Beechcraft C-12C Operator And Technical Reference Manual page 747

NOTE: 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 42 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 2 -4
29,000 0 -5
31,000 -4 -9
33,000 -8 -13
35,000 – – – – – –
NORMAL CRUISE POWER
ISA + 37 qC
TORQUE TOTAL
PER FUEL
ENGINE FLOW
% LB/HR
100 968
100 940
100 912
100 886
96 838
93 790
88 738
84 700
81 664
76 630
76 606
73 582
69 542
63 500
58 460
55 440
51 406
47 376
– – – – – –
Figure 7A-41. Normal Cruise Power, 1700 RPM, ISA + 37
1700 RPM
AIRSPEED
13,000 LB 12,000 LB
IAS TAS IAS
229 245 231
227 249 228
225 254 226
222 259 223
216 260 218
210 261 212
204 261 205
197 261 200
191 261 194
185 261 188
180 263 183
174 263 177
165 258 169
154 251 160
140 237 149
– – – – – – 142
– – – – – – – – –
– – – – – – – – –
– – – – – – – – –
TM 1-1510-218-10
~
KNOTS
11,000 LB
TAS IAS TAS
246 232 247
251 229 252
255 227 257
260 224 262
262 219 263
263 214 265
263 207 265
264 201 266
265 196 267
265 190 268
267 185 270
268 180 272
264 172 270
259 164 266
251 154 260
244 149 256
– – – 137 245
– – – – – – – – –
– – – – – – – – – – – –
q
C
10,000 LB
IAS TAS
232 248
230 253
228 258
225 263
220 265
215 267
209 267
203 268
198 270
192 271
187 273
182 275
175 274
167 271
158 266
154 263
144 257
133 246
– – –
7A-45