Beechcraft C-12C Operator And Technical Reference Manual page 681

NOTE: TO OBTAIN FUEL FLOW PER ENGINE, DIVIDE THE TOTAL FUEL FLOW VALUE FOR THE
CORRESPONDING ALTITUDE BY TWO.
PRESSURE IOAT OAT TORQUE
ALT
qC
FEET
SL 41
2,000 37
4,000 33
6,000 30
8,000 26
10,000 22
12,000 18
14,000 14
10
16,000
18,000 6
20,000 2
22,000 -2
24,000 -6
26,000 -10
-14
28,000
29,000 -16
31,000 -21
33,000 -26
35,000 ---
Figure 7-65. Maximum Cruise Power, 1900 RPM - ISA + 20
MAXIMUM CRUISE POWER
ISA + 20 qC
FUEL FLOW
PER TOTAL
ENGINE
qC
% LB/HR
35 100 1030
31 100 1004
27 100 976
23 100 952
19 400 930
18 96 882
11 91 834
7 86 784
3 82 736
-1 77 690
-5 72 646
-8 67 604
-12 62 564
-16 58 524
-20 53 486
-22 51 468
-26 46 432
-30 42 396
--- --- ---
1900 RPM
@12,000 LB
IAS TAS
243 252
241 257
238 262
236 267
233 272
227 274
220 274
213 274
206 273
199 272
191 270
182 267
174 263
164 258
154 251
148 246
134 232
--- ---
--- ---
TM 1-1510-218-10
AIRSPEED ~ KNOTS
@11,000 LB
IAS TAS
244 253
241 258
239 263
237 268
234 274
228 275
222 275
215 276
208 275
201 274
193 273
185 271
177 268
168 264
159 258
153 255
143 246
129 231
--- ---
q
C
@10,000 LB
IAS TAS
245 254
242 259
240 264
238 269
235 275
230 276
223 277
216 277
210 277
203 277
195 276
188 274
180 272
171 269
163 265
158 262
148 255
138 247
--- ---
7-69