DIAMOND AIRCRAFT
DA 20/100 Flight Manual
Weight & Balance
Doc # 202-100-VLA
20 December, 2000
Page
DOT-Approved
6 - 4
Figure 6.1: Sample Weighing Report
(Aircraft Specific report at the end of this chapter.)
Model:
DA 20/100
S/N: Registration:
Data in accordance with TCDS and Flight Manual
Reason for Weighing:
Reference Datum:
Leading edge of wing at root rib
Horizontal reference line: 24” Spirit Level placed on Fuselage Canopy Rail (L or R), supported at front by a
2 1/4” spacer as shown below
Weighing Conditions:
including brake fluid, lubricant, coolant and unusable fuel (3.31 lbs/1.5 kg)
Equipment List dated:
Support
Gross
[lbs] ([kg])
Tare
[lbs] ([kg])
Net Weight
[lbs] ([kg])
Lever Arm
[in] ([m])
Nose
W
N
=
D
N
=
Main Left
W
L
=
D
L
=
Main Right
W
R
=
D
R
=
Empty Weight W
T
= W
N
+ W
L
+ W
R
= lbs (kg)
Empty Weight Moment
M = W
N
x D
N
+ W
L
x D
L
+ W
R
x D
R
=
_________________
in lbs [m kg]
Empty Weight CG Position
Empty Weight Moment
Empty Weight
M
W
T
=
=
_________________
in [m]
(Positive results indicate, that CG is located aft of RD)
Maximum Permissible Useful Load:
Maximum Weight [lbs] ([kg])
+
Empty Weight [lbs] ([kg])
−
Max useful Load [lbs] ([kg])
=
Data to be entered into the Flight Manual: see page 6-6
Empty Weight [lbs] ([kg])
Empty- Weight-Moment [in
⋅
lbs] ([kg
⋅
m])
Place / Date
Inspector’s Stamp
Inspector’s Signature
