bell 206a - flight manual

465
BHT-206A-FM-1 MODEL 206A ROTORCRAFT FLIGHT MANUAL TYPE CERTIFICATE NO. H-92 REGISTRATION SERIAL NO. APPROVED BY DATE 14 SEPTEMBER 1995 DIRECTOR-AIRWORTHINESS BRANCH DEPARTMENT OF TRANSPORT THE AVIATION REGULATORY AUTHORITY FOR THIS FLIGHT MANUAL IS THE CANADIAN DEPARTMENT OF TRANSPORT, AIRWORTHINESS BRANCH. U.S. REGISTERED HELICOPTERS ARE APPROVED BY THE FAA IN ACCORDANCE WITH THE PROVISIONS OF 14 CFR SECTION 21.29 ON 14 SEPTEMBER 1995 THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS Bell Helicopter A Subsidiary of Textron Inc POST OFFICE BOX 482 FORT WORTH, TEXAS 76101 COPYRIGHT NOTICE COPYRIGHT 2000 BELL ® HELICOPTER TEXTRON INC. AND BELL HELICOPTER TEXTRON, A DIVISION OFTEXTRON CANADA LTD. ALL RIGHTS RESERVED 15 MAY 1970 REVISION D-44 - 06 OCTOBER 2000

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Bell 206A - Flight Manual*For enthusiast purposes only, always refer to the up-to-date manual in the aircraft*

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Page 1: Bell 206A - Flight Manual

BHT-206A-FM-1

MODEL206A

ROTORCRAFTFLIGHT MANUAL

TYPE CERTIFICATE NO. H-92

REGISTRATION SERIAL NO.

APPROVED BY DATE 14 SEPTEMBER 1995

DIRECTOR-AIRWORTHINESS BRANCHDEPARTMENT OF TRANSPORT

THE AVIATION REGULATORY AUTHORITY FOR THIS FLIGHT MANUAL IS THECANADIAN DEPARTMENT OF TRANSPORT, AIRWORTHINESS BRANCH.

U.S. REGISTERED HELICOPTERS ARE APPROVED BY THE FAA IN ACCORDANCEWITH THE PROVISIONS OF 14 CFR SECTION 21.29 ON 14 SEPTEMBER 1995

THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS

Bell HelicopterA Subsidiary of Textron Inc

POST OFFICE BOX 482 FORT WORTH, TEXAS 76101COPYRIGHT NOTICE

COPYRIGHT 2000BELL ® HELICOPTER TEXTRON INC.AND BELL HELICOPTER TEXTRON,A DIVISION OF TEXTRON CANADA LTD.

ALL RIGHTS RESERVED 15 MAY 1970REVISION D-44 - 06 OCTOBER 2000

Page 2: Bell 206A - Flight Manual

Index 206A FLIGHT MANUAL DOT APPROVED

BHT-206A-FM-1

FLIGHT MANUAL INDEX

DOT APPROVED SECTIONS

SECTION 1 OPERATING LIMITATIONS

SECTION 2 OPERATING PROCEDURESNORMAL PROCEDURESEMERGENCY PROCEDURES

SECTION 3 PERFORMANCE DATA

MANUFACTURER'S DATA

SECTION 4 WEIGHT AND BALANCE

SECTION 5 FUEL AND OIL DATA

SECTION 6 CHARTS AND TABLES

SECTION 7 OPTIONAL EQUIPMENTAND SUPPLEMENTS

Index Rev. D-42

Page 3: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Log of Revisions

BHT-206A-FM-1

LOG OF APPROVED REVISIONS

NO. DATE NO. DATE

Original ..... 0 ...... 20 Oct 66 Revision .. D-22 ...... 17 Jun 75Reissued ... 0 ....... 15 May 70 Revision .. D-23 ...... 28 Aug 75Revision ... D-1 ....... 23 Jul 70 Revision .. D-24 ...... 18 Sep 75Revision ... D-2 ...... 06 Aug 70 Revision .. D-25 ...... 28 Apr 76Revision ... D-3 ...... 20 Aug 70 Revision .. D-26 ...... 22 Sep 76Revision ... D-4 ...... 04 Sep 70 Revision .. D-27 ...... 05 Sep 77Revision ... D-5 ...... 16Oct70 Revision .. D-28 ...... 16Feb79Revision ... D-6 ...... 30 Oct 70 Revision .. D-29 ...... 13 May 81Revision ... D-7 ...... 08 Jan 71 Revision .. D-30 ...... 01 Jun 81Revision ... D-8 ...... 12 Mar 71 Revision .. D-31 ...... 30 Oct 81Revision ... D-9 ...... 25 Jun 71 Revision .. D-32 ...... 06 Apr 82Revision .. D-10 ..... 06 Oct 71 Revision .. D-33 ..... 12 Nov 82Revision .. D-11 ...... 18 Oct 71 Revision .. D-34 ...... 08 Nov 83Revision .. D-12 ...... 17 Dec 71 Revision .. D-35 ...... 12 Dec 83Revision .. D-13 ..... 08 Feb 72 Revision ..- 36 ...... 26 Oct 84Revision ..- 14 ...... 16 Jun 72 Revision .. D-37 ...... 13 Sep 85Revision .. D-15 ...... 26 Jun 72 Revision .. D-38 ...... 09 Mar 88Revision .. D-16 ...... 28 Jul 72 Revision .. D-39 ...... 14 Oct 88Revision .. D-17 ...... 20 Nov 72 Revision D.. -40 ...... 24 Feb 89Revision .. D-18 ...... 15 Dec 72 Revision .. D-41 ...... 25 May 90Revision .. D-19 ...... 23 Apr 74 Revision .. D-42 ...... 14 Sep 95Revision .. -20 ...... 17 May 74 Revision .. D-43 ...... 27 Feb 97Revision .. D-21 ...... 21 Jun 74 Revision .. D-44 ...... 06 Oct 00

APPROVED:

CHIEF, FLIGH STFORDIRECTOR - AIRCRAFT CERTIFICATIONTRANSPORT CANADA

NOTE: Revised text is indicated by a black vertical line.Insert latest revision pages; dispose of superseded pages.

October 6, 2000 Rev. D-44 A

Page 4: Bell 206A - Flight Manual

Log of Pages 206A FLIGHT MANUAL TC APPROVED

BHT-206A-FM-1

LOG OF PAGES

FLIGHT MANUAL MANUFACTURER'S DATA

REVISION REVISIONPAGES NO. PAGES NO.

Cover ..................... 37 3-1 - 3-36 ................. 37Title ................ .... 44 4-1--4-4 .................. 37Index ...................... 42 5-1 -5-5 .................. 37A- B ..................... 44 5-6 ........................ 43i .......................... 38 5-7- 5-8 .................. 37ii ......... ................ 40 5-9 ........................ 43iii - iv ..................... 38 5-10-5-16 ................ 371-1 -1-2 .................. 37 6-1 -6-6 .................. 371-2A - 1-2B ............... 37 6-7/6-8 ..................... 371-2C/1-2D .................. 37 7-1 - 7-2 .................. 381-3 -1-4 .................. 37 7-3 - 7-4 .................. 431-5 - 1-6 .................. 42 7-5/7-6 ..................... 431-7--1-8 .................. 371-8A/1-8B .................. 371-9 - 1-10 ................. 371-11 ....................... 441-12 ....................... 392-1 -2-4 .................. 382-5 ........................ 432-6 ........................ 382-6A ....................... 432-6B - 2-6F ................ 38

6G 2-6-6H .................. 412-7 ........................ 382-8 - 2-9 .................. 372-10 ....................... 402-10A ...................... 412-10B -2-10D ............. 402-E2-10E2-10F ................ 402-11 -2-12 .............. 372-12A - 2-12B ............. 372-13 - 2-16 .............. 37

NOTE: Revised text is indicated by a black vertical line.Insert latest revision pages; dispose of superseded pages.

B Rev. D-44 October 6, 2000

Page 5: Bell 206A - Flight Manual

206A FLIGHT MANUAL General Information

BHT-206A-FM-1

GENERAL

ORGANIZATION

This manual is organized into two parts. Part 1 (Sections 1 through 3) contain DOT Approved data. Part 2 (Section 4 through 7) contains supplemental data provided by the manufacturer.

TERMINOLOGY

WARNINGS, CAUTIONS, AND NOTES

Warnings, cautions, and notes are used throughout this manual to emphasize important and critical instructions as follows:

An operating procedure, practice, etc., which, if not correctly followed, could result in personal injury or loss of life.

An operating procedure, practice, etc., which if not strictly observed, could result in damage to or destruction of equipment.

NOTE

An operating procedure, condition, etc., which is essential to highlight.

Rev. D-42 General Information- 1

Page 6: Bell 206A - Flight Manual

General Information 206A FLIGHT MANUAL DOT APPROVED

BHT-206A-FM-1

USE OF PROCEDURAL WORDS

The concept of procedural word usage and intended meaning which has been adhered to in preparing this manual is as follows:

“Shall” has been used only when application of a procedure mandatory.

is

“Should” has been used only when application of a procedure recommended.

is

.

“May” and “need not” have been used only when application of a procedure is optional.

“Will” has been used only to indicate futurity, never to indicate a mandatory procedure.

General Information-2 Rev. D-42

Page 7: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Table of Contents

BHT-206A-FM- 1

I I

Table of Contents

SECTION 1 OPERATING LIMITATIONS

Weight Limitations ................................ Airspeed Limitations ............................... Altitude Limitations ............................... Rotor Limitations. ................................. Power Plant Limitations ............................ Engine Power Limitations. .......................... Engine Starter Limits .............................. Engine Anti-Ice Limitations. ........................ Transmission Limitations ........................... Transmission and Tail Rotor Gearbox Oil Limitations. ..... Placards ......................................... Instrument Markings. .............................. Front Seat Minimum Weight Limits. .................. Longitudinal Center of Gravity Limits. ................ Longitudinal Center of Gravity Limits -

Doors Off ....................................... Center of Gravity vs Gross Weight .................... Lateral CG Limits ................................. Flight Crew ....................................... Type of Operation .................................... Night Flight Limitations ............................. Operation - Doors Off ...............................

SECTION 2 OPERATING PROCEDURES

NORMAL PROCEDURES

Introduction. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Operating Limitations. ...............................

Use or disclosure of data contained on this page is subject to the restriction on the title page of this document. Rev. D-38

PAGE

l-l l-l l-2 l-2 l-2 l-3 l-4 l-4 l-4 l-4 l-5 l-6 l-8 l-8

l-8A l-9

l-10 l-11 l-11

1-12

2-1 2-l

Page 8: Bell 206A - Flight Manual

Table of 206A FLIGHT MANUAL FAA APPROVED Contents

BHT-206A-FM-1

Flight Planning ...................................... Takeoff and Landing Data ...................... . .... Weight and Balance. ................................. Preflight Check ...................................... Before Exterior Check.. .............................. Exterior Check ....................................... Interior Check ........................................ Engine Prestart Check ............................... Engine Starting ...................................... Engine Run-Up Check. ............................... Before Takeoff.......................: ............. Takeoff ........................................... In Flight Operation. ................................ Descent and Landing ............................... Engine Shutdown .................................. After Exiting Helicopter. ............................

