Hawker Beechcraft Hawker 800XP, Руководство по эксплуатации для пилотов, Страница: 681 / 923

Page 6-18
Section IV Sub-section 6
SINGLE ENGINE
P/N 140-590032-0007
Revision A4: Sep, 2010
Pilot’s Operating Manual
SINGLE ENGINE DRIFT DOWN
ALTITUDE ft
AT ENGINE
FAILURE
WEIGHT lb
AT ENGINE
FAILURE
20,000 21,000 22,000 23,000 24,000 25,000 26,000 27,000
41,000
CONSTANT KIAS 185
IOAT AT START
°
C -23
TIME min 61
DISTANCE nm 308
FUEL USED lb 930
FINAL ALTITUDE ft 26,630
39,000
CONSTANT KIAS 185 189 194
IOAT AT START
°
C -24 -24 -23
TIME min 58 61 63
DISTANCE nm 294 305 319
FUEL USED lb 910 980 1055
FINAL ALTITUDE ft 26,610 24,610 23,450
37,000
CONSTANT KIAS 185 189 194 198 202
IOAT AT START
°
C -26 -25 -24 -24 -23
TIME min 56 59 61 64 67
DISTANCE nm 278 291 306 321 338
FUEL USED lb 875 955 1030 1115 1205
FINAL ALTITUDE ft 26,580 24,580 23,430 22,250 21,030
35,000
CONSTANT KIAS 185 189 194 198 202 206 210 214
IOAT AT START
°
C -24 -24 -23 -23 -22 -22 -21 -21
TIME min 53 56 59 62 65 69 74 78
DISTANCE nm 260 275 291 308 325 345 370 393
FUEL USED lb 840 920 1000 1085 1175 1285 1425 1565
FINAL ALTITUDE ft 26,550 24,560 23,400 22,230 21,010 19,740 18,350 16,850
8XC181-1
ISA +20° C
These ceilings are based on average performance at Maximum Continuous Thrust and a constant
drift down KIAS (minimum cruise speed at start of drift down weight).
To check obstacle clearance use the EN ROUTE NET GRADIENT in the Airplane Flight Manual which
will give a lower ceiling than the final drift down altitudes below.