Aerospool WT9 Dynamic LSA / Club, Pilot Operating Handbook

Page: 112 / 204

Page 6-2 EASA Approved Initial issue
6.1 General
This Chapter contains weight and balance records and the loading range for safe operation of WT9 Dynamic LSA
aircraft. As a pre-requisite for safe flight the pilot in command must ensure that the loaded and fueled aircraft
’s
weight and moment are within approved limits during takeoff, flight and landing.
The Basic Empty Weight / Moment are initially specified by the aircraft
’s manufacturer and are recorded into the
Weight and Balance Record (Chapter 6.3). Installation or removal of any equipment will influence this initial data. It is
the duty of any authorized organization installing (or removing) any equipment on (or from) the aircraft
to determine the resulting new Basic Empty Weight / Moment for the aircraft.
The Weight and Balance Record must be maintained current and up-to-date. In simple cases the new Basic Empty
Weight / Moment may be calculated. In more complex cases the new Basic Empty Weight / Moment must be
determined by weighing the newly configured aircraft. The new Basic Empty Weight / Moment values shall be
recorded immediately, along with all other pertinent information into the aircraft
’s Weight and Balance Record
Chapter 6.3). The updated Weight and Balance Record must be used when calculating loading plans for all future
flights.
The WT9 Dynamic LSA center of gravity is expressed as a moment. The moment represents the sum of each individual
load’s moment. Each individual load’s moment is the multiple of its applied load and its distance from a Reference
Datum. The distance from the Reference Datum to the point of each load’s application is known as the CG Arm.
The Reference Datum is located 1.975 m / 77.76 in forward from inner surface of the firewall. The inner surface of the
firewall is identical with the engine cowlings and fuselage vertical border line in which the reference point (RP) lies
(see Chapter 6.2.3).
The approved Aircraft Weight and Moment Limit are presented graphically in the Weight and Moment Limits Chart
(see Chapter 6.6). The limitations presented in the Weight and Moment Limits Chart must be adhered to. If the
aircraft is improperly loaded or overloaded with co-pilot (passenger), baggage or fuel the aircraft
’s performance,
structural strength and center of gravity may be dangerously influenced. If the center of gravity is too far forward it
may be difficult, or impossible, to rotate for takeoff and to flare for landing. If the center of gravity is too far aft
longitudinal stability and aircraft controllability may be dangerously influenced.
WARNING
The loaded aircraft must be operated within approved weight
and CG limits during takeoff, flight and landing!
NOTE
Prior to fuelling the aircraft, check the flig ht’s loading plan and
determine the permissible quantity of fuel. If the loaded and
fueled aircraft is out of weight and CG limitations, the aircraft must
be reloaded.
The total weight and cumulative moment of a loaded and fuelled aircraft is simply calculated using the Weight and
Balance Loading Form (Chapter 6.4.2). This calculation requires the aircraft
’s Basic Empty Weight / Moment, the
weight of pilot/co-pilot (passenger), the total weight of baggage in the baggage compartment, and the usable weight
of fuel. The aircraft
’s Basic Empty Weight / Moment are obtained from the aircraft ’s Weight and Balance Record
(Chapter 6.3).