SavannahTM-S Tail Dragger
Ultralight Aircraft
POH Addendum
English version
Page:6/11
ORIGINAL ISSUE DATE: 20.03.2013
REVISION DATE: 16.10.2017
4.2BASIC EMPTY WEIGHT AND BALANCE DETERMINATION
Forward C of G limit: 25% +/- 0.9 % (330 mm from L. E.) MAC
Rear C of G limit: 38.5%+/- 0.9 % (508 mm from L.E.) MAC
The aircraft is allowed to fly within a quite large weight and balance range thus easing the
aircraft’s load and balance.
Pilot should file the weight and balance table with crew’s weight, on board fuel weight and
luggage weight then check if condition remanis within limits, if not aircraft loading should
be revised.
WARNING
Failure to respect appropriate limits could lead to dangerous situations
In order to calculate weight and balance the basic empty weight and centre of gravity
position should be determined. Every time a configuration change occurs as addition or
removal of options, it is the pilot/owner’s responsibility to update the basic empty weight.
The aircraft MUST be weighed fitted with all equipment, accessories, engine oil,
coolant and WITHOUT FUEL. (NOTE: all the fuel MUST be drained accurately)
Place the aircraft in level flight attitude, rear fuselage upper skin should be
horizontal (Lift the tail).
Place the aircraft on three weight measuring equipment (one under each wheel of
the landing gear).
Record the three weight measuring equipment readings: the rear wheel weight will
be called P1, the left wheel weight P2, the right wheel weight P3.
By using a plumbing wire fixed to the leading edge, measure the distance DT
between the projection on the floor of the leading edge and the rear wheel axle,
and the distance DM between the same projected point and the main landing gear
axle.
Fill in the basic empty weight table reported below and calculate the momentum
