
29,000
-26 -32
31,000
-30 -36
33,000
-35 -40
35,000
-39 -44
7A-78
MAXIMUM 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
-3 100 824
-7 96 782
91 742
88 708
83 672
77 628
72 582
67 536
64 516
58 474
53 436
49 402
Figure 7A-74. Maximum 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
221 278 223
215 279 216
208 279 210
202 280 204
195 279 197
187 277 189
177 273 181
167 267 171
161 262 166
148 250 156
– – – – – – 143
– – – – – – – – –
~
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
280 224 282 225
281 218 283 219
282 212 284 213
283 206 285 207
282 199 285 201
281 192 284 194
277 183 281 186
273 175 278 177
270 170 275 173
262 161 270 164
250 150 263 155
– – – 137 249 145
q
C
TAS
246
251
256
261
266
272
277
283
284
286
287
288
287
285
282
280
276
271
263