ROTORCRAFT 

FLIGHT MANUAL

SUPPLEMENT

INCREASED INTERNAL GROSS WEIGHT

TO 7500 POUNDS (3402 KG)

429-706-079

CERTIFIED

10 JANUARY 2012

This supplement shall be attached to the BHT-429-FM-1 

when the helicopter is operated at internal gross weight 

above 7000 pounds (3175 kg).

Information contained herein supplements information in 

the basic Flight Manual. For Limitations, Procedures, and 

Performance Data not contained in this supplement, refer to 

the basic Flight Manual. 

BHT-429-FMS-11

10 JANUARY 2012

COPYRIGHT NOTICE

COPYRIGHT 2012

BELL ® HELICOPTER TEXTRON INC.

AND BELL HELICOPTER TEXTRON

CANADA LTD.

ALL RIGHTS RESERVED
NOTICE PAGE

Additional copies of this publication may be obtained by contacting:

Commercial Publication Distribution Center

Bell Helicopter Textron Inc.

P. O. Box 482

Fort Worth, Texas 76101-0482

NP 10 JAN 2012

BHT-429-FMS-11

These data are proprietary to Bell Helicopter Textron Inc. Disclosure,

reproduction, or use of these data for any purpose other than helicopter

operation or maintenance is forbidden without prior written authorization 

from Bell Helicopter Textron Inc.

PROPRIETARY RIGHTS NOTICE

DESTINATION CONTROL STATEMENT

These commodities, technology, or software were exported from the 

United States in accordance with the Export Administration Regulations 

(EAR). Diversion contrary to U.S. law prohibited. The data contained in 

this manual are classified as ECCN EAR99.
Original ..................... 0...................... 10 JAN 12

10 JAN 2012 A/B

BHT-429-FMS-11

NOTE

Revised text is indicated by a black vertical line. A revised page with only a vertical line next to 

the page number indicates that text has shifted or that non-technical correction(s) were made

on that page. Insert latest revision pages; dispose of superseded pages.

LOG OF REVISIONS

LOG OF PAGES

REVISION REVISION

PAGE NO. PAGE NO.

FLIGHT MANUAL

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CHIEF, FLIGHT TEST

FOR

DIRECTOR — NATIONAL AIRCRAFT CERTIFICATION

TRANSPORT CANADA

APPROVED DATE

10 JAN 2012 C/D

BHT-429-FMS-11

Original ..................... 0...................... 10 JAN 12

LOG OF TC APPROVED REVISIONS

BHT-429-FMS-11

10 JAN 2012 E/F

LOG OF FAA APPROVED REVISIONS

Original ..................... 0....... Not FAA Approved

BHT-429-FMS-11

GENERAL INFORMATION

ECCN EAR99 10 JAN 2012 i/ii

NOTE

This Flight Manual Supplement is not FAA or EASA approved.

This supplement provides limitations, performance, and weight and balance information for flight 

operations at internal gross weights above 7000 pounds (3175 kg). 

TC APPROVED BHT-429-FMS-11

ECCN EAR99 10 JAN 2012 1

Section 1

LIMITATIONS

1

1-2. BASIS OF CERTIFICATION

This Increased Internal Gross Weight is

certified under the Canadian Airworthiness

Manual as detailed in Transport Canada's

Type Certificate Data Sheet number H-107.

1-5. CONFIGURATION

1-5-A. REQUIRED EQUIPMENT

The following additional equipment and

software shall be installed and functional:

• Radar Altimeter

• HTAWS (Helicopter Terrain Awareness

and Warning System)

• Cockpit Voice/Flight Data Recorder (CV/

FDR)

• Forward facing pulse lights

1-5-B. OPTIONAL EQUIPMENT

Unless specified in another optional

equipment FMS that operations in accordance

with BHT-429-FMS-11 are not approved, all

Bell Helicopter FMSs are approved for

Increased Internal Gross Weight operations to

7500 pounds (3402 kg).

Refer to appropriate FMS for additional

limitations, procedures, and performance data

for optional equipment (see BHT-429-FM-1,

Appendix A).

1-6. WEIGHT AND CENTER OF

GRAVITY

CAUTION

DISPLAY UNIT (DU) FUEL/WEIGHT &

BAL PAGE IN 7500-POUND

(3402-KG) CONFIGURATION DOES

NOT SUPPORT CG ENVELOPE FOR

HELICOPTERS EQUIPPED WITH

EMERGENCY FLOTATION SYSTEM

KIT 429-706-069 (BHT-429-FMS-2).

1-6-A. WEIGHT

Maximum internal gross weight (GW) for

takeoff and landing is 7500 pounds (3402 kg).

1-6-B. CENTER OF GRAVITY

For longitudinal CG limits, refer to Gross

Weight Longitudinal Center of Gravity Limits

chart (Figure 1-1).