EMERGENCY PROCEDURES

Caution System.. ................................. Engine Failure .................................... Tail Rotor Control Failure ........................... Fuel Control and/or Governor Failure. ................. Hydraulic System Failure. ........................... Electrical Power Failure ............................ Fuel System Failure. ............................... Engine Fuel System Failure ......................... Helicopter Fuel System Failure. ...................... Engine Fire During Start. ........................... Engine Fire During Flight ........................... Engine Air Start. ..................................

SECTION 3 PERFORMANCE DATA

Power Check Procedure ............................. Power Check Chart. ................................ Height Velocity Diagram. ........................... Density Altitude. ..................................

PAGE 2-1 2-2 2-2 2-2 2-3 ‘-, 2-3

2-6F 2-6G

2-7 2-10

2-10A 2-10A 2-10A 2-10C 2-10D 2-10E I

2-11 2-12A 2-12B 2-13 2-13 2-14 2-14 2-14 2-14 2-15 2-15 2-16

3-l 3-2 3-3 3-3

ii Rev. D-40

Use or disclosure of data contained on this page is subject to the restriction on the title page of this document.

Page 9: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Table of Contents

BHT-206A-FM-1

.. Operation vs Allowable Wind ........................ Height-Velocity Diagram ... . ........................ Altitude vs Gross Weight Limits for

Height Velocity Diagram .......................... Airspeed Installation Correction Table. ................ Density Altitude Chart ............................. IGE and OGE Hover Ceilings ........................ Critical Relative Wind

AzimuthArea .................................... Hover Ceiling IGE Takeoff Power

5° to -25°C ..................................... Hover Ceiling IGE Takeoff Power

5° to 37.8°C .................................... Hover Ceiling OGE Takeoff Power

5° to -25°C ..................................... Hover Ceiling OGE Takeoff Power 5° to 37.8°C ......... Hover Ceiling IGE Maximum Continuous Power

5° to -25°C ..................................... Hover Ceiling IGE Maximum Continuous Power

5° to 37.8°C .................................... Hover Ceiling OGE Maximum Continuous Power

5° to -25°C ..................................... Hover Ceiling OGE Maximum Continuous Power

5° to 37.8°C .................................... Rate of Climb ..................................... RateofClimb-Door(s) .......................... Rate of Climb - Maximum Take-off Power

Anti-Ice Off. .................................... Rate of Climb - Maximum Continuous Power

Anti-Ice Off. .................................... Rate of Climb - Maximum Take-off Power

Anti-Ice On . ..................................... Rate of Climb - Maximum Continuous Power

Anti-Ice On .....................................

MANUFACTURER’S DATA

SECTION 4 WEIGHT AND BALANCE DATA

Weight Empty Center of Gravity. .....................

Rev. D-38

PAGE 3-4 3-5

3-6 3-7 3-8 3-9

3-11

3-12

3-13

3-14 3-15

3-16

3-17

3-18

3-19 3-20 3-20

3-21

3-25

3-29

3-33

4-l

. . . I

Page 10: Bell 206A - Flight Manual

Table of 206A FLIGHT MANUAL FAA APPROVED Contents

BHT-206A-FM-1

Gross Weight Center of Gravity. ...................... Cockpit and Cabin Loading .......................... FuelLoading ...................................... Baggage Compartment Loading ...................... Weight and Balance Charts and Diagrams. ............. Fuselage Stations. ................................. LoadingChart .....................................

SECTION 5 FUEL AND OIL DATA

Fuels.. ........................................... Fuel System Servicing ............................... Anti - Icing Fuel Additive. ............................. Oils .............................................. EngineOils ........................................ Engine Oil System Servicing .......................... Transmission and Tail Rotor Gearbox Oils. ............... Transmission and Tail Rotor Gearbox Servicing ........... Hydraulic Fluids. ................................... Hydraulic Fluids Servicing. ...........................

SECTION 6 CHARTS AND TABLES

Standard Atmosphere Table ......................... Density Altitude Chart ............................. Centigrade-Fahrenheit Conversion Table. ............. Velocity Conversion Table. ...........................

SECTION 7 OPTIONAL EQUIPMENT AND SUPPLEMENTS

Flight Manual Supplements List .......................

PAGE 4-l

4-l 4-2 4-2 4-2 4-3 4-4

5-1 5-l 5-2 5-5 5-6 5-8 5-9

5-13 5-14 5-15

6-2 6-3 6-4

7-1

iv Rev. D-38

Page 11: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 1

BHT-206A-FM-1 I

COMPLIANCE WITH SECTION 1 OF THIS MANUAL IS MANDATORY

WEIGHT LIMITATIONS

Maximum approved internal gross weight is 3000 pounds, doors on or off.

AIRSPEED LIMITATIONS

NOTE

All airspeed values given throughout this flight manual are for Calibrated Airspeed (CAS), except when Indicated Airspeed (IAS) is specifically stated.

Vne 150 MPH (130 knots), sealevel to 3000feet density altitude.

Decrease Vne 4.0 MPH (3.5 knots), per 1000 feet above 3000 feet density altitude.

Vne steady state autorotation 115 MPH (lOOk) IAS. I

Airspeed limitations with door(s) removed shall be adhered to strictly. Airspeeds exceeding limits will cause cyclic control deterioration and a reversal of fore/aft cyclic stick position gradient.

Rev. D-37 l-l

Page 12: Bell 206A - Flight Manual

Section 1 206A FLIGHT MANUAL FAA APPROVED

BHT-206A-FM-1

AIRSPEED LIMITATIONS (Cont)

AFT DOOR(S) OFF

Vne power on or off is 100 MPH (87 knots) with one or both aft cabin doors off sea level to 3000 feet density altitude.

Decrease Vne one MPH (one knot) per 1000 feet above 3000 feet density altitude.

FORWARD OR FORWARD AND AFT DOOR(S) OFF

Vne power on or off is 80 MPH (69 knots) with one or both forward, or any combination of forward and aft doors off, sea level to 3000 feet altitude.

Decrease Vne one MPH (one knot) per 1000 feet above 3000 feet density altitude.

85 TO 100% TORQUE TAKEOFF POWER RANGE

Vne 92 MPH (80 knots).

ALTITUDE LIMITATIONS

Maximum operating pressure altitude is 20,000 feet.

ROTOR RPM LIMITATIONS

/ POWER ON

Maximum 100%

Minimum 95%

50% to 60% - Accelerate through this range as rapidly as possible with cyclic control in neutral.

I POWER OFF

Maximum 107%

Minimum 90%

1-2 Rev. D-37

Page 13: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 1

POWER PLANT LIMITATIONS

Allison Model 250-C18 or 250-C18B

POWER TURBINE RPM (N2)

Maximum - 100%

Minimum - 95% - below 8000 feet

Minimum - 97% - above 8000 feet

BHT-206A-FM-1

Use of the throttle to control RPM is NOT AUTHORIZED. (Refer to Section 2, Emergency Procedures for exception.)

N2 TRANSIENT OVERSPEED LIMITS

N2 TRANSIENT OVERSPEED

LIMITS 15 SECOND MAX.

SHADED AREA REPRESENTS

ALLOWABLE OVERSPEED

ENGINE TORQUE %

GAS PRODUCER RPM (Nl )

Maximum - 104% RPM

Transients - 105% (maximum of 15 seconds)

FUEL

ASTM D-1655, Type B (JP-4) for all temperatures.

ASTM D-1655, Type A or A-l (JP-5) above -17.8”C (O’F).

I

Rev. D-37 1-2A

Page 14: Bell 206A - Flight Manual

I Section 1 206A FLIGHT MANUAL FAA APPROVED

BHT-206A-FM-1

POWER PLANT LIMITATIONS (Cont)

I

Helicopters equipped with airframe mounted fuel filter do not require the use of anti-icing additive at any ambient temperature. Refer to Allison Operation and Maintenance Manual for AVGAS mix, Cold Weather Fuel and Blending Instructions.

When operating in temperatures below 40°F (4°C), with no airframe fuel filter installed, all fuel, including AVGAS jet fuel mix, used in this helicopter must contain an anti - icing additive meeting the requirements of PFA - 55MB. Concentration of this additive in fuel in a loaded fuel tank must not be less than 0.035 percent nor more than 0.15 percent by volume. The minimum concentration of the additive in the fuel with which the aircraft is to be refueled should be at least 0.06 percent by volume to assure a loaded fuel tank concentration of at least 0.035 percent. (Refer to Section 5 for blending procedures).

FUEL BOOST PUMPS

Fuel boost pumps SHALL BE ON at all times when engine is being operated.

OIL

Aircraft turbine engine oil MIL-L-7808F, MIL-L-7808G, MIL-L-23699 or turbine oil 555. (Refer to Section 5 for list of approved oils.)

Operation with MILL23699 and turbine oil 555 limited to ambient temperature above -40°C (-40°F).

MIXING OF OILS

Refer to Allison Model 250 series engine data regarding mixing of oils of different brands, types and manufacturers.

1-2B Rev. D-37

Page 15: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 1

BHT-206A-FM-1 I

POWER PLANT LIMITATIONS (Cont)

FUEL PRESSURE

Maximum - 50.0 PSI. Minimum - 8.0 PSI.

Optional per Technical Bulletin No. 206-08-74-l

Maximum - 50.0 PSI. Minimum - 4.0 PSI.

OIL PRESSURE

90 to 130 PSI - Gas Producer Speed above 78%.

50 PSI minimum - Gas Producer Speed below 78%.

OIL TEMPERATURE

107°C maximum.

Rev. D-37

Page 16: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 1

BHT-206A-FM-1 I

ENGINE POWER LIMITATIONS

TORQUE

Takeoff - 100% (5 MINUTE LIMIT).

Maximum Continuous - 85.0%.

TURBINE OUTLET TEMPERATURE (TOT)

NOTE

Rev. D-37 l-3

Page 17: Bell 206A - Flight Manual

Section 1 206A FLIGHT MANUAL FAA APPROVED

BHT-206A-FM-1

ENGINE STARTER LIMITS

Limit starter energized time to the following:

External Power Start Battery Start

25 Seconds - ON 40 Seconds - ON 30 Seconds - OFF 60 Seconds - OFF 25 Seconds - ON 40 Seconds - ON 30 Seconds - OFF 60 Seconds - OFF 25 Seconds - ON 40 Seconds - ON 30 Minutes - OFF 30 Minutes - OFF

ENGINE ANTI-ICE LIMITATIONS

TRANSMISSION LIMITATIONS

OIL PRESSURE - Minimum 30 PSI

Continuous operation 30 to 50 PSI

Maximum 70 PSI

OIL TEMPERATURE- Maximum 110°C

TRANSMISSION AND TAIL ROTOR GEARBOX OIL LIMITATIONS

1-4 Rev. D-37

Page 18: Bell 206A - Flight Manual

DOT APPROVED 206A FLIGHT MANUAL Section 1

PLACARDS BHT-206A-FM-1

THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE

APPROVED ROTORCRAFT FLIGHT MANUAL I

MINIMUM PILOT WEIGHT 150 LBS

AIRSPEED LIMITATIONS BASIC CONFIGURATION 3000 LBS GROSS WEIGHT OR LESS

VNE 150 MPS SEA LEVEL TO 3000 FEET ABOVE 3000 FEET DECREASE VNE 4.0 MPH PER 1000 FEET I MAXIMUM ALTITUDE 20,000 FEET

If airspeed indicator is marked in knots, the airspeed limitations placard must be changed to read as follows:

Airspeed Limitations - Basic Configuration Vne 130 knots at sea level to 3000 feet. Above 3000 feet reduce Vne 3.5 knots per 1000 feet.

