Difference between revisions of "Steamly S2-S/Weight and Balance"
(→WEIGHT AND CG LIMITS) |
(→WEIGHT AND CG LIMITS) |
||
| (7 intermediate revisions by the same user not shown) | |||
| Line 13: | Line 13: | ||
!Limit | !Limit | ||
|- | |- | ||
| − | |Max Gross Weight: ||2, | + | |Max Gross Weight: ||2,100 lb |
|- | |- | ||
|Max Forward CG: ||118 inches | |Max Forward CG: ||118 inches | ||
| Line 23: | Line 23: | ||
=== EMPTY WEIGHT AND CG === | === EMPTY WEIGHT AND CG === | ||
| − | The empty weight and CG of this aircraft are: | + | The empty weight and CG of this aircraft are (Empty aircraft weight includes full water level in boiler with empty reservoir and fuel tank): |
{| class=wikitable | {| class=wikitable | ||
| Line 29: | Line 29: | ||
!Limit | !Limit | ||
|- | |- | ||
| − | |Empty Weight: || | + | |Empty Weight: ||1,294 lb |
|- | |- | ||
| − | |Empty Aircraft CG: || | + | |Empty Aircraft CG: ||122.8 in |
|- | |- | ||
| − | |Empty Moment: ||1. | + | |Empty Moment: ||1.58 M-lb-in |
|} | |} | ||
| Line 43: | Line 43: | ||
!Limit | !Limit | ||
|- | |- | ||
| − | |Pilot/Co-Pilot || | + | |Pilot/Co-Pilot ||79 in (2.01 m) |
|- | |- | ||
| − | |Fuel || | + | |Fuel || 114 in (2.89 m) |
|- | |- | ||
| − | |Water Reservoir|| | + | |Water Reservoir|| 139 in (3.53 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 | + | Total weight is calculated by adding total weight of empty aircraft, fuel, passengers and baggage. Fuel weight can be calculated assuming 7.0 pounds per gallon of medium fuel oil. Water in the reservoir can be assumed to weight 8.3 pounds/gallon. 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 12:52, 5 May 2022
SECTION 7. 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 at the tip of the pitot tubes.
2 WEIGHT AND CG LIMITS
The weight and extreme CG limits for this aircraft are:
| Item | Limit |
|---|---|
| Max Gross Weight: | 2,100 lb |
| Max Forward CG: | 118 inches |
| Max Aft CG: | 127 inches |
Not withstanding the maxmimum limits shown above, the helicopter should only be operated within the weight vs CG envelope shown in .
3 EMPTY WEIGHT AND CG
The empty weight and CG of this aircraft are (Empty aircraft weight includes full water level in boiler with empty reservoir and fuel tank):
| Item | Limit |
|---|---|
| Empty Weight: | 1,294 lb |
| Empty Aircraft CG: | 122.8 in |
| Empty Moment: | 1.58 M-lb-in |
4 CG ARM DATA
The following arm data can be used to calculate moment at each of these stations.
| Item | Limit |
|---|---|
| Pilot/Co-Pilot | 79 in (2.01 m) |
| Fuel | 114 in (2.89 m) |
| Water Reservoir | 139 in (3.53 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 7.0 pounds per gallon of medium fuel oil. Water in the reservoir can be assumed to weight 8.3 pounds/gallon. 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.