For lateral CG limits, refer to Gross Weight

Lateral Center of Gravity Limits chart

(Figure 1-2).
BHT-429-FMS-11 TC APPROVED

2 10 JAN 2012 ECCN EAR99

1-9. MANEUVERING

1-9-C. SLOPE LANDINGS

CAUTION

SLOPE LANDINGS HAVE BEEN

DEMONSTRATED TO THE SLOPE

LANDING LIMITS. OTHER

CONDITIONS INCLUDING, BUT NOT

LIMITED TO, WIND DIRECTION AND

VELOCITY, CENTER OF GRAVITY,

AND THE CONDITION OF THE

SLOPE (LOOSE ROCK, SOFT MUD,

SNOW, WET GRASS, ETC.) MAY

LIMIT MAXIMUM SLOPE TO A VALUE

LESS THAN THE PUBLISHED

LIMITS.

Slope landings are limited to 5° slope.
TC APPROVED BHT-429-FMS-11

ECCN EAR99 10 JAN 2012 3

Figure 1-1. Gross Weight Longitudinal Center of Gravity Limits

Longitudinal Gross Weight / CG Envelope

5600 5650 5700 5750 5800 5850 5900 5950

FUSELAGE STATION - MILLIMETERS

220 222 224 226 228 230 232 234

FUSELAGE STATION - INCHES

1800

1900

2000

2100

2200

2300

2400

2500

2600

2700

2800

2900

3000

3100

3200

3300

3400

3500

3600

3700

GROSS WEIGHT - KILOGRAMS

3800

4000

4200

4400

4600

4800

5000

5200

5400

5600

5800

6000

6200

6400

6600

6800

7000

7200

7400

7600

7800

8000

8200

GROSS WEIGHT - POUNDS

4400 lb at Stn 233.0 inches

(1996 Kg at Stn 5918 mm)

5100 lb at Stn 221.8 inches

(2313 Kg at Stn 5634 mm)

5700 lb at Stn 233.0 inches

(2586 Kg at Stn 5918 mm)

7000 lb at Stn 221.8 inches

(3175 Kg at Stn 5634 mm)

7500 lb at Stn 223.1 inches (3402 Kg at Stn 5667 mm)

7500 lb at Stn 227.9 inches

(3402 Kg at Stn 5789 mm)

7500 lb at Stn 225 inches

(3402 Kg at Stn 5715 mm)

Crosshatched Area is Prohibited when FLOAT Kit Installed (429-FMS-2)
BHT-429-FMS-11 TC APPROVED

4 10 JAN 2012 ECCN EAR99

Figure 1-2. Gross Weight Lateral Center of Gravity Limits

-75 -50 -25 0 25 50 75

LATERAL CG - MILLIMETERS

-3 -2 -1 0 1 2 3

LATERAL CG - INCHES

1900

2000

2100

2200

2300

2400

2500

2600

2700

2800

2900

3000

3100

3200

3300

3400

3500

GROSS WEIGHT - KILOGRAMS

4000

4200

4400

4600

4800

5000

5200

5400

5600

5800

6000

6200

6400

6600

6800

7000

7200

7400

7600

7800

GROSS WEIGHT - POUNDS

 7500 lb at -1.7 inches 

 (3402 Kg at -43 mm) 

 7500 lb at 1.7 inches 

 (3402 Kg at 43 mm) 

Lateral Gross Weight / CG Envelope

 5500 lb at 2.5 inches 

 (2495 Kg at 64 mm) 

 5500 lb at -2.5 inches 

 (2495 Kg at -64 mm) 
TC APPROVED BHT-429-FMS-11

ECCN EAR99 10 JAN 2012 5

Section 2

NORMAL PROCEDURES

2

No change from basic manual.

Section 3

EMERGENCY AND MALFUNCTION PROCEDURES

3

No change from basic manual.

Section 4

PERFORMANCE

4

4-1. INTRODUCTION

General information and examples pertaining

to the use of these charts can be found in the

Performance section of the basic Flight

Manual.

4-4. HEIGHT-VELOCITY

Height-velocity information is critical in the

event of single engine failure during takeoff,

landing, or other operations near surface. The

avoid areas on Single Engine Height-Velocity

Diagram (Figure 4-3) define combinations of

airspeed and height above ground from which

safe single engine landing on smooth, level,

firm surface cannot be assured.

Figure 4-3 is applicable to all combinations of

pressure altitude and gross weight up to 7500

pounds (3402 kg). Figure 4-3, Sheet 1 applies

to all ambient temperatures from 20°C to

maximum OAT. Figure 4-3, Sheet 2 applies to

all ambient temperatures below 20°C.

