Weight and
Balance Data
CSP–520N–1
MD 520N (500N) ROTORCRAFT FLIGHT MANUAL
TM
Original
6–5
Aircraft Actual Weight
Model 500N Serial No. Registration No. Date 7/11/91
Weighed by J Doe Witnessed by R Doe
EMPTY
FULL
FUEL
OIL, ENGINE
OIL, MAIN GEARBOX
OIL, FAN GEARBOX
WEIGHING POINT
FIRST
READING
LBS.
SECOND
READING
LBS.
THIRD
READING
LBS.
AVG. SCALE
READING
LBS.
Left Main
692.3
688.5
688.9
689.9
Right Main
675.2
679.7
678.5
677.8
Tail
163.5
163.3
163.5
163.4
TOTAL (AS WEIGHED)
1531.1
20
40
60
80
100
120
140
160 180
200
220
240
260 280
300
320
315.0
100.0
28.0
15.0 STA
STA
STA
STA
STA
3
°
LEVELING PLUMB
STA 92.6
REFERENCE DA
TUM
STA
78.5
JIG POINT
FWD JACKING POINT STA 96.9
ENGINE SECTION
FUEL CELL
COMPARTMENT
JIG POINT
AFT JACKING
POINT STA 275.4
124.0
OIL TANK–RH SIDE
FIRE WALL
NOTE: IN LEVEL ATITUDE, MAIN ROTOR MAST IS TILTED 3
°
FORWARD
F05–030
WEIGHING POINT
AVG. SCALE
READING
LBS.
TARE OR
CALIB. CORR
LBS.
NET
WEIGHT
LBS.
H
ARM
IN.
L
ARM
IN.
H
MOMENT
IN. LB.
L
MOMENT
IN. LB.
Left Main
689.9
0
689.9
96.9
– 25.6
66851
–17661
Right Main
677.8
0
677.8
96.9
+25.6
65679
+17352
Tail
163.4
0
163.4
275.4
0.0
45000
0
TOTAL (AS WEIGHED)
1531.1
115.9
– 0.20
177530
– 309
Less: Surplus Weight (See Table 1)
–10.2
60.9
7.4
–621
–75
Plus: Missing Required Equipment (See Table 1)
183.7
91.5
– 0.03
16812
– 6
TOTAL – BASIC WEIGHT
1704.6
113.6
– .23
193721
– 390
Figure 6–3. Sample Weight and Balance Report (Sheet 1 of 2)
x
x
x
x
