Chinook CH-47/Weight and Balance - Revision history

Kelly at 21:24, 20 June 2021

2021-06-20T21:24:18Z

Kelly: /* CG ARM DATA */

2021-06-20T20:23:41Z

‎CG ARM DATA

Kelly: /* EMPTY WEIGHT AND CG */

2021-06-20T20:21:12Z

‎EMPTY WEIGHT AND CG

Kelly: 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..."

2021-06-20T20:19:50Z

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..."

New page

=== 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:
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 .

=== 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

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

Item Station
Pilot/Co-Pilot 84 in (2.13 m)
Troop #1 & #16 202 in ( m)
Troop #2 & #17 224 in ( m)
Troop #3 & #18 249 in ( m)
Troop #4 & #19 274 in ( m)
Troop #5 & #20 296 in ( m)
Troop #6 & #21 320 in ( m)
Troop #7 & #22 344 in ( m)
Troop #8 & #23 367 in ( m)
Troop #9 & #24 390 in ( m)
Troop #10 & #25 415 in ( m)
Troop #11 & #26 438 in ( m)
Troop #12 & #27 461 in ( m)
Troop #13 & #28 485 in ( m)
Troop #14 & #29 509 in ( m)
Troop #15 & #30 532 in ( m)
Fwd Tanks 260 in ( m)
Main Tanks 386 in ( m)
Aft Tanks 504 in ( m)
Fwd Hook 277 in ( m)
Mid Hook 267 in ( m)
Aft Gook 486 in ( 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 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.

← Older revision		Revision as of 21:24, 20 June 2021
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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.

@@ Line 27: / Line 27: @@
 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)
+! Arm (in.)
-Troop #1 & #16	202 in ( m)
+|-
-Troop #2 & #17	224 in ( m)
+|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)
+|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)
+|-
 === 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.

@@ Line 12: / Line 12: @@
 === EMPTY WEIGHT AND CG ===
 The empty weight and CG of this aircraft are:
 Item	Value
-Empty Weight:	24,577 lb
+{| class=wikitable
-Empty Aircraft CG:	353.5 in
+! Item
-Empty Moment:	8.69 M-lb-in
+! Value
 === CG ARM DATA ===