CSP
−
902RFM207E
−
1
ROTORCRAFT FLIGHT MANUAL
MD900 (902 Configuration with PW 207E)
Weight and
Balance Data
Original
6
−
8
Reissue 2
6
−
4.
LONGITUDINAL WEIGHT AND BALANCE DETERMINATION:
PASSENGER CONFIGURATION
To determine that the gross weight and longitudinal center of gravity (fore and
aft) for a given flight are within limits, proceed as follows.
Obtain aircraft basic weight and moment from the Weight and Balance Record in
serted in this section.
Determine weights and moments of useful load items (Ref. Figure 6-2).
Add above items.
Determine corresponding center of gravity for gross weight by dividing total moment
by gross weight. This computation must be done with zero fuel and with mission
fuel gross weight (Ref. EXAMPLE I: ).
NOTE
:
If loadings are not symmetrical about the aircraft centerline, determine lateral
CG’s as described in Paragraphs 6
EXAMPLE I: Longitudinal CG Determination
−
Passenger
ITEM
WEIGHT
(LB)
STATION
(ARM)
MOMENT
(IN
−
LB)
Basic Weight (from Figure 6-4)
3272.8
688665
Pilot
170
130.70
22219
Copilot/Passenger
170
130.70
22219
Passenger - Rear Facing R/H
170
173.0
29410
Passenger - Rear Facing L/H
170
173.0
29410
Passenger - FWD Facing R/H
170
213.0
36210
Passenger - FWD Facing L/H
170
213.0
36210
1. Zero Fuel Weight
Add: Fuel (Jet-A)
4292.8
994.0
191.1
864343
189953
2. Gross Weight
5286.8
1054296
Calculation of Longitudinal CG
CG at Zero Fuel Weight:
Moment at Zero Fuel Weight
=
864343
= 201.3
Zero Fuel Weight
4292.8
CG at Gross Weight:
Moment at Gross Weight
=
1054296
= 199.4
Gross Weight
5286.8
NOTE
:
The CG’s fall within the limits specified in Table 6
1; therefore, the loading meets
the longitudinal CG limits.
Summary of Contents for MD900 Explorer
Page 4: ......
