Super 80 Professional – AOM
PERFORMANCE
Section 23 Page 15
Super 80 Professional – Aircraft Operating Manual
Coolsky, 2018
MACH .77 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
442
249
-32
1)
2)
1.94
75.1
1.91
77.7
1.88
80.2
1.85
82.5
1.83
84.7
1.80
86.8
1.78
88.8
1.76
90.8
1.75
92.6
1.73
94.5
35
444
261
-29
1.93
68.6
1.91
70.8
1.88
72.8
1.86
74.8
1.84
76.6
1.81
78.3
1.79
80.0
1.78
81.6
1.76
83.2
1.74
84.7
1.73
86.3
1.71
88.0
1.69
89.6
33
448
273
-25
1.92
53.1
1.90
64.9
1.88
66.6
1.86
68.2
1.84
69.7
1.82
71.1
1.80
72.6
1.78
73.9
1.76
75.2
1.75
76.5
1.74
77.8
1.72
79.1
1.71
80.5
1.69
81.8
1.68
83.1
1.66
84.4
31
452
285
-21
1.85
62.6
1.83
63.8
1.81
65.0
1.80
66.2
1.78
67.3
1.77
68.3
1.75
69.5
1.74
70.5
1.73
71.6
1.71
72.8
1.70
73.9
1.69
75.0
1.68
76.1
1.66
77.1
1.65
78.1
1.64
79.1
29
456
298
-16
1.80
60.7
1.78
61.6
1.77
62.5
1.76
63.4
1.74
64.3
1.73
65.2
1.72
66.2
1.71
67.1
1.69
68.0
1.68
68.9
1.67
69.8
1.66
70.7
1.65
71.6
1.64
72.4
1.63
73.2
1.62
74.0
27
460
311
-12
1.75
58.1
1.74
58.9
1.73
59.7
1.72
60.5
1.71
61.2
1.70
62.0
1.69
62.8
1.68
63.5
1.67
64.3
1.66
65.0
1.65
65.7
1.64
66.4
1.63
67.0
1.62
67.7
1.62
68.3
1.61
69.0
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.
Example:
FL310
GWT 144,000
RAT -15°C
From chart:
Specific Range = 63.8
RAT -15°C = STD + 6
TAS = 452 + 6 = 458
Total Fuel Flow = 458 / 63.8 x 1000 = 7178 LBS/HR
ENGINE ALTITUDE CAPABILITY:
Airplane altitude capability at Mach .77 is not limited by engine performance.
