Beechcraft C-12C Operator And Technical Reference Manual page 669

NOTE: 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
27
2,000
4,000 23
6,000 19
8,000 16
10,000 12
12,000 8
14,000 4
16,000 0
18,000 -4 -11
-8 -15
20,000
22,000 -12 -18
24,000 -16 -22
26,000 -20 -26
28,000 -24 -30
29,000 -26 -32
31,000 -31 -36
33,000 -36 -40
35,000 -41 -44
Figure 7-53. Recommended Cruise Power, 1800 RPM - ISA + 10
RECOMMENDED CRUISE POWER
ISA + 10 qC
TORQUE FUEL FLOW
PER TOTAL
ENGINE
qC
% LB/HR
25 100 988
21 100 962
17 100 936
13 100 910
9 100 888
5 100 868
1 100 854
-3 96 810
-7 90 760
85 714
79 668
74 622
68 576
62 532
57 492
55 472
50 436
45 400
40 362
1800 RPM
@12,000 LB
IAS TAS
239 246
237 249
235 254
232 259
230 264
228 269
225 275
219 275
212 275
204 274
196 272
187 269
178 264
167 258
157 251
151 246
138 233
--- ---
--- ---
TM 1-1510-218-10
AIRSPEED ~ KNOTS
@11,000 LB
IAS TAS
240 246
238 250
236 255
234 260
231 265
229 271
226 276
220 277
213 277
206 276
198 275
190 272
181 268
171 264
162 258
257 255
146 246
133 233
--- ---
q
C
@10,000 LB
IAS TAS
241 246
239 251
234 256
234 261
232 266
230 272
227 277
221 278
214 278
207 278
200 277
191 175
183 272
174 268
166 264
161 262
152 256
141 247
128 234
7-57