BHT-505-FM-1
Section 5
WEIGHT AND
AND BALANCE
BALANCE
WEIGHT
5
TABLE OF CONTENTS
Subject
Paragraph
Number
Page
Number
Introduction ............................................................................................
Empty weight center of gravity.............................................................
Gross weight center of gravity (GW/CG) .............................................
Gross weight cg management..........................................................
Doors open or removed ........................................................................
Door weights and moments..............................................................
Cockpit and cabin loading ....................................................................
Baggage compartment loading ............................................................
Fuel loading............................................................................................
Engine oil................................................................................................
Sample loading problem .......................................................................
5-1 ...........
5-2 ...........
5-3 ...........
5-3-A .......
5-4 ...........
5-4-A .......
5-5 ...........
5-6 ...........
5-7 ...........
5-8 ...........
5-9 ...........
5-3
5-3
5-3
5-3
5-3
5-3
5-4
5-4
5-4
5-4
5-4
Table
Number
Page
Number
5-1 ...........
5-2 ...........
5-3 ...........
5-4 ...........
5-5 ...........
5-6 ...........
5-7 ...........
5-8 ...........
5-9 ...........
5-8
5-10
5-12
5-13
5-14
5-16
5-18
5-19
5-20
Figure
Number
Page
Number
5-1 ...........
5-2 ...........
5-6
5-7
LIST OF TABLES
Subject
Example for Computation of GW/CG (U.S.).........................................
Example for Computation of GW/CG (Metric) .....................................
Door Weights and Moments (U.S.) .......................................................
Door Weights and Moments (Metric) ...................................................
Cabin and Baggage Loading (U.S.) ......................................................
Cabin and Baggage Loading (Metric) ..................................................
Fuel Density Versus Temperature........................................................
Fuel Loading (U.S.) ................................................................................
Fuel Loading (Metric).............................................................................
LIST OF FIGURES
Subject
Fuselage stations - Inches (millimeters)..............................................
Buttock lines - Inches (millimeters) .....................................................
Export Classification C, ECCN EAR99
16 APR 2020 Rev. 6 5-1/5-2
BHT-505-FM-1
Section 5
WEIGHT AND
AND BALANCE
BALANCE
WEIGHT
5
5-1. INTRODUCTION
This section provides loading information and
instructions necessary to ensure that flight
can be performed within the approved gross
weight and center of gravity limitations, as
defined in Section 1 (limitations).
5-2. EMPTY WEIGHT CENTER OF
GRAVITY
Empty Weight (EW) configuration consists of
basic helicopter with required equipment,
operational and special equipment,
transmission and gearbox oils, hydraulic
fluid, engine oil, fixed ballast, and unusable
fuel. The empty weight and center of gravity
are recorded on the Actual Weight Record, a
copy of which should be carried in helicopter
for use in weight and balance calculations.
5-3. GROSS WEIGHT CENTER OF
GRAVITY (GW/CG)
Total gross weight of helicopter, with its
contents, includes crew, passengers, fuel,
baggage, and cargo.
5-3-A.
GROSS
WEIGHT
MANAGEMENT
CG
Pilot is responsible to ensure helicopter is
properly loaded so entire flight is conducted
within limits. Refer to Section 1 (limitations) or
appropriate Flight Manual Supplement.
Weight and moment of each component of
helicopter loading is calculated for critical
fuel loadings and verified to within GW/CG
limits.
Export Classification C, ECCN EAR99
Table 5-1 and Table 5-2 are examples for
computation of GW/CG which can be used as
a guide for these calculations. GW and
Longitudinal and lateral CG must be
calculated for each flight from the following:
•
Actual weight record.
•
Diagrams and loading tables.
•
Diagrams and loading tables in
appropriate FMS.
Effects of fuel consumption and addition/
deletion of passengers, baggage, or cargo
should be checked prior to flight to ensure
helicopter is within GW/CG limits for entire
flight.
To aid in weight and balance calculations,
refer to Table 5-1 for fuselage stations and
Figure 5-2 for buttock lines.
5-4. DOORS OPEN OR REMOVED
5-4-A.
