COMCO IKARUS
Maintenance Manual C42 Series
MaintenanceManual C42-
Series_Issue_VII_18.02.2014.doc
Revison No.:1 19 from 107
Insert the values for total empty weight, (G1 + G2) and cg distance aft of
datum, (X), into the table below. Multiply Empty Weight (kg) by cg distance aft
of datum (mm) to derive empty weight moment (kg.mm) in the last column.
Complete the remaining weights for seat loads, fuel and baggage and multiply
these by the lever arm lengths (given below).
Add up the weights and moments, then divide the total weight by the total
moment to give laden cg location aft of datum.
L oa d ing p lan
Posi tio n w eig ht x le ve r arm = m om e nt
lb (k g) in . (m m ) lb in (k gm m )
Em p ty w eig ht
1. S ea ts 15 .7 ( 400 )
2. Fu el 37 .4 ( 950 )
3. B ag gag e 5 1.2 (13 00)
T otal W e igh t lb ( kg ) T otal M o m en t lb in (kg m m )
T o ta l Mo m en t lb i n (kgm m )
centre o f gr av ity C G =
-- ----- ------ ------ ----- ------ ----- ------ - = c m
in (m m )
T o ta l W ei ght lb (k g )
Centre of gravity range is dependant on aircraft model. Refer to POH.
2.2.2 Conditions of Weighing
The dry empty weight of the aircraft is defined under the following conditions:
All normal installed equipment fitted.
Oil and coolant levels normal.
No usable fuel.
Note: Remaining within the Maximum Take-off Weight (MTOW) as
specified in the P.O.H. is the pilot’s responsibility.
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