FWD DOOR(S) OFF Vne 80 MPH (69 knots) CG 106-110)

(Located on both forward doorframe posts.)

CARGO MUST BE SECURED IN ACCORDANCE WITH FLIGHT MANUAL INSTRUCTION I

(Located on the inside of baggage compartment door.)

POWER TURBINE (N2) LIMITATIONS

MAX. TURB. - 100% MIN. TURB. - 97%

ABOVE 8000 FT

Rev. D-42 l-5

Page 19: Bell 206A - Flight Manual

I Section 1

BHT-206A-FM-1

206A FLIGHT MANUAL DOT APPROVED

INSTRUMENT MARKINGS (Sheet 1 Of 21

l-6 Rev. D-42

Page 20: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL sectiil

BHT-206A-FM-1

: -

INSTRWENT MARKINGS (Sheet 2 of 2)

Rev. D-37 l-7

Page 21: Bell 206A - Flight Manual

I Section 1

BHT-206A-FM-1

206A FLIGHT MANUAL FAA APPROVED

FRONT SEAT MINIMUM WEIGHT LIMIT

Minimum crew weight in the cockpit is 150 pounds (68 kilograms).

LONGITUDINAL CENTER OF GRAVITY LIMITS

NOTE

Ballast as required to maintain weight empty CG within limits shown on Center of Gravity vs Weight Empty chart in Maintenance Manual.

Longitudinal center of gravity limits are station 106.0 and station 114.2; however, the aft limit is variable depending upon gross weight. Refer to Center of Gravity vs Gross Weight Chart. These center of gravity limits are such that they shall not be exceeded for any total weight within the limitations of the Loading Chart.

NOTE

Station 0 (datum) is located 55.16 inches forward of forward jack-point center line.

EXAMPLE:

Assume helicopter has gross weight of 3000 pounds with calculated CG of 110.0. Determine if helicopter is within gross weight vs CG limits.

On Center of Gravity vs Gross Weight Chart, enter horizontal scale at 110.0.

Proceed upward to the intersection of the horizontal Gross Weight 3000 pound line. The intersection point is located within the Gross Weight-CG envelope therefore the Gross Weight and CG are within the allowable limits.

1-8 Rev. D-37

Page 22: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 1

BHT-206A-FM-1

LONGITUDINAL CENTER OF GRAVITY LIMITS - DOORS OFF

No change from basic helicopter CG limits with only the aft cabin door(s) off.

Longitudinal CG limits are stations 106.0 and 110.0 with one or both forward doors off or any combination of forward and aft cabin doors off.

Actual weight change shall be determined after doors, etc., have been removed and ballast readjusted, if necessary, to return empty weight center of gravity to within allowable limits.

Rev. D-37 l-8A/1-8B

Page 23: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL

BHT-206A-FM-1

CENTER OF GRAVITY vs GROSS WEIGHT

Rev. D-37 1-9

Page 24: Bell 206A - Flight Manual

I Section 1 206A FLIGHT MANUAL

BHT-206A-FM-1

LATERAL CG LIMITS

FAA APPROVED

3.0 inches left of aircraft center line.

4.0 inches right of aircraft center line.

LATERAL vs LONGITUDINAL CG LIMITS

DOORS ON AND OFF

mm IN.

LATERAL VS LONGITUDINAL CG LIMITS

-58.4 mm - 2.3 IN.

I

50.8 101.6

LATERAL CENTER OF GRAVITY

206900-242A

l-10 Rev. D-37

Page 25: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 1

BHT-206A-FM-1

FLIGHT CREW

The minimum flight crew consists of one pilot who shall operatethe helicopter from the right crew seat.

The left crew seat may be used for an additional pilot when theapproved dual controls are installed.

TYPE OF OPERATION

Basic configuration of the helicopter permits its use as a five placehelicopter for operation on land, day, under VFR nonicingconditions.

OPERATIONAL EQUIPMENT LIMITATIONS

The following equipment shall be installed when conducting flightoperations in falling and/or blowing snow to reduce possibility ofengine flameout:

The Snow Particle Separator Engine Air Induction System Kit(BHT-206A-FMS-18), Deflector Kit (BHT-206A-FMS-24), andEngine (Automatic) Re-ignition (BHT-206A-FMS-25).

Or:

The Snow Witerization Air Induction System (BHT-206A-FMS-11)and Engine (Automatic) Re-ignition (BHT-206A-FMS-25).

For Limitations and Performance Data pertaining to installedkits, refer to appropriate flight manual supplement.

Flight operations are approved with landing gear fairingsremoved.

NIGHT FLIGHT LIMITATIONS

Night flight operation is limited to visual contact flight conditions.Orientation shall be maintained through visual reference toground objects solely as a result of lights on the ground or adequatecelestial illumination.

October 6, 2000 Rev. D-44 1-11

Page 26: Bell 206A - Flight Manual

Section 1 206A FLIGHT MANUAL FAA APPROVED

BHT-206A-FM-1

OPERATION

Turn anti-collision light OFF during flight in or near visiblemoisture to prevent uncommon reflections and possible pilotvertigo.

NOTE

Keep cabin glass clean to prevent halation.Limit operation of beacon light on the ground,to prolong bulb life and to avoid mistakenidentity as an emergency ground vehicle whichuses a similar light.

OPERATION - DOORS OFF

Actual weight change shall be determined after doors, etc., havebeen removed and ballast readjusted, if necessary, to return emptyweight center of gravity to within allowable limits.

Flight operations with doors off requires removal of unsecureditems.

PROTRACTED REARWARD AND SIDEWARD FLIGHTPROHIBITED WITH ANY COMBINATION OF DOORS OFF.

External Cargo Loading limited to 3350 pounds gross weight withforward door(s) off or any combination of forward and aft doors off.(Maximum 3000 pounds internal gross weight.)

Forward door(s) off flight operations prohibited with the Littersoptional equipment installed.

1-12 Rev. D-39

Page 27: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 2

NORMAL PROCEDURES INTRODUCTION

This section contains instructions and procedures for operating the helicopter from the planning stage, through actual flight conditions, to securing the helicopter after landing.

Normal and standard conditions are assumed in these proce- dures. Pertinent data in other sections is referenced when applicable.

The instructions and procedures contained herein are written for the purpose of standardization and are not applicable to all situations.

OPERATING LIMITATIONS

The minimum and maximum limits, and the normal and cau- tionary operating ranges for the helicopter and its subsystems are indicated by instrument markings and placards. The instru- ment markings and placards represent careful aerodynamic calculations that are substantiated by flight test data. Refer to Section 1 for a detailed explanation of each operating limitation.

FLIGHT PLANNING

Planning of the mission to be accomplished will provide the pilot with the data to be used during flight. The information to be used can be compiled as follows:

Rev. D-38 2-l

Page 28: Bell 206A - Flight Manual

Section 2 206A FLIGHT MANUAL FAA APPROVED

BHT-206A-FM-1 Check type of mission to be performed and destination.

Select appropriate performance charts to be used from Section 3.

TAKEOFF AND LANDING DATA

Refer to Section 1 for takeoff and landing weight limits and to Section 3 for performance information.

WEIGHT AND BALANCE

Ascertain proper weight and balance of the helicopter as follows:

Consult applicable weight and balance instructions provided in Section 4.

Compute takeoff and anticipated landing gross weight, check helicopter center of gravity (CG) locations, and ascertain weight of fuel, oil, payload, etc.

Check that the weight and balance limitations listed in Section 1 have not been exceeded.

PREFLIGHT CHECK

The pilot is responsible for determining whether the helicopter is in condition for safe flight.

NOTE

The preflight check is not intended to be a de- tailed mechanical inspection, but simply a guide to help the pilot check the condition of the helicopter. It may be made as comprehen- sive as conditions warrant at the discretion of the pilot.

2-2 Rev. D-38

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BHT-206A-FM-1 NOTE

All areas checked shall include a visual check for evidence of corrosion, particularly when helicopter is flown near or over salt water or in areas of high industrial emissions.

BEFORE EXTERIOR CHECK

Mission Planning - Completed.

Publications - Checked.

Helicopter Servicing - Completed.

Ensure that the helicopter weight and balance are within limits. (Refer to Sections 1 and 4 of this manual and to appropriate sup- plement(s) for optional equipment.)

Battery - Connected and secure.

EXTERIOR CHECK

EXTERIOR CHECK DIAGRAM

Rev. D-38 2-3

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1. FUSELAGE - CABIN RIGHT SIDE.

Right static port - Condition.

Cabin doors - Condition and security.

Windows - Condition and security.

Landing gear - Condition. Ground handling wheel removed.

Forward and aft crosstube fairing - Secure, condition and aligned.

2. FUSELAGE - CENTER RIGHT SIDE.

Cabin roof, transmission fairing, and engine air inlet area - Cleaned of all debris and accumulated snow and ice.

Hydraulic reservoir - Oil level.

Hydraulic system filter - Bypass indicator retracted.

Hydraulic actuators and lines - Condition, security, inter- ference, leakage.

Forward fairing - Secured,

Access door - Secured.

2-4 Rev. D-38

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Transmission Area

Transmission - Oil level. Verify actual presence of oil in sight gage. Check area for leaks.

Transmission and mounts - Security and condition,

Isolation mount - Condition.

Drag pin - Security and evidence of contact with static stop plate.

Main driveshaft forward coupling - Condition, security and grease leakage. Check Temp-Plates (four places) for evidence of elevated temperature indicated by dot changing color to black.

If any Temp-Plate is missing or has black dots, maintenance personnel shall assist in determining airworthiness.

Access door - Secured.

Air induction cowling - Secured.

Engine inlet and plenum - Condition; clear of obstruction.

Fuel filler cap - Visually check level - Secure cap.

Fuel sump - Drain fuel sample as follows:

Manual Drain Valve Installed:

Drain valve - Depress.

Obtain sample.

Drain valve - Pull down to close.

Rev. D-43 2-5

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Electrical: or

Fuel boost pump circuit breakers - OUT.

Battery switch - ON.

Fuel valve switch - OFF.

Fuel drain button - Depress, drain sample, then release.

NOTE

Engine and airframe fuel filters are acces- sible from the left engine compartment.

Engine fuel filter - Drain and check before first flight of the day as follows:

Fuel valve switch - ON.

Fuel boost pump circuit breakers - IN.

Caution LT circuit breaker - IN.

Engine fuel filter drain valve - Open, drain sample, then close.

NOTE

A/F filter test switch is located on top of fuel filter.

A/F fuel filter test switch - Depress and check A/F FUEL FILTER caution light on. Release switch and check light out.

A/F fuel filter drain valve - Open, drain sample, then close.

Fuel valve switch - OFF.

Battery switch - OFF.

Rev. D-38

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Power Plant Area

Main driveshaft coupling - Condition, security and grease leakage. Check Temp-Plates (four places) for evidence of elevated temperature indicated by dot changing color to black.

If any Temp-Plate is missing or has black dots, maintenance personnel shall assist in determining airworthiness.

Engine - Condition; security of attachments. Evidence of oil leakage.

Engine mounts - Condition and security.

Throttle linkage - Condition, security and freedom of operation.

Fuel control and governor - Evidence of leakage.

Hoses and tubing - Chafing, security and condition.

Exhaust stack and clamp - Security and condition.

