Difference between revisions of "H-34 Choctaw/Weight and Balance"

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(Created page with " <span class=sa-section>SECTION 5. WEIGHT AND BALANCE</span> === General === The helicopter must be flown within the weight and CG (Center of Gravity) limits as specified in...")
 
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!Limit
 
!Limit
 
|-
 
|-
−
|Max Gross Weight: ||22,050 lb
+
|Max Gross Weight: ||14,400 lb
 
|-
 
|-
−
|Max Forward CG: ||235 inches
+
|Max Forward CG: ||157 inches
 
|-
 
|-
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|Max Aft CG:         ||251 inches
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|Max Aft CG:         ||177 inches
 
|}
 
|}
  
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!Limit
 
!Limit
 
|-
 
|-
−
|Empty Weight: ||13,341lb
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|Empty Weight: ||7,645 lb
 
|-
 
|-
−
|Empty Aircraft CG: ||240.8in
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|Empty Aircraft CG: ||167.7 in
 
|-
 
|-
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|Empty Moment: ||3.21 M-lb-in
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|Empty Moment: ||1.28 M-lb-in
 
|}
 
|}
  
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!Limit
 
!Limit
 
|-
 
|-
−
|Pilot/Co-Pilot ||73 in (1.85 m)
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|Pilot/Co-Pilot ||119 in (3.02 m)
 
|-
 
|-
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|Winch || 136 in (3.46 m)
+
|Hoist Operator || 147in (3.74 m)
 
|-
 
|-
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|RDF Operator || 145 in (3.68 m)
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|Hook || 168 in (4.26 m)
 
|-
 
|-
−
|Hoist Operator || 150 in (3.82 m)
+
|Fuel || 168 in (4.26 m)
 
|-
 
|-
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|Utility Seat #1 || 243 in (6.17 m)
+
|Winch || 174 in (4.42 m)
 
|-
 
|-
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|Fuel || 262 in (6.67 m)
+
|Utility Seat #1 || 165 in (4.19 m)
 
|-
 
|-
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|Hook || 264 in (6.72 m)
+
|Utility Seat #2 || 182 in (4.63 m)
 
|-
 
|-
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|Utility Seat #2 || 269 in (6.83 m)
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|Utility Seat #3 || 204 in (5.19 m)
 
|-
 
|-
−
|Utility Seat #3 || 295 in (7.50 m)
+
|Utility Seat #4 || 234 in (5.95 m)
 
|-
 
|-
−
|Utility Seat #4 || 320 in (8.12 m)
+
|Utility Seat #5 || 250 in (6.36 m)
 
|-
 
|-
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|Litter/Stokes Basket || 345 (8.78 m)
+
|Utility Seat #6 || 270 in (6.88 m)
−
|-
 
−
|Ramp || 458 (11.63 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 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.

Latest revision as of 02:59, 10 July 2021

SECTION 5. 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: 14,400 lb
Max Forward CG: 157 inches
Max Aft CG: 177 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:

Item Limit
Empty Weight: 7,645 lb
Empty Aircraft CG: 167.7 in
Empty Moment: 1.28 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 119 in (3.02 m)
Hoist Operator 147in (3.74 m)
Hook 168 in (4.26 m)
Fuel 168 in (4.26 m)
Winch 174 in (4.42 m)
Utility Seat #1 165 in (4.19 m)
Utility Seat #2 182 in (4.63 m)
Utility Seat #3 204 in (5.19 m)
Utility Seat #4 234 in (5.95 m)
Utility Seat #5 250 in (6.36 m)
Utility Seat #6 270 in (6.88 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 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.

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