Difference between revisions of "Chinook CH-47/Weight and Balance"

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(Created page with "=== 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 resu...")
 
 
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<span class=sa-section>SECTION 6. WEIGHT AND BALANCE</span>
 
=== General ===
 
=== 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.
 
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.
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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:
−
Item Value
+
 
−
Empty Weight: 24,577 lb
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{| class=wikitable
−
Empty Aircraft CG: 353.5 in
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! Item
−
Empty Moment: 8.69 M-lb-in
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! Value
 +
|-
 +
|Empty Weight ||24,577 lb
 +
|-
 +
|Empty Aircraft CG ||353.5 in
 +
|-
 +
|Empty Moment ||8.69 M-lb-in
 +
|}
  
 
=== 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.
  
−
 
+
{| class=wikitable
−
Item Station
+
! Station
−
Pilot/Co-Pilot 84 in (2.13 m)
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! Arm (in.)
−
Troop #1 & #16 202 in ( m)
+
|-
−
Troop #2 & #17 224 in ( m)
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|Pilot/Co-Pilot ||84
−
Troop #3 & #18 249 in ( m)
+
|-
−
Troop #4 & #19 274 in ( m)
+
|Troop #1 & #16 ||202
−
Troop #5 & #20 296 in ( m)
+
|-
−
Troop #6 & #21 320 in ( m)
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|Troop #2 & #17 ||224
−
Troop #7 & #22 344 in ( m)
+
|-
−
Troop #8 & #23 367 in ( m)
+
|Troop #3 & #18 ||249
−
Troop #9 & #24 390 in ( m)
+
|-
−
Troop #10 & #25 415 in ( m)
+
|Troop #4 & #19 ||274
−
Troop #11 & #26 438 in ( m)
+
|-
−
Troop #12 & #27 461 in ( m)
+
|Troop #5 & #20 ||296
−
Troop #13 & #28 485 in ( m)
+
|-
−
Troop #14 & #29 509 in ( m)
+
|Troop #6 & #21 ||320
−
Troop #15 & #30 532 in ( m)
+
|-
−
Fwd Tanks 260 in ( m)
+
|Troop #7 & #22 ||344
−
Main Tanks 386 in ( m)
+
|-
−
Aft Tanks 504 in ( m)
+
|Troop #8 & #23 ||367
−
Fwd Hook 277 in ( m)
+
|-
−
Mid Hook 267 in ( m)
+
|Troop #9 & #24 ||390
−
Aft Gook 486 in ( m)
+
|-
 +
|Troop #10 & #25 ||415
 +
|-
 +
|Troop #11 & #26 ||438
 +
|-
 +
|Troop #12 & #27 ||461
 +
|-
 +
|Troop #13 & #28 ||485
 +
|-
 +
|Troop #14 & #29 ||509
 +
|-
 +
|Troop #15 & #30 ||532
 +
|-
 +
|Fwd Tanks ||260
 +
|-
 +
|Main Tanks ||386
 +
|-
 +
|Aft Tanks ||504
 +
|-
 +
|Fwd Hook ||277
 +
|-
 +
|Mid Hook ||267
 +
|-
 +
|Aft Hook ||486
 +
|}
  
 
=== 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 21:24, 20 June 2021

SECTION 6. 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: 50,000 lb Max Forward CG: 340 inches Max Aft CG: 380 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 Value
Empty Weight 24,577 lb
Empty Aircraft CG 353.5 in
Empty Moment 8.69 M-lb-in

4 CG ARM DATA

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

Station Arm (in.)
Pilot/Co-Pilot 84
Troop #1 & #16 202
Troop #2 & #17 224
Troop #3 & #18 249
Troop #4 & #19 274
Troop #5 & #20 296
Troop #6 & #21 320
Troop #7 & #22 344
Troop #8 & #23 367
Troop #9 & #24 390
Troop #10 & #25 415
Troop #11 & #26 438
Troop #12 & #27 461
Troop #13 & #28 485
Troop #14 & #29 509
Troop #15 & #30 532
Fwd Tanks 260
Main Tanks 386
Aft Tanks 504
Fwd Hook 277
Mid Hook 267
Aft Hook 486

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 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.

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