Table of Gontents
Weight and Balance
General 4
Preparing Helicopter for Weighing 5
Weight Record 6
Computing Preliminary Empty Weight CG 7
Empty Weight CG Limits 8
Ballast Determination 10
Compute Final Empty Weight 13
Review 15
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WEIGHT AND BALANCE
Terminal Objective
At the end of this lesson the student will be able to level, weigh, and describe weight
and balance calculations.
Enabling Objectives
o Describe weight and balance procedures.
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WEIGHT AND BALANCE
FS 01 FS FS
55.16 377.18
FORWARD TAIL ROTOR
JACKING POINT CENTERLINE
General
Center of gravity (CG) is the term used to define the balance point of a body for
weight and balance purposes.
A helicopter can be compared with a pendulum, the point of suspension being where
the main rotor hub intersects the mast and the pendulum weight being the
helicopter. lf the pendulum weight is allowed to stop it comes to rest with its CG
directly below the suspension point.
Fuselage station 0 is referred to as the datum for weight and balance purposes. All
changes to the CG of an aircraft are measures from this point.
For example, if the CG of a helicopter is aft of the hub/mast intersection, the
helicopter is tail down in flight. The pilot can correct this condition by moving the
cyclic control stick forward. However, the greater the required movement of the stick
the less control power is available for forward speed and maneuverability. Since
such loss of maneuverability is unsafe, care must always be taken to keep the
helicopter CG within specified gross weight flight limits. This is accomplished in two
ways:
1. Moving the location of the helicopter weight empty CG through addition or
deletion of ballast.
2. Computing the combinations of useful load items which are allowable for each
flight.
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WEIGHT AND BALANCE
Preparing Helicopter for Weighing
Accomplish the following procedures prior to weighing to ensure the configuration is
as near weight empty as possible:
1. Remove excessive dirt, grease, moisture, and non-weight empty items from
the helicopter.
2. Ensure baggage comparlment is empty.
3. Add all kits and other weight empty items in their proper locations.
4. Ensure transmission, gearbox, and hydraulics reservoirs are full.
5. Drain the fuel system at ground attitude.
6. Drain the engine oil system where possible; if not, ensure that system is full.
7. Jack and level the helicopter.
NOTE
Empty Weight configuration is the basic helicopter plus kits, special equipment, fixed
ballast, transmission and gearbox oil, hydraulic fluid, unusable fuel, and undrainable
oil.
Weight and balance information for the specific helicopter can be found in the flight
manual.
Notes
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WEIGHT AND BALANCE
Weight Record
BELL H ELICOPTER TEXTRON
ACTUAL WEIGHT RECORD
MODEL 2O6L-4
DATE WEIGHED: SERIAL NUMBER: SAMPI F
ILONGITUOINAL CG, AS WEIGHED
ss.16 ( 1'1s3"0) + 204.52 ( 1212.0 | 31 1 S63
CG= 't 31.9'l INCHES
TOTAL WEIGHT 2365.0
LATERAL CG, AS WEIGHED'
-16.82 (567.0) +'16.82 ( s86.0 ) s20
cG= +O,14 INCHES
TOTAL WEIGHT 2365.0
. IN TATERAL CALCULATIONS - IS LEFT + IS RIGHT
MOST FWD CG
A/EIGHT EMPTY
+PILOT
2393.1 129.4 310714 0.1 265
/U.U tt5.o 1 1050 1,1.0 2;l6lJ
+PASSENGER (I} FWD 170.0 65.0 1't 050
+PASSENGERS (2) MID 340.O !il.u 3(,940 0.o o
+PASSENGERS (2) AFT 340.O 129.0 43660 0.o 0
+O]L, ENGINE 13.O zu5.u 2665 0.o o
+FUEL, MOST FWD (59.9 GAL) JP.s 407.3 1ftt 47E96 0.0 U
3833 4 119.5 454177 9.2 T15
MOST AFT CG
WEIGHT EMPTY
+PILO I
2393.1 129.E I 310714 u.l 265
170.O 65.0 11()50 t4. 23EO
+PASSENGERS (2) AFT 340.O 129.0 43460 0 o
+OII. ENGINE 13.O 205.O 2665 o.o
+FUEL, ('1O.7 GAL) JP.s 752.8 13',1.7 99144 o.o
3668.9 127.1 467433 o.7 2645
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WEIGHT AND BALANCE
Computing Preliminary Empty Weight CG
Prior to determining ballast requirements, the as-weighed weight must be convefted
to a preliminary empty weight condition on which to base balance calculations.