4-5. HOVER CEILING

Satisfactory stability and control have been

demonstrated in each area of hover ceiling

charts with winds as depicted in Hover Ceiling
BHT-429-FMS-11 TC APPROVED

6 10 JAN 2012 ECCN EAR99

Wind Accountability Chart (Figure 4-4 in

BHT-429-FM-1).

4-5-A. HOVER CEILING — IGE

Hover Ceiling IGE charts (Figure 4-5) present

IGE hover performance (relative to GW) for

conditions of pressure altitude (HP) and OAT.

4-5-B. HOVER CEILING — OGE

Hover Ceiling OGE charts (Figure 4-6) present

OGE hover performance (relative to GW) for

conditions of pressure altitude (HP) and OAT.

4-7. CLIMB AND DESCENT

4-7-A. CLIMB

Rate of Climb charts (Figure 4-7 through

Figure 4-10) are presented for various power

settings including OEI operations.

4-10. NOISE LEVELS

VH is defined as airspeed in level flight

obtained using minimum specification engine

torque corresponding to maximum

continuous power available for sea level, 25°C

(77°F) ambient conditions at the relevant

maximum certificated weight. Value of VH

thus defined for this helicopter at gross

weight of 7500 pounds (3402 kg) is 142 KTAS.

The certified noise levels for Model 429 are:

4-10-A. CANADIAN AIRWORTHINESS

MANUAL CHAPTER 516 AND

ICAO ANNEX 16 NOISE LEVEL

CERTIFICATION

The above noise levels were obtained by

analysis of approved data from noise tests

conducted under the provisions of Chapter 8

of ICAO Annex 16, Volume 1, Fifth Edition,

Amendment 9.

This helicopter complies with the noise

emission standards applicable to the

helicopter as set out by the International Civil

Aviation Organization (ICAO) in Annex 16,

Volume 1, Chapter 8, for gross weights up to

and including the certificated maximum

takeoff and landing weight of 7500 pounds

(3402 kg). There are no operating limitations

to meet TC or ICAO takeoff, overflight, or

approach noise requirements.

Flight condition EPNL (EPNdB)

Takeoff 88.2

Flyover 89.6

Approach 91.8
TC APPROVED BHT-429-FMS-11

ECCN EAR99 10 JAN 2012 7

Figure 4-3. Single Engine Height-Velocity Diagram (Sheet 1 of 2)

SINGLE ENGINE HEIGHT-VELOCITY DIAGRAM

FROM -20°C TO MAX OAT

NOTES

1. The shaded AVOID AREA applies to all ambient temperatures from -20°C

 to maximum OAT.

2. This chart is applicable to all gross weights up to 7500 pounds and all

 pressure altitudes.

0

20

40

60

80

100

120

140

160

180

200

220

240

260

280

300

320

340

360

380

400

SKID HEIGHT ABOVE SURFACE - FT

0 5 10 15 20 25 30 35 40 45 50

INDICATED AIRSPEED - KT

0

5

10

15

20

25

30

35

40

45

50

55

60

65

70

75

80

85

90

95

100

105

110

115

120

SKID HEIGHT ABOVE SURFACE - METERS

AVOID

AREA

 8 FT 

DEMONSTRATED

TO 9000 FEET

DENSITY ALTITUDE
BHT-429-FMS-11 TC APPROVED

8 10 JAN 2012 ECCN EAR99

Figure 4-3. Single Engine Height-Velocity Diagram (Sheet 2 of 2)

SINGLE ENGINE HEIGHT-VELOCITY DIAGRAM

FOR OAT BELOW -20°C

NOTES

1. The shaded AVOID AREA applies to all ambient temperatures below -20°C.

2. This chart is applicable to all gross weights up to 7500 pounds and all

 pressure altitudes.

0 5 10 15 20 25 30 35 40 45 50

INDICATED AIRSPEED - KT

0

20

40

60

80

100

120

140

160

180

200

220

240

260

280

300

320

340

360

380

400

SKID HEIGHT ABOVE SURFACE - FT

0

5

10

15

20

25

30

35

40

45

50

55

60

65

70

75

80

85

90

95

100

105

110

115

120

SKID HEIGHT ABOVE SURFACE - METERS

AVOID

AREA

 6 FT 

DEMONSTRATED

TO 9000 FEET

DENSITY ALTITUDE
TC APPROVED BHT-429-FMS-11

ECCN EAR99 10 JAN 2012 9

Figure 4-5. Hover Ceiling IGE (Sheet 1 of 4)

HOVER CEILING

IN GROUND EFFECT

TAKEOFF POWER

ENGINE RPM 100%

GENERATORS 150 AMPS EACH

SKID HEIGHT 4 FT (1.2 METER)