DOOR WEIGHTS AND MOMENTS
Following Table 5-3 and Table 5-4 provide
weight and moment adjustments for cabin
doors. Sign convention for buttock lines used
to compute lateral moments are:
1.
Left is negative.
2.
Right is positive.
Example:
When removing the left doors only, substract
positive weight value and negative moment
value shown in table. Net effect on helicopter
is a reduction in weight and a shift in lateral
CG to right (positive direction).
16 APR 2020
Rev. 6
5-3
BHT-505-FM-1
5-5. COCKPIT
LOADING
AND
CABIN
Cockpit and cabin floor is st ructurally
designed for 55 pounds per square foot (2.68
kg/100 cm²), with a maximum allowable
weight of 425 pounds (192.8 kg).
Loading tables provide weights and moments
for the pilot and baggage compartment in
both U.S. and metric units.
5-6. BAGGAGE
LOADING
COMPARTMENT
When weight is loaded into baggage
compartment, the pilot is required to compute
weight and balance, regardless of passenger
loading.
Baggage compartment is structurally
designed for 50 pounds per square foot (2.44
kg/100 cm²) with a maximum allowable weight
of 250 pounds (113.4 kg).
Load shall be secured to tie-down fittings if
shifting of load in flight could result in
structural damage to baggage compartment
or in gross weight center of gravity being
exceeded.
NOTE
Tables and examples should only be
used if reflects actual loading
conditions.
5-7. FUEL LOADING
Fuel is located at a neutral longitudinal CG
position relative to the flight envelope.
Therefore, in most cases, the most critical aft
and forward CG position will occur with a zero
fuel state. In limited cases when loading near
the aft limit, the most aft condition will occur
with full fuel. This is due to the slope of the
heavy aft limit being slightly different than the
slope of the fuel curve. Therefore both fuel
states should be checked.
5-4
Rev. 6
16 APR 2020
NOTE
Because of change in slope of the aft
limit and shape of the fuel burn
curve, there are two critical values
that should be calculated for the aft
extreme, Gross Weight at Zero Fuel
and Gross Takeoff Weight (GTOW) .
Fuel Density Versus Temperature table
(Table 5-7) is provided to calculate fuel
densities for specific temperature in both U.S.
and metric units.
Fuel Loading tables (Table 5-8 and Table 5-9)
list usable fuel quantities, weight and
moments for Jet A and Jet B fuels at 15 °C, in
both U.S. and metric units.
Critical fuel quantities for calculating extreme
CG cases are also presented in Table 5-8 and
Table 5-9.
5-8. ENGINE OIL
Consumption of engine oil has negligible
effect on helicopter weight and CG and is not
included in weight and balance calculations.
5-9. SAMPLE LOADING PROBLEM
A sample loading problem showing derivation
of critical gross weights and center of gravity
locations for a typical mission is presented in
U.S. and metric units.
Compute weight and CG at takeoff and
landing and determine extreme CG conditions
for flight. Refer to Table 5-1 (US) or Table 5-2
(Metric).
Proceed as follows:
1.
Sum all weights and moments of
payload items and helicopter empty
weight to obtain gross weight and
CG at Zero Fuel Weight (ZFW) . Verify
these are within gross weight/CG
limits. Table 5-3 (US) or Table 5-4
(Metric) presents weight, CG and
moment for crew and baggage.
Export Classification C, ECCN EAR99
BHT-505-FM-1
2.
3.
Add appropriate fuel weight and
moment as read directly from fuel
loading table Table 5-8 (US) or
Table 5-9 (Metric) to obtain gross
weight and CG at takeoff. Verify
these are within gross weight/CG
limits.
Add weight and moment of fuel
remaining to ZFW (step 2) to obtain
gross weight and CG at landing
condition. Verify these are within
gross weight/CG limits
Export Classification C, ECCN EAR99
NOTE
The most critical forward CG will
occur with a full passenger cabin
load and a zero fuel state. The most
critical aft CG will occur with empty
cabin load (single pilot) and either a
zero fuel state (most common) or full
fuel state. Both conditions should be
checked to verify they are within
gross weight/CG limits.
16 APR 2020 Rev. 6
5-5
BHT-505-FM-1
FS 37.8 IN.
