POH / AFM
AQUILA AT01-100C
Section 6
WEIGHT AND BALANCE
Document Nr.:
Issue:
Supersedes Issue:
Date:
Page:
FM-AT01-1010-103
A.08
A.02 (15.10.2013)
25.05.2020
6 - 9
6.4.2 Weight and Moment Determination
Calculating
Loading
Condition
Lever from leading
edge of wing root
rib (BE)
[in]
[m]
Aquila AT01
Example
Registration No.:
Weight
[lb]
[kg]
Moment
[in lb]
[m kg]
Weight
[lb]
[kg]
Moment
[in lb]
[m kg]
EMPTY WEIGHT
(from Table 6.3.1)
D
SL
=
Exp.:
17.3
in
(0.440 m)
1116
506
19309
223
PILOT
19.1
(0.484)
(seat forward)
22.8
(0.580)
(seat aft)
121
55
2311
27
(seat forward)
PASSENGER
19.1
(0.484)
(seat forward)
22.8
(0.580)
(seat aft)
220
100
4609
53
(seat middle)
BAGGAGE
51.2
(1.3)
33
15
1690
20
Weight & Moment
without fuel
1490
676
27919
323
usable
FUEL
(
6.01 lb / US gal
)
(0.72 kg / l)
12.8
(0.325)
159
(= 26,5 gal)
72
(= 100 ltr)
2035
23
Total Weight &
Moment
1649
748
29954
346
Explanation:
Transfer the empty weight and the empty C.G. (D
SL
) from section 6.3.1 or from
the current Aircraft Weighing Report.
Add all the weights
Transfer the moments from chart 6.4.1 or calculate the moments by multiplying the
weight with the arms.
Find the sum of the weights and moments
Plot the total weight and moment in the
Center of Gravity Range and Moment Limits
diagram 6.4.3
.
The flight C.G. from the example is
29954 in lb / 1649 lb = 18.2 in
(limit range: 16.8
– 20.6
in) respectively
346 kgm / 748 kg = 0,463 m
(limit range: 0,427
– 0,523 m) aft of the datum
and is within the limits.
