Difference between revisions of "S-92/Weight and Balance"
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| + | <span class=sa-section>SECTION 5. WEIGHT AND BALANCE</span> | ||
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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 nose. | 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 nose. | ||
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===CG ARM DATA=== | ===CG ARM DATA=== | ||
The following arm data can be used to calculate moment at each of these stations. | The following arm data can be used to calculate moment at each of these stations. | ||
| − | Pilot/Co-Pilot 100.0 in (2.56 m) | + | |
| − | Jumpseat 182.0 in (4.67 m) | + | {|class=wikitable |
| − | Row 1 221.7 in (5.68 m) | + | !Item |
| − | Sponson Baggage 221.7 in (5.68 m) | + | !Limit |
| − | Row 2 283.5 in (7.27 m) | + | |- |
| − | Fuel 307.2 in (7.88 m) | + | |Pilot/Co-Pilot ||100.0 in (2.56 m) |
| − | Row 3 324.0 in (8.31 m) | + | |- |
| − | Row 4 397.6 in (10.19 m) | + | |Jumpseat ||182.0 in (4.67 m) |
| − | Rear Baggage 438.2 in (11.24 m) | + | |- |
| + | |Row 1 ||221.7 in (5.68 m) | ||
| + | |- | ||
| + | |Sponson Baggage ||221.7 in (5.68 m) | ||
| + | |- | ||
| + | |Row 2 ||283.5 in (7.27 m) | ||
| + | |- | ||
| + | |Fuel ||307.2 in (7.88 m) | ||
| + | |- | ||
| + | |Row 3 ||324.0 in (8.31 m) | ||
| + | |- | ||
| + | |Row 4 ||397.6 in (10.19 m) | ||
| + | |- | ||
| + | |Rear Baggage ||438.2 in (11.24 m) | ||
| + | |} | ||
===WEIGHT AND CG CALCULATION=== | ===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. | 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. | ||
Latest revision as of 01:15, 3 August 2021
SECTION 5. WEIGHT AND BALANCE
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 nose.
1 WEIGHT AND CG LIMITS
The weight and CG limits for this aircraft are:
| Item | Limit |
|---|---|
| Max Gross Weight: | 26,500 lb |
| Max Forward CG: | 103 inches |
| Max Aft CG: | 111 inches |
2 EMPTY WEIGHT AND CG
The empty weight and CG of this aircraft are:
| Item | Limit |
|---|---|
| Empty Weight: | 16,520 lb |
| Empty Aircraft CG: | 314.7 in |
| Empty Moment: | 5.199 M-lb-in |
3 CG ARM DATA
The following arm data can be used to calculate moment at each of these stations.
| Item | Limit |
|---|---|
| Pilot/Co-Pilot | 100.0 in (2.56 m) |
| Jumpseat | 182.0 in (4.67 m) |
| Row 1 | 221.7 in (5.68 m) |
| Sponson Baggage | 221.7 in (5.68 m) |
| Row 2 | 283.5 in (7.27 m) |
| Fuel | 307.2 in (7.88 m) |
| Row 3 | 324.0 in (8.31 m) |
| Row 4 | 397.6 in (10.19 m) |
| Rear Baggage | 438.2 in (11.24 m) |
4 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.