(960 mm)
FS 103 IN.
(2616 mm)
CREW
FS 98.0 IN.
(2489 mm)
FS 125.9 IN.
(3199 mm)
FS 165.1 IN.
(4193 mm)
PASSENGERS
FS 135.0 IN.
(3429 mm)
FS 180.9 IN.
(4596 mm)
FS 419.6 IN. FS 442.3 IN.
(10658 mm) (11235 mm)
FS 235.5 IN.
(5982 mm)
FS 325.2 IN.
(8259 mm)
Figure 5-1. Fuselage stations - Inches (millimeters)
5-6
Rev. 6
16 APR 2020
Export Classification C, ECCN EAR99
BHT-505-FM-1
RIGHT, AFT PASSENGER
18.5 IN. (470 mm)
PILOT
14 IN. (356 mm)
LEFT, AFT PASSENGER
-18.5 IN. (470 mm)
COPILOT
-13 IN. (-330 mm)
CENTER
0.0
Figure 5-2. Buttock lines - Inches (millimeters)
Export Classification C, ECCN EAR99
16 APR 2020 Rev. 6
5-7
BHT-505-FM-1
Table 5-1. Example for Computation of GW/CG (U.S.)
A helicopter is chartered to transport four passengers of varying weights plus pilot and 60
pounds of baggage on a trip that will require approximately 50 gallons of Jet A fuel (one way).
The pilot will return alone.
Compute weight and center of gravity at takeoff and landing, and determine extreme CG
conditions for both flights.
OUTBOUND FLIGHT
CENTER OF GRAVITY AND MOMENTS
LONGITUDINAL
LATERAL
Item Description
Weight
(LB)
Arm
(IN)
Moment
(IN-LB)
Arm
(IN)
Moment
(IN-LB)
Empty Weight1
2150.0
177.5
381625
0.1
215
+Pilot
180.0
98.0
17640
14.0
2520
+Forward Passenger (Copilot)
165.0
98.0
16170
-13.0
-2145
+Passenger Aft, Left
170.0
135.0
22950
-18.5
-3145
+Passenger Aft, Center
155.0
135.0
20925
0.0
0
+Passenger Aft, Right
185.0
135.0
24975
18.5
3423
60.0
168.0
10080
0.0
0.0
0.3 
868
+Baggage
Gross Weight at Zero
Fuel2.
+Fuel (84.9 gallons) to
Maximum GTOW
3065.0 
577.0
161.3 
166.0
494365
95782
0.0
0
Gross Takeoff Weight (GTOW)3.
3642.0 
162.0 
590147
0.2 
868
Gross Weight at Zero Fuel
3065.0
161.3
494365
0.3
868
237.0
166.4
39433
0.0
0
+Fuel at Landing (34.9 gallons)
Landing Condition
5-8
Rev. 6
16 APR 2020
3302.0 
161.7 
533798
0.3 
868
Export Classification C, ECCN EAR99
BHT-505-FM-1
RETURN FLIGHT
CENTER OF GRAVITY AND MOMENTS
LONGITUDINAL
LATERAL
Item Description
Weight
(LB)
Arm
(IN)
Moment
(IN-LB)
Arm
(IN)
Moment
(IN-LB)
Empty Weight1
2150.0
177.9
381625
0.1
215
180.0
98.0
17640
14.0
2520
2330.0
171.4
399265
1.2
2735
577.0
166.0
95782
0.0
0
+Pilot
Gross Weight at Zero
Fuel2.
+Fuel (84.9 gallons) to
Maximum GTOW
Gross Takeoff Weight (GTOW)3.
2907.0 
170.3 
495047
0.9 
2735
Gross Weight at Zero Fuel
2330.0
171.4
399265
1.2
2735
237.0
166.4
39433
0.0
0
+Fuel at Landing (34.9 gallons)
Landing Condition
2567.0 
170.9 
438698
1.1 
2735
1
Example only. Refer to Actual Weight Record for Empty Weight data.
2
Critical fuel for most forward condition is Zero Fuel.
3
Both Gross Weight at Zero Fuel and Gross Takeoff Weight (GTOW) should be checked for
most aft condition.
