Example: The sample problem on page 9 calculated a Runway Limit gross weight of 155,300 lbs. If the right engine hydraulic pump were inoperative, the takeoff weight penalty for a flaps 11. takeoff on runway 8 is 1300 lbs. (Interpolation between 1300 and 1200 is authorized if necessary.) The corrected Runway Limit Gross weight is 154,000 and the Climb Limit gross weight remains 149,500 yielding a maximum allowable takeoff weight of 149,500 lbs.
Approach Idle Fail High - ARTS Not Reset
If the Flight Crew uses the Runway Analysis in the Flight Departure Paperwork to determine takeoff capability, the appropriate takeoff weight correction from the table below should be subtracted from the maximum runway limit weight.
-217/-217A
Approach Idle Fail High (ARTS not reset) - Takeoff Weight Corr (lbs.)
Runway slopes -2.0% to +1.7% / Winds -10 to +30 / A/C on or off
Airport Pressure Altitude Runway Length 6000 7000 8000 9000 10,000 11,000 12,000 13,000
SL to Flaps 4.
1000 N/A 2800 2400 10700 17200 21000 21000 21000
2000 N/A 2600 2300 8400 15000 20400 20500 20500
4000 N/A 2500 2300 5100 12400 17200 19600 19600
6000 N/A 2400 2100 2000 8000 13000 16600 16600
SL to Flaps 11.
1000 N/A 2900 2500 9100 9000 9000 10600 10600
2000 N/A 2800 2400 6600 7400 7400 7400 9000
4000 N/A 2600 2300 3900 3900 3900 5500 5500
6000 N/A 2400 2200 1900 1800 1600 2500 2500
SL to Flaps 15.
1000 N/A 2900 3200 5200 5200 7200 7500 7500
2000 N/A 2700 2600 3900 3900 4700 6100 6100
4000 N/A 2700 2300 2100 1900 2000 3100 3100
6000 N/A 2500 2200 2000 1800 1600 400 400
Example: The sample problem on page 9 calculated a Runway Limit gross weight of 155,300 lbs. If the approach idle system fails to high, the takeoff weight penalty for a flaps 11. takeoff on runway 8 is 9100 lbs. (Interpolation between 9100 and 9000 is authorized if necessary.) The corrected Runway Limit Gross weight is 146,200 and the Climb Limit gross weight remains 149,500 yielding a maximum allowable takeoff weight of 146,200 lbs.
V-Speeds for Takeoff - Manual Calculation
Policy & Examples
Note: The following procedure for manual calculation of takeoff V-speeds is for use only when the Accuload system is totally “down” and the Load Planner is unable to use it to prepare the weight manifest. It is not to be used when the Accuload system is in operation.
The instructions for manually calculating V-speeds are on the front of the appropriate (-217 or -217A) foldout page in this section.
Note: Flex (reduced thrust) takeoffs are not authorized when using V-speeds calculated with this procedure.
Example problem #1
Flight 486 LAS to IAH LAS runway 25R
Aircraft 806 / -217A Elevation 2175’
Gross Weight 144,000 Runway slope +1.03
Flaps 4. Ambient temp 95.F
Note that in this problem VR was increased to equal V1.
MD-80 Sec. 5 Page 31
Flight Manual Continental Rev. 05/15/95 #23
Example problem #2
Flight 1573 IAH to AUS IAH runway 14L
Aircraft 870 / -217 Elevation 98’
Gross Weight 100,000 Runway slope -.08
Flaps 11. Ambient temp 35.F
Note that in this problem minimum speeds need to be used for takeoff.
Blank V-Speeds Worksheet
INTENTIONALLY LEFT BLANK
-217 MD-80 TAKEOFF & TRANSITION SPEEDS -217 MD-80 Sec. 5 Page 33 Note: Use this procedure only if the Accuload system is not available.
Flight Manual Continental Rev. 12/01/97 #26
PROCEDURE:
1 BASIC TAKEOFF SPEEDS
GROSS WEIGHT FLAPS 15. FLAPS 11. FLAPS 4.
V1 VR V2 V1 VR V2 V1 VR V2
90,000 100 108 119 102 110 121 111 120 131
92,000 101 110 120 104 111 122 113 122 132
94,000 103 111 121 105 113 123 114 124 134
96,000 104 113 123 107 114 125 116 126 135
98,000 106 115 124 108 116 126 117 127 137
100,000 107 116 125 110 117 127 119 129 138
102,000 109 117 126 111 118 128 121 131 139
104,000 110 118 128 113 120 129 123 132 142
106,000 112 120 129 114 121 131 124 134 143
108,000 113 121 131 116 123 132 126 135 144
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