Engine cowl - Secure.

Starter generator cooling scoop - Clear of debris.

Right exhaust cover - Removed.

The engine oil tank sight gage mounted on left side is not indicative of actual oil quantity. Oil quantity shall be checked with dipstick.

Oil tank - Oil level, leaks, security, and cap secure.

Access door - Secured.

Aft fairing - Secured.

Rev. D-43 2-6A

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Sectlon 2

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206A FLIGHT MANUAL FAA APPROVED

3. FUSELAGE - AFT RIGHT SIDE.

Fuselage - Condition.

Tail rotor driveshaft cover - Condition and secured.

Tailboom - Condition.

Horizontal stabilizer and position light - Condition and security.

Main rotor blade - Condition.

4. FUSELAGE - FULL AFT.

Vertical fin - Condition.

Tail rotor guard - Condition and security.

Anticollision light - Condition.

Aft position light - Condition.

Tail rotor gearbox - Security and evidence of leaks. Verify actual presence of oil in sight gage.

Tail rotor - Tiedown removed, condition and free move- ment.

Tail rotor controls - Condition and security.

Tail rotor blade - Condition. Tip block for rivet damage, corrosion, and seal condition.

2-6B Rev. D-38

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5. FUSELAGE - AFT LEFT SIDE.

Failure to remove rotor tiedowns before engine starting may result in severe damage and possible injury.

Main rotor blade - Tiedown removed; condition.

Tailboom - Condition.

Tail rotor driveshaft cover - Condition and secured.

Horizontal stabilizer and position light - Condition and security.

Fuselage - Condition.

Forward tail rotor driveshaft coupling - Condition of splined adapter and freedom of rotation of witness pin.

Oil cooler blower shaft hanger bearings - Evidence of grease leakage and overheating.

Oil cooler blower - Clear of obstruction and condition.

Oil cooler - Condition and leaks.

Aft fairing - Secured.

Baggage compartment - Cargo tied down. Door secure.

Left exhaust cover - Removed.

Powerplant Area

Engine - Condition, security of attachments.

Rev. D-38 2-6C

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Engine mounts - Condition and security.

Exhaust stack and clamp - Condition and security.

Evidence of fuel and oil leaks.

Hoses and tubing for chafing and condition.

Pneumatic lines - Condition and security.

Linear actuator and governor control linkage - Condition and security.

Engine de-ice valve and linkage - Condition and security.

Tail rotor driveshaft - Condition of splines, couplings and freedom of movement.

Engine cowling - Secured.

Air induction cowling - Secured.

Transmission Area

Transmission and mounts - Condition and security; area for leaks.

Isolation mount - Condition.

Access door - Secured.

6. FUSELAGE - CABIN LEFT SIDE.

Cabin roof, transmission fairing, and engine air inlet area - Cleaned of all debris and accumulated snow and ice.

Engine PLENUM chamber inspection window - Check Plenum clear.

2-6D Rev. D-38

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Rotor head reservoirs (oil lubricated) - Visible oil levels.

Main rotor hub and yoke - Condition.

Main rotor blade doublersand skin - Condition.

Pitch horn trunnion bearing - Wear and security.

Main rotor pitch links - Condition and security of attach- ment bolts and locking hardware.

Swashplate assembly - Condition, security of attached controls, and boot condition.

Control linkages to swashplate - Condition, security of at- tachment bolts and locking hardware.

Forward fairing and access door - Secured.

Cabin doors - Condition and security.

Windows - Condition and security.

Landing gear - Condition. Ground handling wheel removed.

Forward and aft crosstube fairings - Secure, condition and aligned.

Left static port - Condition.

7. FUSELAGE - FRONT.

Exterior surfaces - Condition.

Windshield - Condition and cleanliness.

Rev. D-38 24E

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Battery and vent lines - Condition and security.

Battery access door - Secured.

Pitot tube - Cover removed, clear of obstructions.

External power door - Condition and security.

Landing light glass - Condition.

Instrument panel vent - Clear of debris.

Antennas - Condition and security.

Main rotor blade - Condition.

Auxiliary power unit - Connect for APU start.

INTERIOR CHECK

Cabin interior - Cleanliness and security of equipment.

Fire Extinguisher - Secure. Charge indicator in green arc.

First aid kit - Secure (if installed).

Copilot controls - Security and proper installation.

Copilot seat belt - Secured (if solo).

Pilot seat belt - Fastened.

Cabin loading - Refer to Section 4.

Cabin doors - Secured.

2-6F Rev. D-38

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BHT-206A-FM-1

ENGINE PRESTART CHECK

Flight controls - Release friction; check freedom of movement and adjust to (cyclic) neutral/(collective) flat pitch position and pedals neutral.

Throttle - Check freedom of full travel and flight idle stop operation. Check copilot throttle if installed. Return to closed position.

LDG LTS switch - OFF.

ENGINE DEICING switch - OFF.

CONTROL BOOST switch - ON.

FUEL VALVE switch - ON.

Altimeter - Set.

Instruments/gages - Static position at zero.

Overhead switches - OFF.

NOTE

Effective helicopter S/N 154 and subsequent: For daylight operations, ensure INST LT switch (rheostat) is OFF. If the INST LT switch is on, the caution lights can be dimmed and may not be visible.

Overhead circuit breakers - IN.

GENerator switch - OFF.

Rev. D-41 2-6G/2-6H

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i

BATtery switch - ON (OFF if auxiliary power is used). Observe ENG OUT, ROTOR LOW RPM (if installed) GEN FAIL, and TRANS OIL PRESS lights ON. Applicable RPM audio signals - Check.

NOTE

Engine out audio may be deactivated.

Fuel boost pump, circuit breakers - Check IN.

Fuel pressure - Check, within limits.

ROTOR LOW RPM System Check -Collective pitch OFF down stop. ROTOR LOW RPM Light ON. ROTOR LOW RPM Audio ON.

Collective pitch FULL down. ROTOR LOW RPM Light ON. ROTOR LOW RPM Audio OFF.

Warning and Caution Lights - Test.

TOT LT TEST light (if installed) - Test.

ANTI-COLLision light switch - ON.

ENGINE STARTING Collective pitch - Full down.

- Throttle - Full closed.

Rotors - Clear.

-- STARTER - Engage (see starter limits, Section 1).

Engine oil pressure - Indication of increase.

Rev. D-38 2-7

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206A FLIGHT MANUAL FAA APPROVED

Throttle - Open to flight idle at 15% gas producer RPM with Turbine Outlet Temperature (TOT) at or below 15O°C.

A start should not be attempted at N1 speeds below 12%.

Use the following guide for desired N1 starting speed versus outside air temperature:

N1 RPM TEMP°C (°F) 15% Above 7° (45°) 13% - 18 to + 7° (0 to 45°) 12% Below - 18° (-0”)

NOTE

During the first few seconds of the start the TOT will accelerate at a fairly rapid rate and must be pilot monitored.

Turbine outlet temperature (TOT) - Monitor to avoid hot start. Abort start if either the 927°C maximum or the 749 to 927°C MAXIMUM 10 SECONDS transient limitation is about to be exceeded by depressing the engine IDLE RELease button, CLOSE THROTTLE and continue to motor the starter until TOT decreases to less than 749°C. If limits are exceeded consult Allison Engine Operation and Maintenance Manual.

If the main rotor is not rotating by 25% gas producer speed (N1), abort the start.

STARTER - Release at 58% gas producer RPM (N1).

2-B Rev. D-37

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Engine and transmission oil - Check pressures increasing.

If the engine has been shut down for more than 15 minutes, stabilize at idle speed for one minute before increasing power.

NOTE

During cold temperature operations stabilize engine at idle speed of 60 to 62% gas producer RPM (N1) until oil temperature reaches O°C.

Gas producer RPM (N1) - Check for 60 to 62%.

External power - Remove - BATtery ON.

Throttle - Open to 70% gas producer RPM.

GENerator switch - ON.

Radio equipment - ON.

POSition LT switch - ON.

ANTI COLLision LT switch - ON.

Overhead circuit breakers - Check in.

Fuel boost pump pressure - Check.

Caution light operation - Check.

Smoothly and firmly advance throttle at a continuous rate to full open position, maintaining collective pitch down and cyclic control in neutral.

Power turbine (N2) governor - Check range 95 to 100% RPM.

Use or disclosure of data contalned on this page is subject to the restriction on the title page of this document. Rev. D-37 2-S

Page 43: Bell 206A - Flight Manual

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ENGINE RUN-UP CHECK -

NOTE

If temperature is 4°C (40°F) or below and visible moisture is present, the engine anti-icing system shall be ON.

ENGINE DEICING switch - ON (if conditions warrant) and observe TOT rise.

PITOT HEAT switch - ON (if installed) in visible moisture with temperature below 4°C (40°F).

NOTE

The Hydraulic Systems Check is to determine proper operation of the hydraulic actuators for each flight control system. If abnormal forces, unequal forces, control binding or motoring are encountered, it may be an indication of a malfunction of a flight control actuator.

Collective - Full down, friction removed.

Rotor rpm (Nr) - Set to 100%.

CONTROL BOOST switch - OFF.

Cyclic - Centered, friction removed.

Check normal operation of cyclic control by moving cyclic forward, aft, left and right a slight amount (approximately one inch). Center cyclic.

Collective - Check for normal operations by increasing collective control slightly (1 to 2 inches). Repeat 2 to 3 times as required. Return to full down position.

I Use or disclosure of date contained on this page is subject to the restriction on I

2-10 Rev. D-40 I

Page 44: Bell 206A - Flight Manual

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BHT-206A-FM-1

Pedals (if hydraulically boosted) - Displace slightly left and right. Note an increase in force required to move pedal in each direction. Center pedals.

CONTROL BOOST switch - ON.

Cyclic and collective friction - Set as desired.

BEFORE TAKEOFF

Electrical equipment - Check; reset as required.

Lighting - As required.

INST LT switch (rheostat) - As desired.

Radio - Check as required.

Engine, transmission and electrical instruments - Check within limits.

Flight and navigation instruments - Check and set.

TAKEOFF

Collective pitch - Increase to hover.

Directional control - As required to maintain desired heading.

Cyclic control - Apply as required to accelerate smoothly.

Collective - Apply as required to obtain desired rate of climb and airspeed. Monitor engine limits and adjust collective, as necessary.

IN FLIGHT OPERATION

Airspeed - Within limits for density altitude, power, and door configuration.

Rev. D-41 2-10A

Page 45: Bell 206A - Flight Manual

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Airspeeds in excess of Airspeed Limitations Door(s) OFF will cause cyclic control reversal of fore and aft position gradient and fuselage buffeting.

PITOT HEAT switch - ON (if installed) in visible moisture with

ENGINE DEICING switch - ON in visible moisture when

NOTE

TOT will increase when ENGINE DEICING is switched ON.

Maximum pressure altitude is 20,000 feet.

NOTE

Refer to appropriate operating rules for high altitude oxygen requirements.

2-10B Rev. D-40 I Use or disclosure of data contained on this page is subject to the restriction on

Page 46: Bell 206A - Flight Manual

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BHT-206A-FM-1

DESCENT AND LANDING

Flight controls - Adjust friction as desired.

Throttle - Full open.

