Super 80 Professional – AOM
PERFORMANCE
Section 23 Page 16
Super 80 Professional – Aircraft Operating Manual
Coolsky, 2018
MACH .78 CRUISE
PRESS
ALT
1000FT
STD
TAS
KTS
IAS
KTS
STD
RAT
°C
GROSS WEIGHT – 1000 POUNDS
146 142 138 134 130 126 122 118 114 110 106 102 98
94
90
37
447
253
-31
1)
2)
1.94
74.9
1.91
77.5
1.89
79.9
1.86
82.1
1.83
84.3
1.81
86.5
1.79
88.4
1.77
90.4
1.75
92.3
35
450
264
-29
1.94
68.2
1.91
70.3
1.89
72.4
1.87
74.2
1.84
76.0
1.82
77.9
1.80
79.5
1.78
81.1
1.76
82.7
1.75
84.3
1.73
85.9
1.72
87.5
33
454
277
-24
1.93
62.6
1.91
64.3
1.89
66.0
1.87
67.5
1.85
69.0
1.83
70.6
1.81
72.0
1.79
73.3
1.77
74.6
1.76
76.0
1.74
77.3
1.73
78.6
1.71
79.9
1.70
81.2
1.68
82.5
31
458
289
-20
1.88
60.6
1.86
61.8
1.83
64.4
1.81
65.6
1.79
66.7
1.78
67.8
1.76
68.9
1.75
70.0
1.74
71.1
1.72
72.1
1.71
73.2
1.70
74.3
1.68
75.4
1.68
75.4
1.67
76.4
1.66
77.4
29
462
302
-16
1.82
59.1
1.81
60.0
1.79
60.9
1.78
61.8
1.76
62.8
1.75
63.7
1.74
64.6
1.73
65.5
1.71
66.4
1.70
67.3
1.69
68.3
1.68
69.1
1.67
69.9
1.66
70.8
1.65
71.8
1.64
72.3
27
466
315
-11
1.78
56.7
1.76
57.5
1.75
58.3
1.74
59.0
1.73
59.8
1.72
60.5
1.71
61.3
1.70
62.1
1.69
62.1
1.68
63.5
1.67
64.2
1.66
64.9
1.65
65.6
1.64
66.2
1.64
66.8
1.63
67.4
1)
EPR required
2)
Specific Range (NM/1000 LBS)
TO OBTAIN TOTAL FUEL FLOW:
Total Fuel Flow = TAS / Specific Range x 1000 (LBS/HR)
Correct STD TAS for deviation from standard temperature before computing total fuel flow.
Add 1 KTS for every 1°C above standard temperature, or subtract 1 KTS for every 1°C below
standard temperature.
ENGINE ALTITUDE CAPABILITY:
PRESS
ALT
1000 FT
TEMP DEV FROM STD - °C
+5
AND BELOW +10 +15
+20
GROSS WEIGHT - 1000 POUNDS
37
130
128 126 116
35
142
142 136 126
33
149
149 140 134
31
148 146
29
149 146
27
149
25
148
NOTE:
The weights in this table are the maximum gross weights at which Mach .78 can be
achieved without exceeding maximum cruise EPR limits.