Super 80 Professional – AOM
PERFORMANCE
Section 23 Page 14
Super 80 Professional – Aircraft Operating Manual
Coolsky, 2018
MACH .76 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
436
245
-33
1)
2)
1.88
79.5
1.85
82.0
1.83
84.0
1.81
86.4
1.79
88.5
1.77
90.5
1.75
92.5
1.73
94.5
1.71
96.3
35
438
257
-30
1.88
72.4
1.86
74.5
1.84
76.2
1.82
78.1
1.79
79.9
1.78
81.5
1.76
83.2
1.74
84.8
1.72
86.4
1.71
87.9
1.69
89.5
1.68
91.2
33
442
269
-26
1.88
66.4
1.86
68.1
1.84
69.5
1.82
71.0
1.80
72.6
1.78
73.9
1.76
75.3
1.75
76.7
1.73
78.0
1.72
79.3
1.70
80.5
1.69
81.9
1.67
83.2
1.66
84.6
1.65
85.9
31
446
281
-21
1.83
63.7
1.81
65.1
1.79
66.4
1.78
67.5
1.76
68.6
1.75
69.7
1.74
70.8
1.72
71.9
1.71
72.9
1.70
74.1
1.68
75.2
1.67
76.3
1.66
77.4
1.65
78.5
1.64
79.6
1.63
80.6
29
450
294
-17
1.78
61.8
1.76
62.8
1.75
63.7
1.74
64.7
1.72
65.6
1.71
66.5
1.70
67.3
1.69
68.3
1.68
69.2
1.67
70.2
1.66
71.1
1.65
72.0
1.64
72.9
1.63
73.7
1.62
74.5
1.61
75.4
27
454
306
-13
1.73
59.3
1.72
60.1
1.71
60.8
1.70
61.5
1.69
62.3
1.68
63.1
1.67
63.9
1.66
64.7
1.65
65.4
1.64
66.2
1.63
66.9
1.62
67.6
1.62
68.3
1.61
69.0
1.60
69.6
1.60
70.3
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:
Airplane altitude capability at Mach .76 is not limited by engine performance.