BASIC INLET OR BARRIER FILTER

AIR COND. OFF / HEATER OFF

-40 -20 0 20 40 60

OAT - °C

46 48 50 52 54 56 58 60 62 64 66 68 70 72 74

GROSS WEIGHT - LBS x 100

21 22 23 24 25 26 27 28 29 30 31 32 33 34

GROSS WEIGHT - KG x 100

19,000 FT HD

8000

14,000

6000

4000

2000

12,000

SEA LEVEL

-2000

HP - FT

10,000

16,000

18,000

MINIMUM OAT

OAT - °C

40

30

20

10

0

-20

20,000

 -10 & -30

 -40

AREA C AREA B

 AREA A 

MAX GROSS WEIGHT = 7500 LB

 MAXIMUM OAT 

17,000 FT HD

13,000 FT HD

MAXIM

U

M

OAT
BHT-429-FMS-11 TC APPROVED

10 10 JAN 2012 ECCN EAR99

Figure 4-5. Hover Ceiling IGE (Sheet 2 of 4)

HOVER CEILING

IN GROUND EFFECT

TAKEOFF POWER

ENGINE RPM 100%

GENERATORS 150 AMPS EACH

SKID HEIGHT 4 FT (1.2 METER)

BASIC INLET OR BARRIER FILTER

AIR COND. OFF / HEATER ON

-40 -20 0 20 40 60

OAT - °C

46 48 50 52 54 56 58 60 62 64 66 68 70 72 74

GROSS WEIGHT - LBS x 100

21 22 23 24 25 26 27 28 29 30 31 32 33 34

GROSS WEIGHT - KG x 100

19,000 FT HD

8000

14,000

6000

4000

2000

12,000

SEA LEVEL

-2000

HP - FT

10,000

16,000

18,000

MINIMUM OAT

OAT - °C

20

10

20,000

 -40

AREA C AREA B

 AREA A 

17,000 FT HD

13,000 FT HD

MAXIM

U

M

OAT

 -10

-20 & -30 0

MAX GROSS WEIGHT = 7500 LB
TC APPROVED BHT-429-FMS-11

ECCN EAR99 10 JAN 2012 11

Figure 4-5. Hover Ceiling IGE (Sheet 3 of 4)

HOVER CEILING

IN GROUND EFFECT

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATORS 150 AMPS EACH

SKID HEIGHT 4 FT (1.2 METER)

BASIC INLET OR BARRIER FILTER

AIR COND. OFF / HEATER OFF

-40 -20 0 20 40 60

OAT - °C

46 48 50 52 54 56 58 60 62 64 66 68 70 72 74

GROSS WEIGHT - LBS x 100

21 22 23 24 25 26 27 28 29 30 31 32 33 34

GROSS WEIGHT - KG x 100

19,000 FT HD

8000

14,000

6000

4000

2000

12,000

SEA LEVEL

-2000

HP - FT

10,000

16,000

18,000

MINIMUM OAT

51.7

50

40

30

20

10

0 -10

-30 -20 -40

20,000

OAT - °C

AREA C AREA B

 AREA A 

17,000 FT HD

13,000 FT HD

MAXIM

U

M

OAT

MAXIMUM OAT

MAX GROSS WEIGHT = 7500 LB
BHT-429-FMS-11 TC APPROVED

12 10 JAN 2012 ECCN EAR99

Figure 4-5. Hover Ceiling IGE (Sheet 4 of 4)

HOVER CEILING

IN GROUND EFFECT

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATORS 150 AMPS EACH

SKID HEIGHT 4 FT (1.2 METER)

BASIC INLET OR BARRIER FILTER

AIR COND. OFF / HEATER ON

-40 -20 0 20 40 60

OAT - °C

46 48 50 52 54 56 58 60 62 64 66 68 70 72 74

GROSS WEIGHT - LBS x 100

21 22 23 24 25 26 27 28 29 30 31 32 33 34

GROSS WEIGHT - KG x 100

19,000 FT HD

8000

14,000

6000

4000

2000

12,000

SEA LEVEL

-2000

HP - FT

10,000

16,000

18,000

MINIMUM OAT

20

10

0

-10

20,000

OAT - °C

AREA C AREA B

 AREA A 

17,000 FT HD

13,000 FT HD

MAXIM

U

M

OAT

 -30

 -20

-40

MAX GROSS WEIGHT = 7500 LB
TC APPROVED BHT-429-FMS-11

ECCN EAR99 10 JAN 2012 13

Figure 4-6. Hover Ceiling OGE (Sheet 1 of 4)

HOVER CEILING

OUT OF GROUND EFFECT

TAKEOFF POWER

ENGINE RPM 100%

GENERATORS 150 AMPS EACH

SKID HEIGHT 60 FT (18.3 METER)