Stading with the as-weighed weight, CG, and moment, pedorm the following:
Add all empty weight items not on the helicopter when weighed.
Remove all non-weight empty items on the helicopter when weighed, such as, plumb
bob, spirits level, engine oil, and undrainable fuel.
Example
As-Weighed 131.91
REMOVED
Engine Oil -13.0 205.0 -2665
Plumb bob -0.3 117.7 -35
ADDED
' Undrainable Oil 192.0
Unusable Fuel
.94.0
PRELIMINARY EMPTY 131.42
WEIGHT
UNDRAINABLE ENGINE OIL
Weight CG Moment
oil (LB) (tN) (rN -LB)
DOD-L-85734 1.6 192 307
M lL-L-7808 1.4 192 269
MtL-L-236ee 1.6 192 307
|,.
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WEIGHT AND BALANCE
Empty Weight CG Limits
2900
(1315.4)
\
\
2800
11270.0) \ \
\
2700
(1224.7) \
6 \ \ A FT LIMI'I
I
t(9= VI =R ONL]
I
o
2600
\
=_
o
o
(117e.3)
z
l I \
o
o.
I
2500
\ \
o.
(1134.0)
uJ
I
o
uJ \
= 2400
\
(1088.6)
\
\ \
2300
\
(1043.3)
fr )Rt/l IARI )-
LIN IT
\
-,AF ,rl',rL
vr r\AI lIJ I 1I
tFr rONLY \
\
2200
(ee7.e)
127 128 129 130 131
(32261 (3251) (3277) (3302) (33271
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1
- For Training Purposes Only
WEIGHT AND BALANCE
Empty Weight CG Limits
When a helicopter has a standard fuel system and standard seating arrangement,
the empty weight CG limits may be used as a guide to properly ballast the
helicopter. The chart was derived using the selective passenger loading schedule
shown on the cockpit placard.
Never allow ballast to be installed in both the nose and tailboom locations at the
same time.
lf the weight exceeds the maximum shown on the chart or if the helicopter fuel
system or seating arrangement is non-standard, install the alternate cockpit placard
and compute ballast using gross weight flight limits.
NOTE
It is prohibited to extend the empty weight and balance charl limits if the empty
weight of the aircraft exceeds charl limits.
Notes
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WEIGHT AND BALANCE
Ballast Determination
2068
FS 29.8 FS 345.7
MAXIMUM BALIAST = 20 lbs. AFT PLATES MAXIMUMBALIAST=9lbs.
FS 18.6
MAXIMUM BALLAST = 22lbs. 206 4s1 -237 -17 (3. 5 lbs.) 236 -031 -237 -17 {3. 5 lbs.)
206 .0.31 -237 -13 (6.0 lbs.)
2OO -031 -237 -1 5 (3.0 lbs.) COCKPIT BALIAST PLATES
FORWARD BALLAST PIATES
AFT BALLAST PTATES
FS 341.0
MAXIMUM BALLAST = 18 lbs.
206 -031 -422431 (3.5 lbs.)
206 .{31 -422-A29 (2.0 lbs.)
GOCKPIT BALI-AST
PLATES
?r- MAXIMUM BALI-AST = 30 lbs.
\ 206431-237-109 (5.0 lbs.)
