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-20  “  2.06  2.06  2.06  2.05  2.05  2.04  2.04  2.04 
-16  2.01  2.03  2.03  2.03  2.02  2.02  2.02  2.02  2.04 
-12 2.00  2.00  2.00  2.00  2.00  1.99  1.99  2.00  2.04 
-8 1.97  1.97  1.97  1.97  1.97  1.96  1.96  2.00  2.02 
-4 1.95  1.95  1.95  1.95  1.94  1.94  1.95  1.99  1.99 
0 1.92  1.92  1.92  1.92  1.91  1.91  1.95  1.97  1.97 
4 1.89  1.89  1.89  1.89  1.89  1.90  1.94  1.94  1.94 
8 1.87  1.87  1.87  1.87  1.87  “  1.92  1.92  1.92 
12 1.84  1.84  1.84  1.84  “  1.90  1.90  1.90  1.90 
16 1.82  1.82  1.82  1.83  1.87  1.88  1.87  1.87  1.87 
20 1.78  1.78  1.78  1.83  1.86  1.85  1.85  1.85  -
30 1.73  1.74  1.77  1.79  1.79  1.78  1.78  - -
40 1.71  1.71  1.71  1.71  1.70  1.70  1.70  - -
46  1.65  1.65  1.65  1.69  1.64  - - - -
Anti-ice Bleed Corrections: Engine ON -0.08 / Engine & airfoil -0.10 

-217A

RAT .C  PRESSURE ALTITUDE - FEET 
1000  2000  5000  10000  15000  20000  25000  30000  35000 
-50  1.97  2.00  2.06  2.06  2.05  2.05  2.05  2.05  2.05 
-20  “  “  2.06  2.06  2.05  2.05  2.05  2.05  2.05 
-16  “  “  2.03  2.03  2.03  2.02  2.02  2.02  2.02 
-12 “  2.00  2.00  2.00  2.00  2.00  1.99  “  “ 
-8 1.97  1.98  1.98  1.98  1.97  1.97  1.97  “  “ 
-4 1.95  1.95  1.95  1.95  1.95  1.94  “  2.02  2.02 
0 1.92  1.92  1.92  1.92  1.92  1.91  “  2.00  2.00 
4 1.90  1.90  1.90  1.90  1.89  “  1.97  1.97  1.97 
8 1.87  1.87  1.87  1.87  1.88  “  1.95  1.95  1.95 
12 1.84  1.84  1.84  1.84  “  1.91  1.92  1.92  1.92 
16 1.82  1.82  1.82  “  “  1.90  1.90  1.90  1.90 
20 1.78  1.78  1.80  “  1.88  1.87  1.87  1.87  -
24 1.75  1.77  “  1.84  1.85  1.85  1.84  1.84  -
30 1.75  1.77  1.80  1.82  1.81  1.81  1.80  - -
40 1.73  1.73  1.73  1.73  1.73  1.72  1.72  - -
46  1.66  1.66  1.66  1.66  1.66  - - - -
Anti-ice Bleed Corrections: Engine ON -0.08 / Engine & airfoil -0.10 

Climb Gradient Charts
The following tables are informational only and provide an example of the two engine climb capability.
Note:  Calculations are for flaps 15. takeoffs (conservative for flaps 11. & 4.). Maximum climb thrust, sea level, standard day, long range climb, all engines operating, 250 KIAS climb speed.

-217 & -217A

WT. 1000 LBS.  Average Climb Gradient to 3000 FT FT/NM  Average Climb Gradient to 5000 FT FT/NM 
100  1128  1092 
120  912  871 
140  744  708 
150  672  648 

The two engine Second Segment Climb gradient for a 130,000 lb. aircraft is 814 FT/NM. (-217 & -217A.)
ABNORMAL/ ADJUSTMENTS
Departure with Abnormal Conditions
The following abnormal takeoff conditions require weight penalties to be applied to the allowable takeoff weight. The Dispatcher will input these penalties so that they are applied in the Pilot Weight Manifest that is provided to you. The Runway Analysis in the Flight Departure Paperwork does not take into account any abnormal takeoff conditions. If the Flight Crew needs to use the Runway Analysis in the Flight Departure Paperwork to calculate takeoff capability when any abnormal takeoff condition is in effect, the appropriate takeoff weight penalty from this section must be applied.
Note: V-Speeds in the Runway Analysis in the Flight Departure
Paperwork are valid after application of any of the takeoff weight
　
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