0 50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800 STATIONS
COMPARTMENTS
A
B
C
D
E
F
350
WL
324.7
300
250
200
WATER LINES
GROUND LINE
STA
644.6
STA STA
247
763.5
315.5
STA
270
AB1086
SA
Section II WEIGHT AND BALANCE
6.4 SCOPE.
This section provides appropriate information required for the computation of weight and balance for loading an individual helicopter. The forms currently in use are the DD Form 365 series. The crewmember has available the current basic weight and moment which is obtained from DD Form 365-3 (Chart C) for the individual helicopter. This chapter contains weight and balance de.nitions; ex-planation of, and .gures showing weights and moments of variable load items.
6.5 WEIGHT DEFINITIONS.
a.
Basic Weight. Basic weight of an aircraft is that weight which includes all hydraulic systems and oil sys-tems full, trapped and unusable fuel, and all .xed equip-ment, to which it is only necessary to add the crew, fuel, cargo, passengers and patients to determine the gross weight for the aircraft. The basic weight varies with struc-tural modi.cations and changes of .xed aircraft equipment.
b.
Operating Weight. Operating weight includes the ba-sic weight plus aircrew, the aircrew’s baggage, and emer-gency and other equipment that may be required. Operating weight does not include the weight of fuel, ammunition, cargo, passengers or external auxiliary fuel tanks if such tanks are to be disposed of during .ight.
c.
Gross Weight. Gross weight is the total weight of an aircraft and its contents.
6.6 BALANCE DEFINITIONS.
6.6.1 Horizontal Reference Datum. The horizontal reference datum line is an imaginary vertical plane at or forward of the nose of the helicopter from which all hori-zontal distances are measured for balance purposes. Dia-grams of each helicopter show this reference datum line as balance station zero.
6.6.2 Arm. Arm, for balance purposes, is the horizontal distance in inches from the reference datum line to the CG of the item. Arm may be determined from the helicopter diagram in Figure 6-1.
6.6.3 Moment. Moment is the weight of an item multi-plied by its arm. Moment divided by a constant is generally used to simplify balance calculations by reducing the num-ber of digits. For this helicopter, moment/1000 has been used.
6.6.4 Average Arm. Average arm is the arm obtained by adding the weights and moments of a number of items, and dividing the total moment by the total weight.
6.6.5 Basic Moment. Basic moment is the sum of the moments for all items making up the basic weight. When using data from an actual weighing of a helicopter, the basic moment is the total of the basic helicopter with re-spect to the reference datum. Basic moment used for com-puting DD Form 365-4 is the last entry on DD Form 365-3 for the speci.c helicopter. Cargo Hook Moments and Res-cue Hoist Moments are shown in Figures 6-4 and 6-5, re-
spectively.
6.6.6 Center of Gravity (CG). Center of gravity is the point about which a helicopter would balance if suspended. Its distance from the reference datum line is found by di-viding the total moment by the gross weight of the helicop-ter.
6.6.7 CG Limits. CG limits (Figures 6-9 and 6-10) de-
.nes the permissible range for CG stations. The CG of the loaded helicopter must be within these limits at takeoff, in the air, and on landing.
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