Difference between revisions of "Steamly S2-S/Weight and Balance"

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(WEIGHT AND CG LIMITS)
(WEIGHT AND CG LIMITS)
 
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!Limit
 
!Limit
 
|-
 
|-
|Max Gross Weight: ||2,000 lb
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|Max Gross Weight: ||2,100 lb
 
|-
 
|-
|Max Forward CG: ||157 inches
+
|Max Forward CG: ||118 inches
 
|-
 
|-
|Max Aft CG:         ||177 inches
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|Max Aft CG:         ||127 inches
 
|}
 
|}
  
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=== 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
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!Limit
 
!Limit
 
|-
 
|-
|Empty Weight: ||7,645 lb
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|Empty Weight: ||1,294  lb
 
|-
 
|-
|Empty Aircraft CG: ||167.7 in
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|Empty Aircraft CG: ||122.8 in
 
|-
 
|-
|Empty Moment: ||1.28 M-lb-in
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|Empty Moment: ||1.58 M-lb-in
 
|}
 
|}
  
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!Limit
 
!Limit
 
|-
 
|-
|Pilot/Co-Pilot ||119 in (3.02 m)
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|Pilot/Co-Pilot ||79 in (2.01 m)
 
|-
 
|-
|Fuel || 168 in (4.26 m)
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|Fuel || 114 in (2.89 m)
 
|-
 
|-
|Water Reservoir|| 174 in (4.42 m)
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|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 5.8 pounds per gallon of (100LL) 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 7.0 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

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.