Chinook CH-47/Weight and Balance

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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.