Beechcraft C-12C Operator And Technical Reference Manual page 771

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 qC
FEET
SL
58 52
2000
54 48
4000
50 44
6000
46 40
8000
43 36
10,000
39 32
12,000
35 28
14,000
31 24
16,000
27 20
18,000
23 16
20,000
19 12
22,000
15 8
24,000
11 4
26,000
7 0
28,000
3 -4
29,000
1 -5
31,000
-5 -9
33,000
-9 -13
35,000
– – – – – –
NORMAL CRUISE POWER
ISA + 37 qC
TORQUE TOTAL
PER FUEL
ENGINE FLOW
% LB/HR
100 1002
99 968
97 930
94 886
91 838
88 792
83 738
80 700
77 664
74 630
72 606
70 584
65 544
61 502
55 460
53 440
47 400
44 370
– – – – – –
Figure 7A-65. Normal Cruise Power, 1800 RPM, ISA + 37
1800 RPM
AIRSPEED
13,000 LB 12,000 LB
IAS TAS IAS
234 250 236
231 254 232
227 257 228
222 259 224
217 260 218
211 262 213
204 261 206
198 262 200
192 262 194
186 263 189
181 265 184
176 266 179
167 262 171
156 254 162
142 240 151
130 223 143
– – – – – – 125
– – – – – – – – –
– – – – – – – – –
TM 1-1510-218-10
~
KNOTS
11,000 LB
TAS IAS TAS
251 236 252
255 233 256
258 229 260
261 225 262
262 220 264
264 214 266
264 208 266
265 202 267
265 196 268
266 191 269
269 186 272
271 182 274
268 174 273
263 166 269
254 156 263
247 151 259
223 139 247
– – – 121 225
– – – – – – – – – – – –
q
C
10,000 LB
IAS TAS
237 253
236 257
231 261
226 263
221 265
215 267
209 268
203 269
198 270
193 272
188 275
184 278
177 277
169 274
160 270
156 267
146 260
134 249
– – –
7A-69