NOTE

Decreasing the collective pitch into the low power realm may result in an RPM overspeed condition. For prolonged low power approaches the RPM can be controlled by a small amount of collective pitch increase (no significant torque increase) and/or by beeping down the N2 governor speed controller to 100% RPM. This will maintain governing within limits during low power descents, however, the GOV RPM switch should be beeped to INCR as collective is applied. (See N2 Transient Overspeed Limits in Section 1.)

Flight path - As required for type of approach being made.

LDG LTS switch - ON as required.

I Use or disclosure of data contained on this page is subject to the restriction on the title page of this document. Rev. D-40

Page 47: Bell 206A - Flight Manual

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ENGINE SHUTDOWN

Throttle - Flight idle - Check engine deceleration time.

Flight controls - Position for shutdown; apply friction.

ENGINE DEICING switch - OFF.

TOT - Stabilized at flight idle speed for two minutes.

IDLE RELease button - Depress and roll throttle firmly to full closed position.

TOT - Check decreasing.

To ensure engine cutoff, hold throttle in closed position until N1 decelerates to 0 and TOT is stabilized.

During rotor coast down, apply cyclic to minimize static stop contact.

Radio equipment - OFF.

FUEL VALVE switch - OFF.

GENerator switch - OFF.

All switches - OFF.

BATtery switch - OFF after N1 is zero and TOT stabilized.

Pilot should remain at flight controls until rotor has come to a complete stop.

Rev. D-40

Use or disclosure of data contained on this page is subject to the restriction on the title page of this document.

Page 48: Bell 206A - Flight Manual

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AFTER EXITING HELICOPTER

If any of the following conditions exist:

Thunderstorms are in the local area or forecasted.

Winds in excess of 20 knots or a gust spread of 15 knots exists or is forecasted.

Helicopter is parked within 150 feet of hovering or taxiing aircraft that are in excess of gross weight of helicopter.

Helicopter to be parked overnight.

Perform the following:

Secure main rotor blade with tiedown assembly.

Secure tail rotor with tiedown strap.

Install protective covers and plugs.

I Use or disclosure of data contained on this page is subject to the restriction on the title page of this document. I Rev. D-40

Page 49: Bell 206A - Flight Manual

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EMERGENCY PROCEDURES This section contains fault conditions considered to constitute an emergency condition. Caution and warning lights are located on the instrument panel and provide the pilot with a visual indication of a condition, fault, or system malfunction by means of an individual system light. Illumination is an indication that a problem has occurred which, unless treated properly, could affect flight safety Therefore, remedial action as described below should be taken with the urgency each situation warrants.

DEFINITION

The following terms indicate the degree of urgency in landing the helicopter.

Land as soon as possible - Land without delay at nearest suitable area (i.e. open field) at which a safe approach and landing is reasonably assured.

Land as soon as practical - The landing site and duration of the flight are at the discretion of the pilot. Extended flight beyond the nearest approved landing area is not recommended.

CAUTION SYSTEM

CAUTION/WARNING LIGHT

TRANS TEMP

TRANS CHIP (if installed)

FAULT AND REMEDY

Main transmission oil temperature is at or above red line. Reducing power will help alleviate the condition. Check transmission oil pressure. Land as soon as possible.

Metal particles in transmission oil. Land as soon as possible.

Rev. D-37 2-11

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CAUTION/WARNING FAULT AND REMEDY LIGHT TRANS PRS Main transmission pressure is below

minimum. Land as soon as possible.

FUEL PUMP One of two fuel boost pumps inoperative. Descend to below 5000 feet pressure altitude if flight permits. Land as soon as practical.

With one or both fuel boost pumps inoperative, the unusable fuel is ten gallons.

Check pump operation on ground only

FUEL FILTER

A/F FUEL FILTER (if installed)

FUEL LOW (if installed)

ENG OUT (audio if functional)

ENG CHIP

T/R CHIP (if installed)

ROTOR LOW RPM (audio & light) (if installed)

Fuel filter clogged, land as soon as practical.

Airframe fuel filter clogged. Land as soon as practical.

Approximately 20 gallons of fuel remaining. Plan landing.

Engine power failure. Reduce pitch immediately to autorotate. If ample altitude remains, investigate failure, attempt engine relight.

Metallic particles in engine oil. Land as soon as possible.

-Metal particles in tail rotor gearbox oil. Land as soon as possible.

Rotor RPM is below normal. Reduce collective pitch and check that throttle is full open.

2-12 Rev. D-37

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ENGINE FAILURE

Collective pitch control - Adjust as required to maintain rotor rpm, 90% to 107%.

NOTE

Rotor rpm maintained at the high end of the operating range will provide maximum rotor energy to accomplish the landing but will cause an increased rate of descent.

Cyclic control - Adjust to obtain desired autorotative airspeed for existing conditions.

NOTE

Nominal autorotative airspeed is 58 to 69 MPH (50 to 60 knots) IAS.

Maximum airspeed for steady autorotation is 115 MPH (100 knots). Autorotation above this speed results in high rates of descent and low rotor speed. A blue radial is installed on the airspeed indicator as a reminder of this condition.

If altitude permits, attempt Engine Air Start.

At low altitude, close throttle, FLARE to lose excessive speed.

Apply collective pitch as flare effect decreases to further reduce forward speed and cushion landing. it is recommended that level touchdown be made prior to passing through 70% rotor rpm. Upon ground contact, collective pitch shall be reduced smoothly while maintaining cyclic in neutral or centered position.

Excessive ground run with collective up, or any tendency to float for long distance prior to ground contact shall be avoided.

Rev. D-37 2-12A

Page 52: Bell 206A - Flight Manual

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TAIL ROTOR CONTROL FAILURE

I

A tail rotor failure can be one of two types. Each type requires its own procedure and shall be performed as follows:

COMPLETE LOSS OF THRUST

Immediately enter autorotation and maintain an airspeed of 58 MPH (50 knots) during approach.

A run-on type of autorotation landing is recommended with the throttle in flight idle position.

2-12B Rev. D-37

Page 53: Bell 206A - Flight Manual

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Note BHT-206A-FM-1

The large vertical fin may permit controlled flight at low power levels and sufficient airspeed when a suitable landing site is not available; however, the touchdown shall be accomplished with the throttle in flight idle position.

FIXED PITCH FAILURE (Pitch change slider, control failure etc.)

Depending on the pitch position of the tail rotor, at the time of failure, engine power and airspeed shall be varied as follows:

Power - Adjust as required to minimize excessive yawing.

Airspeed - Adjust to determine best velocity to minimize excessive yawing.

FUEL CONTROL and/or GOVERNOR FAILURE

Engine fuel control and/or governor failure will be apparent by a change of power or RPM. There is no manual fuel control on the engine. Control power with throttle if engine over speeds.

Maintain RPM with collective pitch if engine under speeds.

Establish autorotative glide if power is very low or if engine must be shut down.

Prepare for power off landing.

HYDRAULIC SYSTEM FAILURE

The first indication of hydraulic boost failure will be an increase in the force required for control movement; feed-back forces will be noticed. Control motions will result in normal flight reactions in all respects, except for the increased force required for control movement. In the event of hydraulic power failure, proceed as follows: Airspeed - 70 to 80 MPH (61 to 69 knots). Hydraulic control circuit breaker - Check IN. Hydraulic control switch - ON; OFF if power is not restored. Land as soon as practical (slow slide-on landing recommended).

Rev. D-37 2-13

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ELECTRICAL POWER FAILURE Electrical power for flight is furnished by the starter which is

. utilized as a generator after the start has been accomplished. Evidence of ma in generator failure will be provided by observing loadmeter load. There is no provision for stand-by operation in the event of generator failure. Necessary power can be furnished by the battery for short periods of time. In case of generator failure:

Cycle generator switch - If power is not restored - OFF.

All electrical equipment - OFF (to conserve battery).

Required electrical equipment - ON, only as needed

I

Reduce altitude to below 5000 feet pressure altitude if flight permits prior to battery depletion and loss of fuel boost pump pressure.

Land as soon as practical.

FUEL SYSTEM FAILURE Fuel system failures are divided into two types consisting of

helicopter fuel system failure and engine fuel system failure.

ENGINE FUEL SYSTEM FAILURE The engine high pressure fuel pump is either a dual element type

pump or a single element pump. A failure of either element of the dual element pump will not result in an engine failure as either element is capable of supplying engine fuel require- ments. A failure of the single element pump will require execution of the Engine Failure procedure.

HELICOPTER FUEL SYSTEM FAILURE Helicopter fuel system failure will be caused by a malfunction

of one or both of the fuel boost pumps and will be evident by the illumination of the FUEL PUMP caution light. ,The engine will operate without boost pump pressure under low altitide conditions and one pump will supply sufficient fuel for normal engine operation under all conditions of power and altitude.

2-14 Rev. D-37

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Operation with both fuel boost pumps inoperative is not approved. Due to possible fuel sloshing in unusual attitude or out of trim conditions and one or both fuel boost pumps inoperative, the unusable fuel is ten gallons.

ENGINE FIRE DURING START

An engine fire during start will be caused by an overloading of fuel in the combustion chamber and a delayed ignition of the fuel, resulting in flame emanating from the tailpipe. To extinguish fire, proceed as follows:

Throttle - FULL CLOSED.

Starter - Continue to motor the engine.

Main fuel switch - OFF.

ENGINE FIRE DURING FLIGHT

Throttle - Close.

Immediately enter autorotation.

Fuel valve switch - OFF

Battery switch - OFF.

Generator switch - OFF.

Execute autorotational descent and landing.

NOTE

Do not restart engine until corrective maintenance has been performed.

Rev. D-37 2-15

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ENGINE AIR START

When cause of the engine failure is believed to be mechanical, do not attempt a restart.

Collective pitch control - Adjust as required to maintain rotor rpm, 90 to 107%.

Cyclic control - Adjust to desired autorotative airspeed for existing conditions (nominal 58 to 69 MPH) (50 to 60 knots).

Do not attempt air start above 12,000 feet. (TOT rises too fast to control.)

Generator - OFF. Perform normal engine startprocedure.

2-16 Rev. D-37

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BHT-206A-FM-1 I

Section 3

The Bell 206A performance data is contained in this section. The data listed on the graphs is derived from actual flight test and is intended to provide conservative information to be used in conducting flight operations.

POWER CHECK PROCEDURE

The Power Check Chart will indicate the percent torque that should be available from a minimum Allison Specification Engine.

The take-off power limits (5 minutes) of the 250-C 18 engine are:

Maximum torque - 100%.

On cold days the torque pressure limit may be reached before the TOT limit is reached. On standard or hot days or at high altitudes, the TOT will be the limiting factor. To perform a power check make sure the anti-ice and generator switches are OFF. Raise collective, increasing

to Power Check Chart.

Note

When the chart percent torque reading is exceeded, during the Power Check, it indicates a better than minimum specification engine.

Rev. D-37 3-l

Page 58: Bell 206A - Flight Manual

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HEIGHT-VELOCITY DIAGRAM

Section 3

BHT-206A-FM- 1 I

The Height-Velocity Diagram defines the conditions from which a safe landing can be made on a smooth, level, firm surface following an engine failure. The Height-Velocity Diagram is valid only when the helicopter gross weight does not exceed the limits of the Altitude Versus Gross Weight for Height-Velocity Diagram.

DENSITY ALTITUDE

A Density Altitude Chart is provided to aid in calculation of performance and limitations. Density altitude is an expression of the density of the air in terms of height above sea level; hence, the less dense the air, the higher the density altitude. For standard conditions of temperature and pressure, density altitude is the same as pressure altitude. As temperature increases above standard for any altitude, the density altitude will also increase to values higher than pressure altitude. The Density Altitude Chart expresses density altitude as a function of pressure altitude and temperature.