-\
FORWARD BALI.AST
A S/N 4129 AND SUB
PI.ATES
A S/N 3907AND SUB
FS 13.0
A s/N 2212 - 3906
MAXIMUM BALIAST = 28 lbs.
206431-205-007 (2.9 lbs.) A S/N 3567AND SUB
A MAXIMUM BALI.ASTTHIS LOCATION
tr RESTRICTED TO 18 lbs. WTH 17 AMP
BATTERY INSTALLED.
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WEIGHT AND BALANCE
206L
FS 29.8
MAXIMUM BALLAST = 1O.O Ib.
FS 16.4 206431 -237 -117 (3.5 tb.)
MAXIMUM BALLAST = 22lb. 3 PER SIDE
206 -031 -237 -1 1 3 (6.0 I b.)
206-031 -237 -1 15 (3.0 I b.)
FS 283.6 AND FS 294.9
2064s3427 -123 (1.0 tb.)
FS 282.7 AND FS 291.3
MAXIMUM BALLAST = 10 lb.
206-033 427 -1 19 (6,0 tb.)
206-033427 -121 (3.0 tb.)
FS 35.8
FS 13.0 MAXIMUM BALLAST = 15.0 lb.
MAXIMUM BALLAST = 28 lb. 206-031 -237 -109 (5.0 LB.)
206-031-205-007 (2.9 tb.)
Note
It is not recommended to have ballast installed in the nose and tailboom locations at
the same time.
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WEIGHT AND BALANCE
Ballast Determination
Exact ballast determination may require more than one computation since ballast
weight has a maximum amount allowable at each location.
2068 Example
Required Ballast = (Empty Weiqht) (Required CG - Derived CG)
(Ballast Location - Required CG)
Required Ballast = (1754.9) (116.2 - 118.1)
(1s.0 - 116.2)
Required Ballast = 32 pounds
206L Example
Required Ballast = (Empty Weiqht) (Required CG - Derived CG)
(Ballast Location - Required CG)
Required Ballast = (2360.9) (129.8 - 131 .42)
(13.0 - 12e.8)
Required Ballast = 32.7 pounds
Since required ballast exceeds maximum, revise preliminary empty weight and
recompute required ballast.
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WEIGHT AND BALANCE
Compute Final Empty Weight
2OOB Example
Preliminary Empty Weight
ADD
Ballast @ F.S. 13.0
Ballast @ F.S. 16.4
FINAL EMPTY WEIGHT
206L Example
Preliminary Empty Weight
ADD
Ballast @ F.S. 13.0
Ballast @ F.S. 16.4
FINAL EMPTY WEIGHT 310714
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WEIGHT AND BALANCE
Ballast Installation
Ballast weights are manufactured from lead sheet and vary in thickness from 1/16
inch (1.58 mm) lo1l4 inch (6.35 mm).Each ballast plate is impression stampedwith
its weight. Ballast plates require specialized support assemblies, brackets, or
hardware to be installed: refer to BHT-206 Series lPBs. Ballast plates may be
modified to meet ballast requirements without excess weight by contacting Product
Support Engineering.
Notes
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WEIGHT AND BALANCE
Review
1. Weight and balance information for a specific helicopter would be found in the
manual.
2. Fuselage station 0 is referred to as the for weight and
balance purposes.
3. The aircraft must be and prior to
weighing the helicopter to calculate a derived weight and balance change.
4. Previously installed ballast is paft of the
of the aircraft.
5. Empty weight is calculated with the engine oil drained to the
state.
6. When calculating the center of gravity, it is necessary to
the two readings, as they are on
the same arm.
7. lt is to extend the empty weight and balance chaft limits
if the empty weight of the aircraft exceeds the charl limits.
8. It is not recommended to have ballast installed in the
and location at the same time.
9. Each ballast location has its own allowable ballast.
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WEIGHT AND BALANCE
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