Difference between revisions of "H-160/Weight and Balance"
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===GENERAL=== | ===GENERAL=== | ||
The helicopter must be flown within the weight and CG (Center of Gravity) limits as specified in this section. Failure to adhere to these limitations will result in unpredictable performance. CG is measured in inches aft of the datum plane. The datum plane is located at the forward most point of the aircraft body. | The helicopter must be flown within the weight and CG (Center of Gravity) limits as specified in this section. Failure to adhere to these limitations will result in unpredictable performance. CG is measured in inches aft of the datum plane. The datum plane is located at the forward most point of the aircraft body. | ||
Latest revision as of 04:13, 23 October 2021
SECTION 5. WEIGHT AND BALANCE
Contents
1 GENERAL
The helicopter must be flown within the weight and CG (Center of Gravity) limits as specified in this section. Failure to adhere to these limitations will result in unpredictable performance. CG is measured in inches aft of the datum plane. The datum plane is located at the forward most point of the aircraft body.
2 WEIGHT AND CG LIMITS
The weight and extreme CG limits for this aircraft are:
| Item | Limit |
|---|---|
| Max Gross Weight: | 12,500 lb |
| Max Forward CG: | 220 inches |
| Max Aft CG: | 240 inches |
Not withstanding the maximum limits shown above, the helicopter should only be operated within the weight vs CG envelope shown in Figure 1.
3 EMPTY WEIGHT AND CG
The empty weight and CG of this aircraft are:
| Item | Value |
|---|---|
| Empty Weight: | 9,384 lb |
| Empty Aircraft CG: | 236.6 in |
| Empty Moment: | 2.22 M-lb-in |
4 CG ARM DATA
The following arm data can be used to calculate moment at each of these stations.
| Item | Station |
|---|---|
| Pilot/Co-Pilot | 108 in (2.77 m) |
| Passenger (Row 1) | 151 in (3.86 m) |
| Passenger (Row 2) | 189 in (4.84 m) |
| Passenger (Row 3) | 225 in (5.77 m) |
| Main Tanks | 253 in (6.49 m) |
| Baggage | 269 in (6.90 m) |
5 WEIGHT AND CG CALCULATION
Total weight is calculated by adding total weight of empty aircraft, fuel, passengers and baggage. Fuel weight can be calculated assuming 7 pounds per gallon of (Jet-A) fuel. The CG is obtained by dividing total moment by total weight. Moment at each station is obtained by multiplying the arm of that station by the weight at that station. Total moment is obtained by adding moment for each station and the moment for the empty aircraft.