The Density Altitude Chart also includes the inverse of the square

the relation:

EXAMPLE:

If the ambient temperature is -15°C and the pressure altitude is

for 100 KCAS.

Solution:

Move vertically upward to the 6000 foot pressure altitude line.

Rev. D-37 3-3

Page 60: Bell 206A - Flight Manual

I Section 3

BHT-206A-FM-1

206A FLIGHT MANUAL FAA APPROVED

From this point, move horizontally to the left and read a density altitude of 4000 feet and move horizontally to the right and read

OPERATION vs ALLOWABLE WIND

Satisfactory stability and control in rearward and sideward flight has been demonstrated for speeds up to and including 20 MPH (17 knots) at all loading conditions; however, this is not to be considered a limiting value as maximum operating wind velocities have not been established.

3-4 Rev. D-37

Page 61: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 3

BHT-206A-FM-1 I

Rev. D-37 3-5

Page 62: Bell 206A - Flight Manual

I ! Section 3 206A FLIGHT MANUAL FAA APPROVED

BHT-206A-FM-1

ALTITUDE VS GROSS WEIGHT LIMITS FOR HEIGHT VELOCITY DIAGRAM

3-6 Rev. D-37

Page 63: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 3

BHT-206A-FM-1 I

AIRSPEED INSTALLATION CORRECTION TABLE

INDICATED CALIBRATED A/S - MPH A/S - MPH

40 40.5

45 45

50 50

60 59.5

70 69

80 79

90 88.5

100 98.5

110 108

120 118

130 128

140 138

148 150

Indicated Airspeed (IAS) corrected for position and instrument error equals Calibrated Airspeed (CAS). Determine Calibrated Airspeed (CAS) from the above table.

Rev. D-37 3-7

Page 64: Bell 206A - Flight Manual

I Section 3 206A FLIGHT MANUAL FAA APPROVED

BHT-206A-FM-1

DENSITY ALTITUDE CHART

6

36 1

1.76 DENSITY ALT IS 4.000 F 34

32 - 1

3-B Rev. D-37

Page 65: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL

IGE AND OGE HOVER CEILINGS

Section 3

BHT-206A-FM-1 I

The IGE and OGE Hover Ceiling Charts present hover performance (allowable gross weight) for conditions of pressure altitude and OAT. Each chart is divided into two areas.

AREA A (white area), as shown on the hover ceiling charts, presents hover performance for which satisfactory stability and control has been demonstrated in relative winds of 17 knots (20 MPH) sideward and rearward at all loading conditions.

Note

Engine TOT will rise noticeably when hovering downwind. Avoid hovering downwind when operating near TOT limits.

AREA B (yellow area), as shown on hover ceiling charts, presents additional hover performance which can be realized in CALM WINDS or winds outside the CRITICAL RELATIVE WIND AZIMUTH AREA.

Note

Tail rotor control margin and/or control of engine temperature (TOT) may preclude operation in AREA B of the Hover Ceiling Charts when the relative wind is in the Critical Wind Azimuth Area.

Caution should be exercised when operating at low airspeeds above altitudes published in performance charts. Tail rotor effectiveness may be marginal at high power settings under these conditions.

Rev. D-37 3-9

Page 66: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED

BHT-206A-FM-1

The following example is for use with the Hover Ceiling In-Ground-Effect (takeoff power 5° to -25°C) Chart with anti-ice OFF and is typical for use of all other Hover Ceiling charts.

EXAMPLE:

What gross weight hover capability could be expected at a site having the following conditions:

Pressure Altitude = 12,000 feet.

Outside Air Temperature = -20°C.

From the appropriate IGE chart obtain:

I

A maximum of 2875 pounds (1305 kilograms) for all allowable wind conditions, and a maximum of about 2925 pounds (1328 kilograms) when wind conditions are calm or outside the critical wind azimuth area.

3-10 Rev. D-37

Page 67: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL

270

Section 3

BHT-206A-FM-1 I

0

-090

180

CRITICAL RELATIVE WIND AZIMUTH AREA

L206900-69

Rev. D-37 3-11

Page 68: Bell 206A - Flight Manual

Section 3

BHT-206A.FM-l

206A FLIGHT MANUAL FAA APPROVED

3-12 Rev. D-37

Page 69: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL

HOVER CEILING IN GROUND EFFECT TAKEOFF POWER 5° TO 37.8°c

GENERATOR 22.3 AMP8 ANTI-ICE OFF SKID HEIGHT 2.0 FT (0.8 METERS) ENGINE RPM 100%

0 10 20 30 40 20. 24 28 32 LB x 1OO OAT-°c I

9 10 11 12 13 14 Kg x 100 GROSS WEIGHT

206706.157

Rev. D-37 3-13

Page 70: Bell 206A - Flight Manual

206A FLIGHT MANUAL FAA APPROVED

iT-206A-FM-1

AiEA A

’ - :5

- 5

-T

3-14 Rev. D-37

Page 71: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 3

BHT-206A-FM-1

I

I

HOVER CEILING OUT OF GROUND EFFECT TAKEOFF POWER

5° TO 37.8°C I

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 40 FT. (12.2 METERS) ENGINE RPM 100%

OAT-°c 9 10 11 12 13 14 Kg

GROSS WEIGHT

LB x 100

x 100

206706.163

Rev. D-37

Page 72: Bell 206A - Flight Manual

206A FLIGHT MANUAL FAA APPROVED

HOVER CEILING IN GROUND EFFECT

GENERATOR 22.3 AMPS ANTI-ICE OFF ENGINE RPM 100%

I Section 3

BHT-206A-FM-1

206706-160

3-16 Rev. D-37

Page 73: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 3

BHT-206A-FM-1

HOVER CEILING IN GROUND EFFECT

GENERATOR 22.3 AMPS ANTI-ICE OFF ENGINE RPM 100%

Rev. D-37

Page 74: Bell 206A - Flight Manual

206A FLIGHT MANUAL FAA APPROVED

HT-206A-FM-1

HOVER CEILING OUT OF GROUND EFFECT

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT40 FT. (12.2 METERS) ENGINE RPM 100%

100

GROSS WEIGHT 206706-161

3-18 Rev. D-37

Page 75: Bell 206A - Flight Manual
Page 76: Bell 206A - Flight Manual

I Section 3 206A FLIGHT MANUAL FAA APPROVED

BHT-206A-FM-1

RATE OF CLIMB

The following example is for use with the Rate of Climb - Maximum, Takeoff Power, Anti-Ice Off, Gross Weight 2000 pounds chart and is typical for Rate of Climb Charts.

EXAMPLE:

Assume a pressure altitude of 8500 feet and OAT of -5°C. Determine the initial maximum rate of climb.

Enter vertical scale at 8500 feet, proceed horizontally to intersection of -5°C OAT line, then proceed down to horizontal scale and read 2100 feet per minute which is the initial maximum rate of climb.

RATE OF CLIMB - DOOR(S) OFF

I Reduce rate of climb, as determined herein or in appropriate optional equipment supplement, 350 feet per minute when operating with one, all or any combination of cabin doors OFF

3-20 Rev. D-37

Page 77: Bell 206A - Flight Manual

BHT-POBA-FM-1

FAA APPROVED 206A FLIGHT MANUAL

RATE OF CLIMB-MAXIMUM TAKE-OFF POWER

ANTI-ICE OFF

GROSS WEIGHT 2000 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100%

3-21

Page 78: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED

BHT-206A-FM-1

RATE OF CLIMB-MAXIMUM TAKE-OFF POWER

ANTI-ICE OFF

GROSS WEIGHT 2300 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100%

3-22 Rev. D-37

Page 79: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 3

I

RATE OF CLIMB-MAXIMUM TAKE-OFF POWER

ANTI-ICE OFF

GROSS WEIGHT 2600 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100%

Rev. D-37 3-23

Page 80: Bell 206A - Flight Manual

I Section 3 206A FLIGHT MANUAL FAA APPROVED

BHT-206A-FM-1

RATE OF CLIMB-MAXIMUM TAKE-OFF POWER

ANTI-ICE OFF

GROSS WEIGHT 3000 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100%

3-24 Rev. D-37

Page 81: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 3

BHT-206A-FM-1 I

RATE OF CLIMB-MAXIMUM MAXIMUM CONTINUOUS POWER

ANTI-ICE OFF

GROSS WEIGHT 2000 LB Vcal 55 MPH - 4’7 KNOTS ENGINE RPM 100%

Rev. D-37 3-25

Page 82: Bell 206A - Flight Manual

I Section 3

BHT-206A-FM-1

206A FLIGHT MANUAL FAA APPROVED

RATE OF CLIMB-MAXIMUM MAXIMUM CONTINUOUS POWER

ANTI-ICE OFF

GROSS WEIGHT 2300 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100%

3-26 Rev. D-37

Page 83: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 3

BHT-206A-FM-1 I

RATE OF CLIMB-MAXIMUM MAXIMUM CONTINUOUS POWER

ANTI-ICE OFF

GROSS WEIGHT 2600 LB Vcal 55 MPH - 4’7 KNOTS ENGINE RPM 100%

Rev. D-37 3-27

Page 84: Bell 206A - Flight Manual

ection 3 206A FLIGHT MANUAL FAA APPROVED

HT-206A-FM-1

RATE OF CLIMB-MAXIMUM MAXIMUM CONTINUOUS POWER

ANTI-ICE OFF

GROSS WEIGHT 3000 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100%

3-28 Rev. D-37

Page 85: Bell 206A - Flight Manual

Section 3

BHT-206A-FM-1 I

FAA APPROVED 206A FLIGHT MANUAL

RATE OF CLIMB-MAXIMUM TAKE-OFF POWER

ANTI-ICE ON

GROSS WEIGHT 2000 LB Vcal 55 MPH - 47 KNOT: ENGINE RPM 100%

Rev. D-37 3-29

Page 86: Bell 206A - Flight Manual

I Section 3 206A FLIGHT MANUAL FAA APPROVED

BHT-206A-FM-1

RATE OF CLIMB-MAXIMUM TAKE-OFF POWER

ANTI-ICE ON

GROSS WEIGHT 2300 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100%

3-30 Rev. D-37

Page 87: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section3

BHT-206A-FM-1 I

RATE OF CLIMB-MAXIMUM TAKE-OFF POWER

ANTI-ICE ON

GROSS WEIGHT 2600 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100%

Rev. D-37 3-31

Page 88: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED

I I E BHT-206A-FM-1

RATE OF CLIMB-MAXIMUM TAKE-OFF POWER

ANTI-ICE ON

GROSS WEIGHT 3000 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100%

3-32 Rev. D-37

Page 89: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL

BHT-206A-FM-1

RATE OF CLIMB-MAXIMUM MAXIMUM CONTINUOUS POWER

ANTI-ICE ON

GROSS WEIGHT 2000 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100%

Rev. D-37 3-33

Page 90: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED

BHT-206A-FM-1

RATE OF CLIMB-MAXIMUM MAXIMUM CONTINUOUS POWER

ANTI-ICE ON

GROSS WEIGHT 2300 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100%

3-34 Rev. D-37

Page 91: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 3

I BHT-206A-FM-1

RATE OF CLIMB-MAXIMUM MAXIMUM CONTINUOUS POWER

ANTI-ICE ON

GROSS WEIGHT 2600 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100%

Rev. D-37 3-35

Page 92: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED

BHT-206A-FM-1

RATE OF CLIMB-MAXIMUM MAXIMUM CONTINUOUS POWER

ANTI-ICE ON

GROSS WEIGHT 3000 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100%

ä i i i

3-36 Rev. D-37

Page 93: Bell 206A - Flight Manual

Manufacturer’s Data

206A FLIGHT MANUAL Section 4

BHT-206A-FM-1

WEIGHT EMPTY CENTER OF GRAVITY

The empty weight consists of the basic helicopter with required equipment, optional equipment kits, transmission and gearbox oils, hydraulic fluid, unusable fuel, undrainable engine oil, and fixed ballast. The empty weight center of gravity shall be adjusted within the limits of the Center of Gravity versus Weight Empty Chart in the Maintenance Manual.

