Page 6-11
Pilot’s Operating Manual
P/N 140-590032-0007
Revision A4: Sep, 2010
Section IV Sub-section 6
SINGLE ENGINE
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
33,000
CONSTANT KIAS
185
189
194
198
202
206
210
214
IOAT AT START
°
C
-57
-57
-56
-56
-56
-55
-55
-55
TIME min
24
26
30
33
36
39
41
43
DISTANCE nm
117
129
148
168
184
198
210
221
FUEL USED lb
385
435
505
595
665
735
800
860
FINAL ALTITUDE ft
31,380
31,030
30,180
29,290
28,380
27,480
26,570
25,650
31,000
CONSTANT KIAS
189
194
198
202
206
210
214
IOAT AT START
°
C
-53
-53
-53
-52
-52
-52
-51
TIME min
10
20
27
31
34
37
39
DISTANCE nm
47
101
134
157
174
189
202
FUEL USED lb
165
355
485
580
660
735
805
FINAL ALTITUDE ft
30,820
30,070
29,210
28,320
27,430
26,520
25,610
29,000
CONSTANT KIAS
198
202
206
210
214
IOAT AT START
°
C
-49
-49
-49
-48
-48
TIME min
7
21
27
31
35
DISTANCE nm
34
102
135
158
176
FUEL USED lb
130
390
530
630
720
FINAL ALTITUDE ft
28,910
28,170
27,330
26,450
25,550
27,000
CONSTANT KIAS
206
210
214
IOAT AT START
°
C
-45
-45
-45
TIME min
4
20
27
DISTANCE nm
20
98
134
FUEL USED lb
80
405
565
FINAL ALTITUDE ft
26,960
26,270
25,440
25,000
CONSTANT KIAS
IOAT AT START
°
C
TIME min
DISTANCE nm
FUEL USED lb
FINAL ALTITUDE ft
8XC177-2
ISA -15° 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.
