Beechcraft C-12C Operator And Technical Reference Manual page 670

TM 1-1510-218-10
NOTE: TO OBTAIN FUEL FLOW PER ENGINE, DIVIDE THE TOTAL FUEL FLOW VALUE FOR THE
CORRESPONDING ALTITUDE BY TWO.
PRESSURE IOAT
ALT
qC
FEET
SL 41
2,000 37
4,000 33
6,000 30
8,000 26
10,000 22
18
12,000
14,000 14
16,000 10
6
18,000
20,000 2
22,000 -2
24,000 -6
26,000 -10
28,000 -14
29,000 -17
31,000 -21
33,000 -26
35,000 -30
Figure 7-54. Recommended Cruise Power, 1800 RPM - ISA + 20
7-58
RECOMMENDED CRUISE POWER
ISA + 20 qC
OAT TORQUE FUEL FLOW
PER TOTAL
ENGINE
qC
% LB/HR
35 100 994
31 100 966
27 100 940
23 100 914
19 100 892
15 98 860
11 93 812
7 88 764
3 84 718
-1 79 674
-5 74 630
-8 69 590
-12 64 550
-16 59 512
-20 54 474
-22 52 456
-26 47 420
-30 42 392
-34 37 356
1800 RPM
@12,000 LB
IAS TAS
238 247
236 252
233 257
231 262
229 267
224 270
218 270
211 270
204 270
196 268
188 267
180 264
172 260
162 254
151 246
144 240
128 222
--- ---
--- ---
AIRSPEED ~ KNOTS
@11,000 LB
IAS TAS
239 248
237 253
234 258
232 263
230 268
225 271
219 272
212 272
205 272
198 271
191 270
183 268
175 265
166 261
156 255
151 250
139 240
122 219
--- --
q
C
@10,000 LB
IAS TAS
240 249
237 254
235 259
233 264
231 269
227 273
220 273
214 274
207 274
200 273
193 272
185 271
178 269
169 266
161 261
156 259
146 251
134 240
119 222