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AIRCRAFT PERFORMANCES & LIMITATIONS
The “Supplement” contains charts for takeoff distance, time fuel and distance to climb, cruise
performance including range and endurance… but for some reason, no short field landing distance.
Regarding the takeoff distance charts (page 5-2 of the “Supplement”), two conditions are considered:
takeoff at maximum allowable weight 980 kg, and at 880 kg. Note that TAE considers 1 litre of fuel for
engine start, taxi and take-off.
With regard to range and endurance, the values are based on 109 litres on departure.
The aircraft is certified for both Normal and Utility categories.
Maximum allowable altitude is 16500 ft.
WEIGHT & BALANCE
Remember that diesel and JET FUEL are heavier than AVGAS and they carry more energy
per volume.
Because the fuel in the Robin series is in an aft location, fuel consumption shifts the CG
forward. The DR400/135CDI delivers greater range and, at altitude, greater speed, than
AVGASpowered Robin of equivalent sea-level power ratings, for a given volume of fuel.
Normal category
Maximum ramp weight: 980 kg
Maximum takeoff weight: 980 kg
Maximum landing weight: 980 kg
Utility category:
Maximum ramp weight: 910 kg
Maximum takeoff weight: 910 kg
Maximum landing weight: 910 kg
Consequently, assuming two occupants of 80 kg each + 10 kg of baggage (flight cases, etc…) + fuel
up to 110 litres, we have:
600 + 160 + 10 + 89 = 859 kg ramp weight, 858 kg takeoff weight
Needless to say that a third person on board would significantly reduce the allowable fuel load. As for
operations in utility category, it seems that only two persons can be on board.
Note also that the “Supplement” includes only a “LOAD MOMENT” graph. This document is to be used
together with a copy issued from the original POH for the “LOADED AIRPLANE MOMENT/1000” and
“AIRPLANE C.G. LOCATION” graphs. These documents are those which must be used for load &
balance calculations
Versie oktober 07