BASIC INLET OR BARRIER FILTER

AIR COND. OFF / HEATER OFF

-40 -20 0 20 40 60

OAT - °C

46 48 50 52 54 56 58 60 62 64 66 68 70 72 74

GROSS WEIGHT - LBS x 100

21 22 23 24 25 26 27 28 29 30 31 32 33 34

GROSS WEIGHT - KG x 100

19,000 FT HD

8000

14,000

6000

4000

2000

12,000

SEA LEVEL

-2000

HP - FT

10,000

16,000

18,000

MINIMUM OAT

40

30

20

10

0 -20

20,000

OAT - °C

-10 & -30

 -40

AREA C AREA B

 AREA A 

 MAXIMUM OAT 

13,000 FT HD

17,000 FT HD

MAXIMU

M

OAT

MAX GROSS WEIGHT = 7500 LB
BHT-429-FMS-11 TC APPROVED

14 10 JAN 2012 ECCN EAR99

Figure 4-6. Hover Ceiling OGE (Sheet 2 of 4)

HOVER CEILING

OUT OF GROUND EFFECT

TAKEOFF POWER

ENGINE RPM 100%

GENERATORS 150 AMPS EACH

SKID HEIGHT 60 FT (18.3 METER)

BASIC INLET OR BARRIER FILTER

AIR COND. OFF / HEATER ON

-40 -20 0 20 40 60

OAT - °C

46 48 50 52 54 56 58 60 62 64 66 68 70 72 74

GROSS WEIGHT - LBS x 100

21 22 23 24 25 26 27 28 29 30 31 32 33 34

GROSS WEIGHT - KG x 100

19,000 FT HD

8000

14,000

6000

4000

2000

12,000

SEA LEVEL

-2000

HP - FT

10,000

16,000

18,000

MINIMUM OAT

20

10

-20 & -30

20,000

OAT - °C

 -40

AREA C AREA B

 AREA A 

13,000 FT HD

17,000 FT HD

MAXIMU

M

OAT

0

 -10

MAX GROSS WEIGHT = 7500 LB
TC APPROVED BHT-429-FMS-11

ECCN EAR99 10 JAN 2012 15

Figure 4-6. Hover Ceiling OGE (Sheet 3 of 4)

HOVER CEILING

OUT OF GROUND EFFECT

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATORS 150 AMPS EACH

SKID HEIGHT 60 FT (18.3 METER)

BASIC INLET OR BARRIER FILTER

AIR COND. OFF / HEATER OFF

-40 -20 0 20 40 60

OAT - °C

46 48 50 52 54 56 58 60 62 64 66 68 70 72 74

GROSS WEIGHT - LBS x 100

21 22 23 24 25 26 27 28 29 30 31 32 33 34

GROSS WEIGHT - KG x 100

19,000 FT HD

8000

14,000

6000

4000

2000

12,000

SEA LEVEL

-2000

HP - FT

10,000

16,000

18,000

MINIMUM OAT

51.7

50

40

30

20

10

0 -10 -20 -30 & -40

20,000

OAT - °C

AREA C AREA B

 AREA A 

17,000 FT HD

13,000 FT HD

MAXIMU

M

OAT

MAXIMUM OAT

MAX GROSS WEIGHT = 7500 LB
BHT-429-FMS-11 TC APPROVED

16 10 JAN 2012 ECCN EAR99

Figure 4-6. Hover Ceiling OGE (Sheet 4 of 4)

HOVER CEILING

OUT OF GROUND EFFECT

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATORS 150 AMPS EACH

SKID HEIGHT 60 FT (18.3 METER)

BASIC INLET OR BARRIER FILTER

AIR COND. OFF / HEATER ON

-40 -20 0 20 40 60

OAT - °C

46 48 50 52 54 56 58 60 62 64 66 68 70 72 74

GROSS WEIGHT - LBS x 100

21 22 23 24 25 26 27 28 29 30 31 32 33 34

GROSS WEIGHT - KG x 100

19,000 FT HD

8000

14,000

6000

4000

2000

12,000

SEA LEVEL

-2000

HP - FT

10,000

16,000

18,000

MINIMUM OAT

20

10

0

-30 & -40

20,000

OAT - °C

AREA C AREA B

 AREA A 

17,000 FT HD

13,000 FT HD

MAXIM

U

M

OAT

 -20

 -10

MAX GROSS WEIGHT = 7500 LB
TC APPROVED BHT-429-FMS-11

ECCN EAR99 10 JAN 2012 17

Figure 4-7. Rate of Climb — Takeoff Power

REDUCE RATE OF CLIMB 260 FT/MIN (1.3 M/SEC)

FOR HEATER ON (20°C AND COLDER) AT ALTITUDES ABOVE 2000 FT

TAKEOFF POWER

ENGINE RPM 100%

GENERATORS 150 AMPS EACH

60 KIAS

BASIC INLET OR BARRIER FILTER

AIR COND. OFF / HEATER OFF

RATE OF CLIMB

Gross Weight 7500 lbs (3402 kg)