 A check of weight and CG values against gross weight center of gravity limits chart shows
that the loading will be within limits throughout flight. In lateral calculations, - is left side
and + is right side.
Export Classification C, ECCN EAR99
16 APR 2020 Rev. 6
5-9
BHT-505-FM-1
Table 5-2. Example for Computation of GW/CG (Metric)
A helicopter is chartered to transport four passengers of varying weights plus pilot and 27
kilograms of baggage on a trip that will require approximately 189 liters of Jet A fuel (one way).
The pilot will return alone.
Compute weight and center of gravity at takeoff and landing, and determine extreme CG
conditions for both flights.
OUTBOUND FLIGHT
CENTER OF GRAVITY AND MOMENTS
LONGITUDINAL
Item Description
LATERAL
Weight
(Kg)
Arm
(mm)
Moment
(kg-mm)
Arm
(mm)
Moment
(kg-mm)
975.2
4509
4397177
3
2926
+Pilot
81.6
2489
203102
356
29050
+Forward Passenger (Copilot)
74.8
2489
186177
-330
-24684
+Passenger Aft, Left
77.1
3429
264376
-470
-362
+Passenger Aft, Center
70.3
3429
241059
0
0
+Passenger Aft, Right
83.9
3429
287693
470
394
+Baggage
27.2
4267
116062
0
0
Empty Weight1
Gross Weight at Zero
Fuel2.
+Fuel (321 Liters) to Maximum
GTOW
1390.1 
261.7
4097 
5695647
5 
4216
1103327
0
7320
0
Gross Takeoff Weight (GTOW)3.
1651.8 
4116 
6798974
4 
7323
Gross Weight at Zero Fuel
1390.1
4097
5695647
5
7323
107.5
4227
454403
0
0
+Fuel at Landing (34.9 gallons)
Landing Condition
5-10
Rev. 6
16 APR 2020
1497.6 
4107 
6150049
5 
7323
Export Classification C, ECCN EAR99
BHT-505-FM-1
RETURN FLIGHT
CENTER OF GRAVITY AND MOMENTS
LONGITUDINAL
Item Description
Weight
(kg)
Arm
(mm)
Moment
(kg-mm)
Arm
(mm)
Moment
(kg-mm)
975.2
4509
4397177
3
2926
81.6
2489
203102
356
29050
1056.8
4353
4600279
30
31975
261.7
4216
1103327
0
0
Empty Weight1
+Pilot
Gross Weight at Zero
LATERAL
Fuel2.
+Fuel (321Liters) to Maximum
GTOW
Gross Takeoff Weight (GTOW)3.
1318.5 
4326 
5703606
24 
31975
Gross Weight at Zero Fuel
1056.8
4353
4600279
30
31975
107.5
4227
454403
0
0
4341 
438698
+Fuel at Landing (132 Liters)
Landing Condition
1164.3 
1.1 
2735
1
Example only. Refer to Actual Weight Record for actual empty weight data.
2
Critical fuel for most forward condition is Zero Fuel.
3
Both Gross Weight at Zero Fuel and Gross Takeoff Weight (GTOW) should be checked for
most aft condition.
 A check of weight and CG values against gross weight center of gravity limits chart shows
that the loading will be within limits throughout flight. In lateral calculations, - is left side
and + is right side.
Export Classification C, ECCN EAR99
16 APR 2020 Rev. 6
5-11
BHT-505-FM-1
Table 5-3. Door Weights and Moments (U.S.)
LONGITUDINAL
DOOR
LATERAL
WEIGHT
CG
MOMENT
CG
MOMENT
(LB)
(IN.)
(IN•LB)
(IN.)
(IN•LB)
One crew door
18.1
112.0
2027
±28.6
±518
Both crew doors
36.2
112.0
4057
0
0
Clamshell passenger door
6.3
136.3
859
-28.8
-181
5-12
Rev. 6
16 APR 2020
Export Classification C, ECCN EAR99
BHT-505-FM-1
Table 5-4. Door Weights and Moments (Metric)
LONGITUDINAL
DOOR
LATERAL
WEIGHT
CG
MOMENT
CG
MOMENT
(KG)
(MM)
(KG•MM)
(MM)
(KG•MM)
One crew door
8.2
2845
23356
±726
±5964
Both crew doors
16.4
2845
46570
0
0
Clamshell passenger door
2.9
3462
9893
-732
-2090
Export Classification C, ECCN EAR99
16 APR 2020 Rev. 6
5-13
BHT-505-FM-1
Table 5-5. Cabin and Baggage Loading (U.S.)
