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6.7 DD FORM 365-3 (CHART C) WEIGHT AND BAL-ANCE RECORDS.
DD Form 365-3 (Chart C) is a continuous history of the basic weight, moment, and balance, resulting from struc-tural and equipment changes in service. At all times the last weight, moment/constant, is considered the current weight and balance status of the basic helicopter.
6.8 LOADING DATA.
The loading data in this chapter is intended to provide information necessary to work a loading problem for the helicopter. From the .gures, weight and moment are ob-tained for all variable load items and are added arithmeti-cally to the current basic weight and moment from DD Form 365-3 (Chart C) to obtain the gross weight and mo-ment. If the helicopter is loaded within the forward and aft CG limits, the moment .gure will fall numerically between the limiting moments. The effect on the CG of the expen-ditures in .ight of such items as fuel and passengers may be checked by subtracting the weights and moments of such items from the takeoff gross weight and moment, and checking the new moment, with the CG limits chart. This check should be made to determine whether or not the CG will remain within limits during the entire .ight.
Change 4 6-3

6.9 DD FORM 365-4 (FORM F).
There are two versions of DD Form 365-4. Refer to TM 55-1500-342-23 for completing the form.
Section III FUEL/OIL
6.10 FUEL MOMENTS.

Fuel transfer sequence must be carefully planned and executed in order to main-tain CG within limits.
When operating with a light cabin load or no load, it may be necessary to adjust fuel load to remain within aft CG limits. Fuel loading is likely to be more restricted on those aircraft with the HIRSS installed.

For a given weight of fuel there is only a very small variation in fuel moment with change in fuel speci.c weight. Fuel moments should be determined from the line on Figure 6-2 which represents the speci.c weight closest to that of the fuel being used. The full tank usable fuel weight will vary depending upon fuel speci.c weight. The aircraft fuel gage system was designed for use with JP-4, but does tend to compensate for other fuels and provide acceptable readings. When possible the weight of fuel on-board should be determined by direct reference to the air-craft fuel gages. The following information is provided to show the general range of fuel speci.c weights to be ex-pected. Speci.c weight of fuel will vary depending on fuel temperature. Speci.c weight will decrease as fuel tempera-ture rises and increases as fuel temperature decreases at the rate of approximately 0.1 lb/gal for each 15°C change. Spe-ci.c weight may also vary between lots of the same type fuel at the same temperature by as much as 0.5 lb/gal. The following approximate fuel weights at 15°C may be used for most mission planning:
Fuel Type Speci.c Weight
JP-4 6.5 lb/gal.
JP-5 6.8 lb/gal.
JP-8 6.7 lb/gal.
Jet A 6.8 lb/gal.
Jet B 6.3 lb/gal.
Change 4 6-5

EXAMPLE WANTED FUEL MOMENT
KNOWN
FUEL QUANTITY MAIN 1700 POUNDS
METHOD
FOR MAIN TANK ENTER AT 1700 POUNDS AND MOVE RIGHT TO MAIN LINE. MOVE DOWN READ MOMENT / 1000 = 710

GALLONS ARM = 420.75 JP.4 JP.5 450 450

400 400
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0
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0  200  400  600  800  1000 
FUEL MOMENT/1000  SA AB1087 
Figure 6-2. Fuel Moments 

Section IV PERSONNEL
6.11 PERSONNEL MOMENTS.
When aircraft are operated at critical gross weights, the exact weight of each individual occupant plus equipment should be used. Personnel stations are shown on Figure 6-3. If weighing facilities are not available, or if the tactical situation dictates otherwise, loads shall be computed as fol-lows:
a.
Combat equipped soldiers: 240 pounds per individual.
　
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