0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

18,000

20,000

PRESSURE ALTITUDE - FEET

0 400 800 1200 1600 2000 2400 2800 3200 3600 4000

RATE OF CLIMB - FT/MIN

0 2 4 6 8 10 12 14 16 18 20

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PRESSURE ALTITUDE - 1000 METERS

OAT-°C

MAX OAT

0

-10

-20

-40

50

10

30

20

40

-30
BHT-429-FMS-11 TC APPROVED

18 10 JAN 2012 ECCN EAR99

Figure 4-8. Rate of Climb — Maximum Continuous Power

RATE OF CLIMB

Gross Weight 7500 lbs (3402 kg)

0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

18,000

20,000

PRESSURE ALTITUDE - FEET

0 400 800 1200 1600 2000 2400 2800 3200 3600 4000

RATE OF CLIMB - FT/MIN

0 2 4 6 8 10 12 14 16 18 20

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PRESSURE ALTITUDE - 1000 METERS

OAT-°C

0

10

20

-20

50

MAX

OAT

40

-30

-10

-40

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATORS 150 AMPS EACH

60 KIAS

BASIC INLET OR BARRIER FILTER

AIR COND. OFF / HEATER OFF

REDUCE RATE OF CLIMB 290 FT/MIN (1.5 M/SEC)

FOR HEATER ON (20°C AND COLDER) AT ALL ALTITUDES

30
TC APPROVED BHT-429-FMS-11

ECCN EAR99 10 JAN 2012 19

Figure 4-9. Rate of Climb — 30 Minute OEI Power

SINGLE ENGINE RATE OF CLIMB

Gross Weight 7500 lbs (3402 kg)

30 MINUTE OEI POWER

ENGINE RPM 100%

GENERATOR 150 AMPS

60 KIAS

BASIC INLET OR BARRIER FILTER

AIR COND. OFF / HEATER OFF

0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

18,000

20,000

PRESSURE ALTITUDE - FEET

-200 -100 0 100 200 300 400 500 600 700 800

RATE OF CLIMB - FT/MIN

-1 0 1 2 3 4

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PRESSURE ALTITUDE - 1000 METERS

MAX OAT

0

10

-10

-20

OAT-°C

-40

30

50

20

40

-30
BHT-429-FMS-11 TC APPROVED

20 10 JAN 2012 ECCN EAR99

Figure 4-10. Rate of Climb — Maximum Continuous OEI Power

MAXIMUM CONTINUOUS OEI POWER

ENGINE RPM 100%

GENERATOR 150 AMPS

60 KIAS

BASIC INLET OR BARRIER FILTER

AIR COND. OFF / HEATER OFF

SINGLE ENGINE RATE OF CLIMB

Gross Weight 7500 lbs (3402 kg)

0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

18,000

20,000

PRESSURE ALTITUDE - FEET

-200 -100 0 100 200 300 400 500 600 700 800

RATE OF CLIMB - FT/MIN

-1 0 1 2 3 4

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PRESSURE ALTITUDE - 1000 METERS

MAX OAT

0

10

-30

OAT-°C

-40

30

20

50

40

-10

-20
BHT-429-FMS-11

ECCN EAR99 10 JAN 2012 21

Section 5

WEIGHT AND BALANCE

5

5-3. GROSS WEIGHT CENTER OF

GRAVITY

5-3-A. GROSS WEIGHT CG

MANAGEMENT

Pilot is responsible to ensure helicopter is

properly loaded so entire flight is conducted

within gross weight/center of gravity limits.

(See Section 1 of this manual or appropriate

Flight Manual Supplement.)

NOTE

The empty weight CG chart method

for gross weight CG management

cannot be used when the gross

weight exceeds 7000 pounds

(3175 kg).

There are two methods by which this can be

achieved (see paragraph 5-3-A-2 and

paragraph 5-3-A-3).

5-3-A-2. USE OF ACTUAL WEIGHT

RECORDS WITH FLIGHT MANUAL

LIMITS

This method can be used in all loading cases.

Weight and moment of each component of

helicopter loading is calculated for critical

fuel loadings and verified to be within GW/CG

limits.

Table 5-1 and Table 5-1M (BHT-429-FM-1,

Section 5) are examples for computation of

GW/CG which can be utilized as a guide for

these calculations. GW, longitudinal, and

lateral CG must be calculated for each flight

from following:

Actual Weight Record.

Diagrams and loading tables in

BHT-429-FM-1, Section 5.

Diagrams and loading tables in

appropriate Flight Manual Supplements.

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.

Significant fuselage stations and buttock

lines are shown in Figure 5-1 and Figure 5-2

(BHT-429-FM-1, Section 5) to aid in weight and

balance calculations.