Table of moments (inch•pound)
5-14
Weight
Pilot and Copilot
Aft Row
Baggage Center
(LB)
FS 98
FS 135
FS 168
10
980
1350
1680
20
1960
2700
3360
30
2940
4050
5040
40
3920
5400
6720
50
4900
6750
8400
60
5880
8100
10080
70
6860
9450
11760
80
7840
10800
13440
90
8820
12150
15120
100
9800
13500
16800
110
10780
14850
18480
120
11760
16200
20160
130
12740
17550
21840
140
13720
18900
23520
150
14700
20250
25200
160
15680
21600
26880
170
16660
22950
28560
180
17640
24300
30240
190
18620
25650
31920
200
19600
27000
33600
210
20580
28350
35280
220
21560
29700
36960
230
22540
31050
38640
240
23520
32400
40320
250
24500
33750
42000
260
25480
35100
270
26460
36450
Rev. 6
16 APR 2020
Export Classification C, ECCN EAR99
BHT-505-FM-1
Table 5-5. Cabin and Baggage Loading (U.S.) (Cont)
Table of moments (inch•pound)
Weight
Pilot and Copilot
Aft Row
Baggage Center
(LB)
FS 98
FS 135
FS 168
280
27440
37800
290
28420
39150
300
29400
40500
310
30380
41850
320
31360
43200
330
32340
44550
340
33320
45900
350
34300
47250
360
35280
48600
370
36260
49950
380
37240
51300
390
38220
52650
400
39200
54000
410
40180
55350
420
41160
56700
430
42140
58050
440
43120
59400
450
44100
60750
460
45080
62100
470
46060
63450
480
47040
64800
490
48020
66150
500
49000
67500
510
49980
68850
520
50960
70200
530
51940
71550
540
52920
72900
Export Classification C, ECCN EAR99
16 APR 2020 Rev. 6
5-15
BHT-505-FM-1
Table 5-6. Cabin and Baggage Loading (Metric)
Table of moments (kg•mm)
5-16
Weight
Pilot and Copilot
Aft Row
Baggage Center
(KG)
2489 mm
3429 mm
4267 mm
5
12446
17145
21336
10
24892
34290
42672
15
37338
51435
64008
20
49784
68580
85344
25
62230
85725
106680
30
74676
102870
128016
35
87122
120015
149352
40
99568
137160
170688
45
112004
154305
192024
50
124460
171450
213360
55
136906
188595
234696
60
149352
205740
256032
65
161798
222885
277368
70
174244
240030
298704
75
186690
257175
320040
80
199136
274320
341376
85
211582
291465
362712
90
224028
308610
384048
95
236474
325755
405384
100
248920
342900
426720
105
261366
360045
448056
110
273812
377190
469392
113.4
282275
388849
483900
115
286258
394335
120
298704
411480
125
311150
428625
130
323596
445770
Rev. 6
16 APR 2020
Export Classification C, ECCN EAR99
BHT-505-FM-1
Table 5-6. Cabin and Baggage Loading (Metric) (Cont)
Table of moments (kg•mm)
Weight
Pilot and Copilot
Aft Row
Baggage Center
(KG)
2489 mm
3429 mm
4267 mm
135
336042
462915
140
348488
480060
145
360934
497205
150
373380
514350
155
385826
531495
160
398272
548640
165
410718
565785
170
423164
582930
175
435610
600075
180
448056
617220
185
460502
634365
190
472948
651510
195
485394
668655
200
497840
645800
205
510286
702945
210
522732
720090
215
535178
737235
220
547624
754380
225
560070
771525
230
572516
788670
235
584962
805815
240
597408
822960
245
609854
840105
249.5
609854
855536
250
62230
857250
Export Classification C, ECCN EAR99
16 APR 2020 Rev. 6
5-17
BHT-505-FM-1
Table 5-7. Fuel Density Versus Temperature
Temperature
(°F)
1
Density
lb/Gallon
Density
lb/Gallon
JET A
JET B
120
6.59
6.27
100
6.66
80
Temperature
(°C)
Density
kg/Liter
Density
kg/Liter
JET A
JET B
40
0.797
0.759
6.35
30
0.805
0.767
6.73
6.42
20
0.812
0.775
601
6.80
6.50
15.561
0.815
0.779
40
6.87
6.58
10
0.820
0.784
20
6.94
6.65
0
0.827
0.792
0
7.01
6.73
-10
0.835
0.800
-20
7.08
6.80
-20
0.842
0.808
-40
7.15
6.88
-30
0.850
0.816
-40
0.857
0.824
Standard density, used to derive fuel burn curves.
