Beechcraft C-12C Operator And Technical Reference Manual page 758

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 39
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 -11 -16
33,000 -15 -20
35,000 -19 -24
7A-56
MAXIMUM CRUISE POWER
TORQUE TOTAL
PER FUEL
ENGINE FLOW
qC
% LB/HR
45 100 964
41 100 936
37 100 910
33 100 882
29 100 858
25 99 830
21 94 774
17 91 740
13 88 706
9 85 674
5 83 650
1 79 620
-3 74 580
-7 69 536
63 494
61 474
55 434
51 402
46 370
Figure 7A-52. Maximum Cruise Power, 1700 RPM, ISA + 30
1700 RPM
ISA + 30 qC
AIRSPEED
13,000 LB 12,000 LB
IAS TAS IAS
231 243 231
228 248 229
226 252 227
223 257 224
221 262 222
216 266 219
210 266 212
205 267 206
199 268 201
193 269 195
188 271 190
181 271 184
173 267 176
163 261 167
151 252 157
144 244 151
– – – – – – 138
– – – – – – – – –
– – – – – – – – –
~
KNOTS
11,000 LB 10,000 LB
TAS IAS TAS IAS
244 232 245 233
249 230 250 231
254 228 255 229
259 225 260 226
264 223 265 224
268 220 270 221
268 213 270 215
269 208 272 210
271 203 273 204
272 197 275 199
274 193 277 194
275 187 278 189
272 179 276 182
267 171 273 174
261 162 268 165
257 157 265 161
243 146 257 151
– – – 133 243 141
– – – – – – – – – 128
q
C
TAS
246
251
256
261
266
271
271
273
275
277
288
281
280
278
274
272
266
258
243