5-3-A-3. USE OF WEIGHT AND BALANCE

NOMOGRAPH

Loading chart (Figure 5-3 or Figure 5-3M) is a

quick and simple method of checking weight

and longitudinal balance for specific

loadings. It can provide a permanent record of

a particular flight or loading condition. Use of

this method is detailed in BHT-429-FM-1,

Section 5.
BHT-429-FMS-11

22 10 JAN 2012 ECCN EAR99

Figure 5-3. Loading Chart (U.S.)

70 80 90 100 110 120

MODEL 429 LOADING CHART

Aircraft Serial No.

Registration No.

Date 

This loading is based on

Actual Weight Record dated

EMPTY WEIGHT LONGITUDINAL INDEX

EMPTY WEIGHT x ( CG - 230.0 )

2000

= + 100 [ ]

LONGITUDINAL INDEX ADJUSTMENTS

Empty Weight CG - 230.0 = (a)

Empty Weight / 2000 = (b)

(a) x (b) = (c)

(c) + 100 = = Empty Weight

Longitudinal Index

Weight (lb.)

Empty Weight 

 Pilot & Fwd Pass. (Copilot) 

 Passengers : Mid Row 

 Baggage Compartment (1) 

 Passengers : Aft Row 

Zero Fuel Weight 

 Fuel Index & Weight 

 CG Check:Fuel Burn 

Take-Off Gross Weight 

No Index Adjustment Required

(50 lb) 

(50 lb) 

(50 lb) 

Jet B

(6.5 lb/US Gal)

Weight Index

 100 0.7

 200 1.3

 300 2.1

 400 3.3

 500 4.3

 600 5.2

 700 6.2

 800 7.2

 900 8.1

1000 9.1

1100 10.0

1200 10.9

1235 10.9

1300 11.5

1400 12.2

 1410 * 12.2

Jet A

(6.8 lb/US Gal)

Weight Index

 100 0.7

 200 1.3

 300 2.1

 400 3.2

 500 4.2

 600 5.2

 700 6.2

 800 7.1

 900 8.1

1000 9.1

1100 10.0

1200 10.9

1292 11.7

1300 11.7

1400 12.4

1475 * 12.8

FUEL INDEX

NOTES:

(1) Assumes longitudinal CG of items in

centre of Baggagge Bay.

4200

4600

5000

5400

5800

6200

6600

7000

7400

Fwd

Limit

Aft Limit

220 222 224 226 228 230 232 234

Longitudinal CG (inches)

GROSS WEIGHT / CENTER OF GRAVITY CHART

Gross Weight (pounds)

* Most forward extreme CG condition.
BHT-429-FMS-11

ECCN EAR99 10 JAN 2012 23

Figure 5-3M. Loading Chart (Metric)

70 80 90 100 110 120

MODEL 429 LOADING CHART

(Metric)

Aircraft Serial No.

Registration No.

Date 

This loading is based on

Actual Weight Record dated

EMPTY WEIGHT LONGITUDINAL INDEX

EMPTY WEIGHT x ( CG - 5842 )

23037

= + 100 [ ]

LONGITUDINAL INDEX ADJUSTMENTS

Empty Weight CG - 5842 = (a)

Empty Weight / 23037 = (b)

(a) x (b) = (c)

(c) + 100 = = Empty Weight

Longitudinal Index

Weight (Kg)

Empty Weight 

 Pilot & Fwd Pass. (Copilot) 

 Passengers : Mid Row 

 Baggage Compartment (1) 

 Passengers : Aft Row 

Zero Fuel Weight 

 Fuel Index & Weight 

 CG Check:Fuel Burn 

Take-Off Gross Weight 

No Index Adjustment Required

(23 Kg) 

(23 Kg) 

(23 Kg) 

Jet B 

(0.779 Kg / Liter)

Weight Index

 50 0.7 

100 1.5

150 2.4

200 3.7

250 4.8

300 5.8

350 6.9

400 8.0

450 9.0

500 10.0

550 11.0

560 11.7

600 10.7

639.6 * 12.2

Jet A

(0.815 Kg / Liter)

Weight Index

 50 0.7 

100 1.5

150 2.4

200 3.6

250 4.7

300 5.8

350 6.8

400 8.0

450 9.0

500 10.0

550 11.0

586 11.7

600 11.9

650 12.6

669 * 12.8

FUEL INDEX

NOTES:

(1) Assumes longitudinal CG of items in

centre of Baggagge Bay.

1900

2000

2100

2200

2300

2400

2500

2600

2700

2800

2900

3000

3100

3200

3300

3400

3500

Fwd

Limit

Aft Limit

5600 5650 5700 5750 5800 5850 5900 5950

Longitudinal CG (mm)

GROSS WEIGHT / CENTER OF GRAVITY CHART

Gross Weight (Kg)

* Most forward extreme CG condition.
BHT-429-FMS-11

24 10 JAN 2012 ECCN EAR99

Figure 5-4. Loading Chart Example (U.S.)

