6-5
Weight and Balance Determination for Flight
6-5-1
General
This section contains the crew seats, baggage, fuel load moments charts and C of G
envelopes in LB-IN and KG-M.
Refer to the Interior Configurations section for the passenger seat moments. Find the correct
Moment Chart for the Interior Code No. of the aircraft.
An Example Loading Form and a blank Loading Form for owners/operators use are given in
. Instructions on how to use the charts, complete the loading form and
to determine if center of gravity is within approved limits are given below.
6-5-2
Completion of the Loading Form
Enter the current Running Basic Empty Weight and Total Moment from
in the
appropriate space on the Loading Form,
(be careful to factor the moment by 1000 if
appropriate).
Enter the weights of all of the crew, passengers, items stowed in cabinets and baggage to be
loaded, in the appropriate space on the Loading Form,
Use the Moment Charts in
,
, and
, to determine the moment for the crew and baggage.
Use the correct Interior Code No. Moment Chart in the Interior Configurations section, to
determine the moment for the passengers.
Enter the moment of each item in the appropriate space on the Loading Form,
.
Add the weight and moment of all of the items to the Basic Empty Weight and Moment of the
airplane to determine the Zero Fuel Weight and Moment. Divide the moment by the weight to
determine the c.g. arm.
Locate this point in the C.G. Envelope,
. If the point falls within the envelope, the
loading meets the weight and balance requirements.
Use the Moment Chart in
, to determine the moment of the fuel
load.
Enter the weight and moment of the fuel in the appropriate space on the Loading Form,
.
Add the fuel weight and moment to the calculated Zero Fuel Weight and Moment to determine
the Ramp Weight and Moment. Divide the moment by the weight to determine the c.g. arm.
Locate this point in the C.G. Envelope,
. If the point falls within the envelope, the
loading meets the weight and balance requirements.
Subtract the weight and moment of the fuel allowance for engine start and ground operations
to determine Takeoff Weight and Moment. Divide the moment by the weight to determine the
c.g. arm. Nose and main landing gear retraction or extension and flap retraction or extension
weight and balance effects need not to be considered by the pilot for the weight and balance
calculation.
Locate this point in the C.G. Envelope,
. If the point falls within the envelope, the
loading meets the weight and balance requirements for takeoff.
Section 6 - Weight and Balance (EASA Approved)
Weight and Balance Determination for Flight
Pilot's Operating Handbook
Report No: 02406
Issue date: Mar 06, 2020
Page 6-5-1
12-C-A15-30-0605-00A-169A-A
FOR
GENERAL
FAMILIARIZATION
ONLY