# ROTORCRAFT FLIGHT MANUAL SUPPLEMENT 

# INCREASED INTERNAL GROSS WEIGHT TO 7500 POU NDS (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 Insert latest revision pages; dispose of superseded pages.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 NO. NO. PAGE PAGE
FLIGHT MANUAL Title.............................................................0 NP ...............................................................0 A/B..............................................................0 C/D..............................................................0 E/F ..............................................................0 i/ii ................................................................0 1


# – 24..........................................................0 25/26 ...........................................................0

## 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

10 JAN 2012 i/ii ECCN EAR99 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

10 JAN 2012 1 ECCN EAR99 

# 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 Cent er 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

10 JAN 2012 3 ECCN EAR99 Figure 1-1. Gross Weight Longi tudinal 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 3700GROSS WEIGHT - KILOGRAMS



### 3800 4000 4200 4400 4600 4800 5000 5200 5400 5600 5800 6000 6200 6400 6600 6800 7000 7200 7400 7600 7800 8000 8200GROSS 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 3500GROSS WEIGHT - KILOGRAMS



### 4000 4200 4400 4600 4800 5000 5200 5400 5600 5800 6000 6200 6400 6600 6800 7000 7200 7400 7600 7800GROSS 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

10 JAN 2012 5 ECCN EAR99 

# 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 (H P 

## ) 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 (H P 

## ) 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
V H 

## 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 V H 

## 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

10 JAN 2012 7 ECCN EAR99 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 400SKID 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 120SKID 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 400SKID 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 120SKID HEIGHT ABOVE SURFACE - METERS



