Kelly: /* CG ARM DATA */

2022-04-12T03:59:13Z

‎CG ARM DATA

Kelly: Created page with " SECTION 7. WEIGHT AND BALANCE === General === The helicopter must be flown within the weight and CG (Center of Gravity) limits as specified in..."

2022-04-12T03:58:28Z

Created page with " <span class=sa-section>SECTION 7. 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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<span class=sa-section>SECTION 7. WEIGHT AND BALANCE</span>

=== 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.

=== WEIGHT AND CG LIMITS ===
The weight and extreme CG limits for this aircraft are:

{| class=wikitable
!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 .

=== EMPTY WEIGHT AND CG ===
The empty weight and CG of this aircraft are:

{| class=wikitable
!Item
!Limit
|-
|Empty Weight: ||7,645 lb
|-
|Empty Aircraft CG: ||167.7 in
|-
|Empty Moment: ||1.28 M-lb-in
|}

=== CG ARM DATA ===
The following arm data can be used to calculate moment at each of these stations.

{| class=wikitable
!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)
|}

=== 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.

@@ Line 44: / Line 44: @@
 |-
 |Pilot/Co-Pilot	||119 in (3.02 m)
 |-
 |Fuel || 168 in (4.26 m)
 |-
-|Winch || 174 in (4.42 m)
+|Water Reservoir|| 174 in (4.42 m)
 |}
 === 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.

S2-S/Weight and Balance - Revision history

Kelly: /* CG ARM DATA */

Kelly: Created page with " SECTION 7. WEIGHT AND BALANCE === General === The helicopter must be flown within the weight and CG (Center of Gravity) limits as specified in..."