70 80 90 100 110 120

MODEL 429 LOADING CHART

Aircraft Serial No.

Registration No.

Date 

This loading is based on

Actual Weight Record dated

EMPTY WEIGHT LONGITUDINAL INDEX

Example

EMPTY WEIGHT x ( CG - 230.0 )

2000

= + 100 [ ]

LONGITUDINAL INDEX ADJUSTMENTS

Empty Weight CG 236.9 - 230.0 = 6.9 (a)

Empty Weight 4558.0 / 2000 = 2.3 (b)

(a) 6.9 x (b) 2.3 = 15.7 (c)

(c) 15.7 + 100 = 115.7 = Empty Weight

Longitudinal Index

Weight (lb.)

Empty Weight 4558

 Pilot & Fwd Pass. (Copilot) 400

 Passengers : Mid Row 200 

 Baggage Compartment (1) 54

 Passengers : Aft Row 360 

Zero Fuel Weight 5572

 Fuel Index & Weight (12.5) 1428 

 CG Check:Fuel Burn 

1428 lb (12.5) (7000)

Take-Off Gross Weight 7000

No Index Adjustment Required

(50 lb) 

(50 lb) 

(50 lb) 

Jet B

(6.5 lb/US Gal)

Weight Index

 100 0.7

 200 1.3

 300 2.1

 400 3.3

 500 4.3

 600 5.2

 700 6.2

 800 7.2

 900 8.1

1000 9.1

1100 10.0

1200 10.9

1235 10.9

1300 11.5

1400 12.2

 1410 * 12.2

Jet A

(6.8 lb/US Gal)

Weight Index

 100 0.7

 200 1.3

 300 2.1

 400 3.2

 500 4.2

 600 5.2

 700 6.2

 800 7.1

 900 8.1

1000 9.1

1100 10.0

1200 10.9

1292 11.7

1300 11.7

1400 12.4

1475 * 12.8

FUEL INDEX

NOTES:

(1) Assumes longitudinal CG of items in

centre of Baggagge Bay.

4200

4600

5000

5400

5800

6200

6600

7000

7400

TOGW

ZFW

Fwd

Limit

Aft Limit

(12.5)

220 222 224 226 228 230 232 234

Longitudinal CG (inches)

GROSS WEIGHT / CENTER OF GRAVITY CHART

Gross Weight (pounds)

* Most forward extreme CG condition.
BHT-429-FMS-11

ECCN EAR99

Figure 5-4M. Loading Chart Example (Metric)

70 80 90 100 110 120

MODEL 429 LOADING CHART

(Metric)

Aircraft Serial No.

Registration No.

Date 

This loading is based on

Actual Weight Record dated

EMPTY WEIGHT LONGITUDINAL INDEX

Example

EMPTY WEIGHT x ( CG - 5842 )

23037

= + 100 [ ]

LONGITUDINAL INDEX ADJUSTMENTS

Empty Weight CG 6017 - 5842 = 175.3 (a)

Empty Weight 2067 / 23037 = 0.9 (b)

(a) 175.3 x (b) 0.9 = 15.7 (c)

(c) 15.7 + 100 = 115.7 = Empty Weight

Longitudinal Index

Weight (Kg)

Empty Weight 2067

 Pilot & Fwd Pass. (Copilot) 182

 Passengers : Mid Row 91 

 Baggage Compartment (1) 24

 Passengers : Aft Row 163 

Zero Fuel Weight 2527

 Fuel Index & Weight (12.5) 648 

 CG Check:Fuel Burn 

648 Kg (12.5) (3175)

Take-Off Gross Weight 3175

No Index Adjustment Required

(23 Kg) 

(23 Kg) 

(23 Kg) 

Jet B 

(0.779 Kg / Liter)

Weight Index

 50 0.7 

100 1.5

150 2.4

200 3.7

250 4.8

300 5.8

350 6.9

400 8.0

450 9.0

500 10.0

550 11.0

560 11.7

600 10.7

639.6 * 12.2

Jet A

(0.815 Kg / Liter)

Weight Index

 50 0.7 

100 1.5

150 2.4

200 3.6

250 4.7

300 5.8

350 6.8

400 8.0

450 9.0

500 10.0

550 11.0

586 11.7

600 11.9

650 12.6

669 * 12.8

FUEL INDEX

NOTES:

(1) Assumes longitudinal CG of items in

centre of Baggagge Bay.

1900

2000

2100

2200

2300

2400

2500

2600

2700

2800

2900

3000

3100

3200

3300

3400

3500

TOGW

ZFW

Fwd

Limit

Aft Limit

(12.5)

5600 5650 5700 5750 5800 5850 5900 5950

Longitudinal CG (mm)

GROSS WEIGHT / CENTER OF GRAVITY CHART

Gross Weight (Kg)

* Most forward extreme CG condition.

10 JAN 2012 25/26