GROSS WEIGHT CENTER OF GRAVITY

It shall be the pilots responsibility to ensure that the helicopter is properly loaded so that the entire flight is conducted within the limits of the Center of Gravity Vs. Gross Weight chart in Section I. The gross weight center of gravity may be calculated from the helicopter Actual Weight Record and the Loading Chart in this section or in appropriate Flight Manual Supplements to assure safe loading.

COCKPIT AND CABIN LOADING

A minimum crew weight of 150 pounds in the cockpit is required. Crew and passengers may be loaded in any sequence without exceeding the gross weight center of gravity limits if forward doors are on. CG shall be computed.

If forward doors are removed,

The passenger compartment contains 40 cubic feet of space and the cargo loading limit is 75 pounds per square foot, and 86 pounds per square foot when cargo service platform is installed.

Rev. D-37 4-l

Page 94: Bell 206A - Flight Manual

Section 4

I 206A FLIGHT MANUAL

BHT-206A-FM-1

FUEL LOADING

Manufacturer’s Data

The helicopter center of gravity will move forward as fuel is consumed because the CG of the fuel is slightly aft of aircraft CG. With normal crew and passenger loading, gross weight CG should remain within limits at any fuel quantity, if forward doors are on. If forward doors are removed, CG shall be computed.

BAGGAGE COMPARTMENT LOADING

The baggage compartment is accessible from the left side of the helicopter and contains approximately 16 cubic feet of space. The baggage compartment has a load limit of 250 pounds (86 pounds per square foot), which is a structural limitation only, and does not infer that CG will remain within approved limits. When weight is loaded into the baggage compartment, indiscriminate crew, passenger and fuel loading can no longer be assumed, and the pilot must compute gross weight CG to assure loading within approved limits.

Loading of the baggage compartment should be from front to rear. The load shall be secured to tiedown fittings if shifting of the load in flight could result in structural damage to the baggage compartment or in gross weight center of gravity limits being exceeded. The CG shall be computed with the load in the most adverse position.

WEIGHT AND BALANCE CHARTS AND DIAGRAMS

HELICOPTER STATION DIAGRAM. The necessary helicopter stations are shown on station diagram.

CENTER OF GRAVITY VS GROSS WEIGHT. (See Section 1.)

CENTER OF GRAVITY VS WEIGHT EMPTY. See Maintenance Manual.

4-2 Rev. D-37

Page 95: Bell 206A - Flight Manual

P b 2 e w

61.0 107.1 (1549) (2720)

341.6

I I I I 36.2 73.0 167.0

(919) (1854) 127.5 (4242) 205.7 55.1 (3239) (5225)

(1400)

FUSELAGE STATIONS IN INCHES (FUSELAGE STATIONS IN MILLIMETERS)

(8677)

206900-590

Page 96: Bell 206A - Flight Manual
Page 97: Bell 206A - Flight Manual

Manufacturer’s Data

206A FLIGHT MANUAL Section 5

FUELS

Fuels conforming to the following commercial and military specifications are approved:

ASTM D - 1655, Type A, A-1, or B

MIL - T - 5624, Grade JP - 4 or JP - 5

NATO F40 or F44

Refer to Fuel Limitations in Section 1.

The following fuel listing is provided for the convenience of the operator (table 5 - 1). It shall be the responsibility of the operator and his fuel supplier to ensure that the fuel used in the helicopter conforms to one of the approved specifications above.

Refer to Allison Operation and Maintenance Manual for alternate or emergency fuels.

FUEL SYSTEM SERVICING

Total capacity: 77.06 U.S. gallons (291.7 liters).

Usable fuel: 76 U.S. gallons (287.7 liters).

The fuel system is serviced through a fuel port located on the right side of the helicopter. A grounding jack is provided near the fueling port. An electric sump drain is located in the tank and is activated by a button located at the right aft lower side of the fuselage. The battery switch must be on (or external power applied) and the fuel valve switch must be off to activate the sump drain.

Rev. D-37 5-1

Page 98: Bell 206A - Flight Manual

Manufacturer’s Data

Section 5 206A FLIGHT MANUAL

BHT-206A-FM-1

ANTI - ICING FUEL ADDITIVE

The fuel to be used when conducting flight operations below 40°F (4.4°C) must contain an anti-icing additive meeting the specification requirements of PFA-55MB or MIL-I-27686 (NATO S-748). The fuel additive marketed under the trade name PRIST meets this requirement and is manufactured for blending with ASTM types A, A-l, and B. JP-4 and JP-5 procured through military sources normally contains this additive.

Helicopters equipped with airframe mounted fuel filter do not require the use of anti - icing additive at any ambient temperature.

The minimum concentration of the additive in a loaded fuel tank should be at least 0.035 percent by volume.

The minimum concentration of the additive in the fuel with which the aircraft is to be refueled should be at least 0.06 percent by volume.

The maximum concentration of the additive that may be used in fuel is 0.15 percent by volume.

If it is not known whether or not the fuel in the aircraft contains this additive, or if the percent concentration is not known, the fuel must be drained from the helicopter and refueled with fuel containing this additive, or a differential refractometer, Seiscor Model AC - 500, may be used to accurately measure the percent concentration of additive in the fuel. This equipment is available from Seismograph Service Corporation, Tulsa, Oklahoma.

Refueling from supply pumps with a flow rate of 25 to 60 GPM must be accomplished by using a PRIST l/2 gallon container, Model PAB - 103, with the PRIST Proportioner, Model PRB - 101, and the instructions furnished with each proportioner.

Refueling from supply pumps with a flow rate of 8 to 12 GPM can be accomplished manually by using a PRIST LO - FLO, 6.5 ounce, aerosol can and blending the additive and fuel per the instructions stated on the container.

For proper blending, the flow of the additive shall commence with the initial start of the fuel flow.

5-2 Rev. D-37

Page 99: Bell 206A - Flight Manual

Manufacturer’s Data

206A FLIGHT MANUAL Section 5

BHT-206A-FM-1 Table 5 - 1. Fuels

COMMERCIAL TYPE A AND A-l FUELS (FOR OAT ABOVE -17.8°C/0°F)

FUEL ASTM D-l 666. TYPE A ASTM D-1666, TYPE A-l VENDOR PRODUCT NAME PRODUCT NAME

American Oil and Supply

ARCO (Atlantic Richfield)

Boron Oil

British-American

British Petroleum

California-Texas

Chevron

Cities Service

Continental

Exxon International

Exxon Co. U.S.A.

Gulf Oil

Mobil Oil

Phillips Petroleum

Pure Oil

Shell Oil

Standard Oil of British

Columbia

Standard Oil of California

Standard Oil of Indiana

Standard Oil of Kentucky

Standard Oil of New Jersey

Standard Oil of Ohio

Standard Oil of Texas

Texaco

Union Oil

American Jet Fuel Type A

Arcojet A

Jet A Kerosene

B-A Jet Fuel JP-1

B. P. Jet A

Chevron Jet A-60

Turbine Type A

Conoco Jet-60

Exxon Turbo Fuel A

Gulf Jet A

Mobil Jet A

Philjet A-60

Purejet Turbine Fuel Type A

Aeroshell Turbine Fuel 640

Chevron Jet Fuel A-60

Chevron Jet Fuel A-60

American Jet Fuel Type A

Standard Turbine Fuel A-60

Standard Jet A

Jet A Kerosene

Chevron Jet Fuel A-60

Texaco Avjet A

76 Turbine Fuel

American Jet Fuel Type A-l

Arcojet A-l

Jet A-l Kerosene

B. P. A.T.K.

Caltex Jet A-l

Chevron Jet A-l

Conoco Jet-60

Esso Turbo Fuel A-l

Exxon Turbo Fuel A-l

Gulf Jet A-l

Mobil Jet A-l

Purejet Turbine Fuel Type A-l

Aeroshell Turbine Fuel 660

Chevron Jet Fuel A-l

Chevron Jet Fuel A-l

American Jet Fuel Type A-l

Standard Turbine Fuel A-l

Standard Jet A-l

Jet A-l Kerosene

Chevron Jet Fuel A-l

Texaco Avjet A-l

Rev. D-37 5-3

Page 100: Bell 206A - Flight Manual

Section 5 206A FLIGHT MANUAL Manufacturer’s Data

BHT-206A-FM-1

Table 5 - 1. Fuels (Cont)

COMMERCIAL TYPE B FUELS (FOR ANY OAT)

FUEL VENDOR ASTM D-1655, TYPE B PRODUCT NAME

American Oil and Supply

ARCO (Atlantic Richfield)

British-American

British Petroleum

California-Texas

Chevron

Continental

Exxon International

Exxon Co. U.S.A.

Gulf Oil

Mobil Oil

Phillips Petroleum

Shell Oil

Standard Oil of California

Standard Oil of Indiana

Standard Oil of Kentucky

Standard Oil of New Jersey

Standard Oil of Texas

Texaco

Union Oil

American JP-4

Arcojet B

B-A Jet Fuel JP-4

B.P. A.T.G.

Caltex Jet B

Chevron Jet B

Conoco JP-4

Esso Turbo Fuel 4

Exxon Turbo Fuel 4

Gulf Jet B

Mobil Jet B

Philjet JP-4

Aeroshell Turbine Fuel JP-4

Chevron Jet Fuel B

American JP-4

Standard Turbine Fuel B

Standard Jet B

Chevron Jet Fuel B

Texaco Avjet B

Union JP-4

5-4 Rev. D-37

Page 101: Bell 206A - Flight Manual

Manufacturer’s Data

206A FLIGHT MANUAL Section 5

BHT-206A-FM-1 Table 5-1. Fuels (Cont)

MILITARY FUELS

COUNTRY

Belgium

Canada

Denmark

France

Germany

Greece

Italy

Netherlands

Norway

Portugal

Turkey

United Kingdom

United States

NATO F-40 (JP-4 TYPE)

BA-PF-2

3-GP-22

MIL-T-5624, Grade JP-4

AIR 3407

VTL 9130-006

MIL-T-5624, Grade JP-4

AER-M-C.142

MIL-T-5624, Grade JP-4

MIL-T-5624, Grade JP-4

MIL-T-5624, Grade JP-4

MIL-T-5624, Grade JP-4

D. Eng. R.D. 2454

MIL-T-5624, Grade JP-4

NATO F-44 (JP-5 TYPE)

3-GP-24

3-GP-24

AIR 3404

VTL-9130-007 VTL-9130-010

AA-M-C.143

0. Eng. R.D. 2498

D. Eng. R.D. 2498 D. Eng. R.D. 2452

MIL-T-5624, Grade JP-5

OILS

Approved oils and vendors are listed in this section for the convenience of the operator. -

An appropriate entry shall be made in the helicopter logbook when oil has been added to the engine, transmission, or tail rotor gearbox. The entry shall show the type and brand name of oil used to prevent inadvertent mixing of oils.