## AVOID AREA

6 FT DEMONSTRATED TO 9000 FEET DENSITY ALTITUDE

## TC APPROVED BHT-429-FMS-11

10 JAN 2012 9 ECCN EAR99 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 H D

8 0 0 0 1 4

, 0 0 0

6 0 0 0

4 0 0 0

2 0 0 0 1 2

, 0 0 0

S E A

L E V

E

L

- 2 0 0 0 H

P - F T

1 0

, 0 0 0 1 6

, 0 0 0 1 8

, 0 0 0MINIMUM OAT O A

T

- °

C

4 0 3

0 2

0 1 0 0

- 2

0 2 0

, 0 0 0



### -10 & -30 -40 AREA B AREA C



### AREA AMAX GROSS WEIGHT = 7500 LB 

### MAXIMUM OAT 17,000 FT H D



### 13,000 FT H D

M A X I M U M O A T

## 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 H D

8 0 0 0 1 4

, 0 0 0

6 0 0 0

4 0 0 0

2 0 0 0 1 2

, 0 0 0

S E A

L E V

E

L

- 2 0 0 0 H

P - F T

1 0

, 0 0 0 1 6

, 0 0 0 1 8

, 0 0 0MINIMUM OAT O A

T

- °

C

2

0 1 0 2 0

, 0 0 0



### -40 AREA B AREA C



### AREA A 17,000 FT H D



### 13,000 FT H D

M A X I M U M O A T 

### -10

- 2

0

&

- 3

0 0MAX GROSS WEIGHT = 7500 LB

## TC APPROVED BHT-429-FMS-11

10 JAN 2012 11 ECCN EAR99 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 H D

8 0 0 0 1 4

, 0 0 0

6 0 0 0

4 0 0 0

2 0 0 0 1 2

, 0 0 0

S E A

L E V

E

L

- 2 0 0 0 H

P - F T

1 0

, 0 0 0 1 6

, 0 0 0 1 8

, 0 0 0MINIMUM OAT

5 1

. 7 5

0 4

0 3

0 2

0 1 0 0 - 1 0

- 3

0 - 2

0

- 4

0 2 0

, 0 0 0

O A

T

- °

C 

### AREA C AREA B



### AREA A 17,000 FT H D



### 13,000 FT H D

M A X I M U M O A T M A

X

I M

U

M

O

A

TMAX 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 H D

8 0 0 0 1 4

, 0 0 0

6 0 0 0

4 0 0 0

2 0 0 0 1 2

, 0 0 0

S E A

L E V

E

L

- 2 0 0 0 H

P - F T

1 0

, 0 0 0 1 6

, 0 0 0 1 8

, 0 0 0MINIMUM OAT 2 0 1 0 0 - 1 0 2 0

, 0 0 0

O A

T

- °

C 

### AREA C AREA B



### AREA A 17,000 FT H D



### 13,000 FT H D

M A X I M U M O A T 

### -30

-20

- 4

0MAX GROSS WEIGHT = 7500 LB

## TC APPROVED BHT-429-FMS-11

10 JAN 2012 13 ECCN EAR99 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 H D

8 0 0 0 1 4

, 0 0 0

6 0 0 0

4 0 0 0

2 0 0 0 1 2

, 0 0 0

S E A

L E V

E

L

- 2 0 0 0 H

P - F T

1 0

, 0 0 0 1 6

, 0 0 0 1 8

, 0 0 0MINIMUM OAT
4 0 3

0 2

0 1 0 0

- 2

0 2 0

, 0 0 0 O A

T

- °

C



### -10 & -30

-40 AREA B AREA C



### AREA A MAXIMUM OAT 13,000 FT H D 

### 17,000 FT H D

M A X I M U M O A TMAX 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 H D

8 0 0 0 1 4

, 0 0 0

6 0 0 0

4 0 0 0

2 0 0 0 1 2

, 0 0 0

S E A

L E V

E

L

- 2 0 0 0 H

P - F T

1 0

, 0 0 0 1 6

, 0 0 0 1 8

, 0 0 0MINIMUM OAT 2 0 1 0 - 2

0

&

- 3 0 2 0

, 0 0 0

O A

T

- °

C



### -40 AREA B AREA C



### AREA A 13,000 FT H D 

### 17,000 FT H D

M A X I M U M O A T 0 

### -10MAX GROSS WEIGHT = 7500 LB

## TC APPROVED BHT-429-FMS-11

10 JAN 2012 15 ECCN EAR99 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 H D

8 0 0 0 1 4

, 0 0 0

6 0 0 0

4 0 0 0

2 0 0 0 1 2

, 0 0 0

S E A

L E V

E

L

- 2 0 0 0 H

P - F T

1 0

, 0 0 0 1 6

, 0 0 0 1 8

, 0 0 0MINIMUM OAT

5 1

. 7 5

0 4

0 3

0 2

0 1 0 0 - 1 0 - 2 0

- 3 0

&

- 4

0 2 0

, 0 0 0

O A

T

- °

C 

### AREA B AREA C



### AREA A 17,000 FT H D



### 13,000 FT H D

M A X I M U M O A T M A

X

I M

U

M

O

A

TMAX 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 H D

8 0 0 0 1 4

, 0 0 0

6 0 0 0

4 0 0 0

2 0 0 0 1 2

, 0 0 0

S E A

L E V

E

L

- 2 0 0 0 H

P - F T

1 0

, 0 0 0 1 6

, 0 0 0 1 8

, 0 0 0MINIMUM OAT 2 0 1 0 0

- 3 0

&

- 4

0 2 0

, 0 0 0

O A

T

- °

C 

### AREA B AREA C



### AREA A 17,000 FT H D



### 13,000 FT H D

M A X I M U M O A T 

### -20 -10MAX GROSS WEIGHT = 7500 LB

## TC APPROVED BHT-429-FMS-11

10 JAN 2012 17 ECCN EAR99 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 20,000PRESSURE 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 6PRESSURE ALTITUDE - 1000 METERS O

A

T

- ° C

M A X

O A T 0 - 1 0 - 2 0 - 4 0

5 0 1 0

3 0 2 0

4 0 - 3 0

## 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 20,000PRESSURE 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 6PRESSURE ALTITUDE - 1000 METERS O

A

T

- ° C

0

1 0 20 - 2 0

5 0 M A X O A T

4 0 - 3 0

- 1 0 - 4 0 

### 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

3 0

## TC APPROVED BHT-429-FMS-11

10 JAN 2012 19 ECCN EAR99 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 20,000PRESSURE 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 6PRESSURE ALTITUDE - 1000 METERS

M

A

X

O

A

T 

### 0 

### 1

0 - 1

0 - 2

0 O

A

T

- °

C

- 4

0



### 3

0

5 0 

### 2

0

4

0 

### - 3

0

## 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 20,000PRESSURE 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 6PRESSURE ALTITUDE - 1000 METERS

M

A

X

O

A

T 

### 0 1

0 - 3

0 

### O

A

T

- °

C

- 4

0

3

0 

### 2

0

5

0 

### 4 0



### - 1

0 - 2

0

## BHT-429-FMS-11

10 JAN 2012 21 ECCN EAR99 

# 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 E M P T Y W E I G H T x ( C G

- 2 3 0

. 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

F w d L i m i t

A f t L i m i t



### 220 222 224 226 228 230 232 234 Longitudinal CG (inches) GROSS WEIGHT / CENTER OF GRAVITY CHARTGross Weight (pounds)

* Most forward extreme CG condition.

## BHT-429-FMS-11

10 JAN 2012 23 ECCN EAR99 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 E M P T Y W E I G H T x ( C G

- 5 8 4 2 ) 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

F w d L i m i t

A f t L i m i t



## 5600 5650 5700 5750 5800 5850 5900 5950
Longitudinal CG (mm) GROSS WEIGHT / CENTER OF GRAVITY CHARTGross 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 E M P T Y W E I G H T x ( C G

- 2 3 0

. 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 F w d L i m i t

A f t L i m i t (12.5)



### 220 222 224 226 228 230 232 234 Longitudinal CG (inches) GROSS WEIGHT / CENTER OF GRAVITY CHARTGross 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 E M P T Y W E I G H T x ( C G

- 5 8 4 2 ) 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 F w d L i m i t

A f t L i m i t (12.5)



## 5600 5650 5700 5750 5800 5850 5900 5950
Longitudinal CG (mm) GROSS WEIGHT / CENTER OF GRAVITY CHARTGross Weight (Kg)

* Most forward extreme CG condition.



## 10 JAN 2012 25/26