NOTE
In Table 5-8 and Table 5-9, lateral
CG for basic helicopter fuel is
always ZERO.
5-18
Rev. 6
16 APR 2020
Export Classification C, ECCN EAR99
BHT-505-FM-1
Table 5-8. Fuel Loading (U.S.)
Quantity
Jet A
Longitudinal
Weight
CG
Moment
(U.S. GAL)
(LB)
(IN.)
(IN•LB)
0
0
164.7
5
34
10
Quantity
Jet B
Longitudinal
Weight
CG
Moment
(U.S. GAL)
(LB)
(IN.)
(IN•LB)
0
0
0
164.7
0
167.1
5681
5
33
167.1
5514
68
167.6
11397
10
65
167.6
10894
12.2
83
167.7
13919
12.2
79
167.7
13248
15
102
167.5
17085
15
98
167.5
16415
20
136
167.0
22712
20
130
167.0
2170
25
170
166.7
28339
25
163
166.7
27172
30
204
166.5
33966
30
195
166.5
32468
35
238
166.4
39603
35
228
166.4
37939
40
272
166.3
45234
40
260
166.3
43238
45
306
166.2
50857
45
293
166.2
48697
50
340
166.1
56474
50
325
166.1
53983
55
374
166.1
62121
55
358
166.1
59464
60
408
166.1
67769
60
390
166.1
64779
65
442
166.0
73372
65
423
166.0
70218
70
476
166.0
79016
70
455
166.0
75530
75
510
166.0
84660
75
488
166.0
81008
80
544
166.0
90304
80
520
166.0
86320
84.9
577
166.0
95782
84.9
552
166.0
91632
Export Classification C, ECCN EAR99
16 APR 2020 Rev. 6
5-19
BHT-505-FM-1
Table 5-9. Fuel Loading (Metric)
Quantity
Jet A
Longitudinal
Weight
CG
Moment
(LITERS)
(KG)
(MM)
(KG•MM)
0
0
4183
20
16.3
40
Quantity
Jet B
Longitudinal
Weight
CG
Moment
(LITERS)
(KG)
(MM)
(KG•MM)
0
0
0
4183
0
4247
66253
20
15.6
4247
67946
32.6
4259
132881
40
31.2
4259
132014
46
37.5
4258
152862
46
35.9
4258
153295
60
48.9
4253
198615
60
46.7
4253
199886
80
65.2
4240
264152
80
62.3
4240
262911
100
81.5
4233
329751
100
77.9
4233
330151
120
97.8
4228
395318
120
93.5
4228
393195
140
114.1
4225
460948
140
109.1
4225
460481
160
130.4
4222
526061
160
124.6
4222
527788
180
146.7
4221
591784
180
140.2
4221
590884
200
163.0
4219
657320
200
155.8
4219
658211
220
179.3
4218
722965
220
171.4
4218
721346
240
195.6
4218
788766
240
187.0
4218
788710
260
211.9
4217
853943
260
202.5
4217
856092
280
228.2
4216
919510
280
218.1
4216
919197
300
244.5
4216
985279
300
233.7
4216
986661
320
260.8
4216
1051049
320
249.3
4216
1049834
321.2
261.7
4216
1054843
321.2
250.2
4216
1054050
5-20
Rev. 6
16 APR 2020
Export Classification C, ECCN EAR99