Performance DA 42 NG AFM
Page 5 - 22 Rev. 3 01-Apr-2014 Doc. No. 7.01.16-E
Gradient
ROC fpm
TAS KTAS
[%] .
[]
[]
098
5.3.8 ONE ENGINE INOPERATIVE CLIMB PERFORMANCE
Conditions:
- Remaining engine .................... 92% load
- Dead engine ......................... feathered and secured
- Flaps .............................. UP
- Landing gear ........................ retracted
- Airspeed ............................ v
YSE
=85 KIAS
- Sideslip............................. half ball out
NOTE
With respect to handling and performance, the left-hand
engine (pilots view) is considered the "critical" engine.
The climb performance tables show the rate of climb. The gradient of climb can be
calculated using the following formula:
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