Mixing of oils is permitted only within a given group. In the following list of oils, there is a group number column on the left. An oil may be mixed with any other oil in its group. For example, an oil in group 4 may be mixed with another brand in group 4. An oil in group 23 may

Rev. D-37 5-5

Page 102: Bell 206A - Flight Manual

Section 5 206A FLIGHT MANUAL Manufacturer’s Data

BHT-206A-FM-1 OILS (Cont)

be mixed with any other brand in group 23. Mixing of oils not in the same group is permitted only in an emergency, but shall not exceed 5 hours total operating time.

Do not mix oils of different specifications. If oils become mixed, the system shall be drained and flushed.

ENGINE OILS

Certain oils which conform to the following specifications are approved for use in the engine (table 5-2):

MIL-L-7808G (and subsequent suffixes) (NATO 0-148).

MIL-23699 (any suffix) (NATO 0-156).

Turbine Oil 555

Engine oils shall meet the engine manufacturer’s approval in all cases. Consult the engine manufacturer for use of oil brands not listed herein.

5-6 , Rev. D-43

Page 103: Bell 206A - Flight Manual

Manufacturer’s Data

206A FLIGHT MANUAL Section 5

OILS (Cont) BHT-206A-FM-1

Table 5-2. Engine oils

MIL-L-7808 (NATO 0-148) OILS (FOR ANY OAT)

GROUP NO. OIL VENDOR MIL-L-7808 PRODUCT NAME

1 American Oil and Supply American PO Lubricant 6899

2 Bray Oil Brayco 880H

3 Exxon Co. U.S.A. Exxon Turbo Oil 2389

3 Exxon International Esso Turbo Oil 2389

4 Mobil Oil Mobil Avrex S Turbo 256

4 Mobil Oil Mobil RM-201A

5 Mobil Oil Mobil RM-184A

6 Stauffer Chemical Stauffer Jet I

MIL-L-23699 (NATO 0- 156) (FOR OAT ABOVE -40°C/-40°F)

GROUP MIL-L-23699

NO. OIL VENDOR PRODUCT NAME

21

21

22

22

22

23

23

Mobil Oil Mobil Jet II (RM-139A)

Mobil Oil Mobil Jet Oil (RM-254A)

Royal Lubricants Royco Turbine Oil 500

Royal Lubricants Royco 899 (C-915)

Shell Oil AeroShell Turbine Oil 500

American Oil and Supply American PQ Lubricant 6700

Bray Oil Brayco 899G

Rev. D-37 5-7

Page 104: Bell 206A - Flight Manual

Section 5 206A FLIGHT MANUAL Manufacturer’s Data

BHT-206A-FM-1

OILS (Cont) Table 5-2. Engine oils (Cont)

MIL-L-23699 (NATO O-l 56) (FOR OAT ABOVE - 40°C/ - 40°F)

GROUP MIL-L-23699

NO. OIL VENDOR PRODUCT NAME

23 Hatco Chemical Hatcol3211

24 Exxon Co. U.S.A. Exxon Turbo Oil 2380 -

24 Exxon international Esso Turbo Oil 2380

25 Castrol Oils Castrol 205

25 Stauffer Chemical Stauffer Jet II (6924)

26 Caltex Petroleum Caltex RPM Jet Engine Oil 5

26 Chevron International Chevron Jet Engine Oil 5

TURBINE OIL 555 (FOR OAT ABOVE -40°C/-40°F)

GROUP TURBINE OIL 555 NO. OIL VENDOR PRODUCT NAME

27 Royal Lubricants Royco Turbine Oil 555

27 Shell International AeroShell Turbine Oil 555

ENGINE OIL SYSTEM SERVICING

Capacity: 5.5 U.S. quarts (5.2 liters).

The engine oil tank is located under the aft fairing, and access doors are provided for filling and draining the oil tank. A filler cap dip stick is provided to determine the quantity of oil in the tank.

5-8 Rev. D-37

Page 105: Bell 206A - Flight Manual

Manufacturer’s Data

206A FLIGHT MANUAL Section 5

OILS (Cont)

ENGINE OIL SYSTEM SERVICING (Cont)

NOTE

BHT-206A-FM-1

MIL-L-23699 and Turbine Oil 555 are not approved for use in ambient temperatures below -40°C (-40°F). When changing to an oil of a different specification, the system shall be drained and flushed.

Refer to the engine Maintenance Manual for servicing instructions and oil filter change procedures.

TRANSMISSION AND TAIL ROTOR GEARBOX OILS

The oils listed herein are approved for use in the transmission and tail rotor gearbox (table 5-3). These oils conform to the following specifications:

MIL-L-7808E (and subsequent suffixes) (NATO O-148).

MIL-L-23699 (any suffix) (NATO O-156).

Turbine Oil 555

Rev. D-43 5-9

Page 106: Bell 206A - Flight Manual

Section 5

BHT-206A-FM-1 OILS (Cont)

206A FLIGHT MANUAL Manufacturer’s Data

Table 5-3. Transmission and tail rotor gearbox oils

MIL-L-7808 (NATO 0-148) OILS (FOR ANY OAT)

OIL VENDOR MIL-L-7808 PRODUCT NAME

American Oil and Supply

Bray Oil

Burmah-Castrol (UK) Ltd.

Exxon Co. U.S.A.

Exxon International

Hatco Chemical Hatcol 1278

Mobil Oil RM-184A RM-201A RM-248A Avrex S Turbo 256

NYCO, S.A.

NYC0 International

Royal Lubricants

Shell International

Stauffer Chemical

American PQ Lubricant 6899 PQ Turbine Oil 8365 PQ Turbine Oil 9900

Brayco 880H

Castrol 399

Exxon Turbo Oil 2389 Exxon Turbo Oil 2391

Esso Turbo Oil 2389 Esso Turbo Oil 2391

Turbonycoil 160

NII 160

Royco 808H

AeroShell Turbine Oil 308

Stauffer Jet I

5-10 Rev. D-37

Page 107: Bell 206A - Flight Manual

Manufacturer’s Data

206A FLIGHT MANUAL Section 5

BHT-206A-FM-1 OILS (Cont)

Table 5-3. Transmission and tail rotor gearbox oils (Cont)

MIL-L-23699 (NATO 0-l56) OILS (FOR OAT ABOVE -40°C/-40°F)

OIL VENDOR MIL-L-23699 PRODUCT NAME

American Oil and Supply PQ Turbine Lubricant C-3788 PQ Turbine Lubricant 3889 PQ Turbine Lubricant 3893 PQ Turbine Lubricant 6423 PQ Turbine Lubricant 6700 PQ Turbine Lubricant 9598

Bray Oil

Burmah-Castrol

Caltex Petroleum

Castrol Oils

Chevron

Emery Industries

Exxon Co. U.S.A.

Exxon International

Hatco Chemical

Brayco 899, 899G. and 899M

Castrol 5000

Caltex RPM Jet Engine Oil 5

Castrol 205

Chevron Jet Engine Oil 5

Emgard Synthesized Turbine Lubricant (2949) Emgard Synthesized Turbine Lubricant (2952)

Exxon Turbo Oil 2380

Esso Turbo Oil 2380

Hatcol 1639 Hatcol 1680 Hatcol 3211 Hatcol 3611

Rev. D-37 5-11

Page 108: Bell 206A - Flight Manual

Section 5. 206A FLIGHT MANUAL Manufacturer’s Data

BHT-206A-FM-1

OILS (Cont) Table 5-3. Transmission and tail rotor gearbox oils (Cont)

MB-L-23699 (NATO 0- 156) OILS (FOR OAT ABOVE - 40°C/ - 40°F)

OIL VENDOR MIL-L-23699 PRODUCT NAME

Mobil Oil

NYCO, S.A. Turbonycoil 599 Nyco 599A Nyco 599B

PVO International STO-5700

Royal Lubricants Royco Turbine Oil 500 Royco 899 (C-91 5) Royco 899B (D-759-3) Royco 899C (D-758) Royco 899 HC Royco 899E-1 Royco 899E-2

Shell Oil

Standard Oil of California

Stauffer Chemical

Mobil Jet Oil II Mobil RM-139A Mobil RM-147A Mobil RM-246A Mobil RM-247A Mobil RM-249A Mobil RM-254A Mobil RM-270A

AeroShell Turbine Oil 500

Chevron Jet Engine Oil 5

Stauffer Jet II (6924) Stauffer STL (E-7306)

5-12 Rev. D-37

Page 109: Bell 206A - Flight Manual

Manufacturer’s Data

206A FLIGHT MANUAL Section 5

OILS (Cont) BHT-206A-FM-1

Table 5-3. Transmission and tail rotor gearbox oils (Cont)

TURBINE OIL 555 (FOR OAT ABOVE -40°C/-40°F)

OIL VENDOR

Royal Lubricants

TURBINE OIL 555 PRODUCT NAME

Royco Turbine Oil 555

Shell International AeroShell Turbine Oil 555

TRANSMISSION AND TAIL ROTOR GEARBOX SERVICING

Transmission oil capacity: 5.0 U.S. quarts (4.7 liters).

Tail rotor gearbox oil capacity: 0.375 U.S. pint (0.2 liter).

NOTE

MIL-L-23699 and Turbine Oil 555 are not approved for use in ambient temperatures below -40% (-40°F). When changing to an oil of a different specification, the system shall be drained and flushed.

Refer to Maintenance Manual for detailed procedures for draining oil and changing filters.

OIL CHANGE - DIFFERENT SPECIFICATION

When changing to an oil of a different specification accomplish the following steps:

1. Drain transmission, freewheeling unit, and tail rotor gearbox.

2. Replace transmission oil filter.

3. Service transmission with proper amount of approved oil.

Rev. D-37 5-13

Page 110: Bell 206A - Flight Manual

Section 5 206A FLIGHT MANUAL Manufacturer’s Data

BHT-206A-FM-1

OILS (Cont)

OILCHANGE - DIFFERENT SPECIFICATION (Cont)

4. Service tail rotor gearbox with proper amount of approved oil.

5. Operate aircraft for not less than 30 minutes nor longer than 5 hours.

6. Drain transmission, freewheeling unit, and tail rotor gearbox.

7. Service transmission with the proper amount of approved oil.

8. Service tail rotor gearbox with proper amount of approved oil.

9. During first 100 hours of operation with new oil, check oil sight glasses closely for indications of foggy or hazy appearance. If these indications occur, repeat steps 6 through 9 until eliminated.

OIL CHANGE - SAME SPECIFICATION

When oil is being replaced by oil of a different brand but the same specification, accomplish the following steps:

1. Drain transmission, freewheeling unit, and tail rotor gearbox.

2. Replace transmission oil filter.

Service transmission with proper amount of approved oil. 3.

4. Service tail rotor gearbox with proper amount of approved oil.

HYDRAULIC FLUIDS

The hydraulic fluids listed herein conform to MIL-H-5606 (NATO H-515) and are approved for use in the flight control hydraulic system and the rotor brake (table 5-4).

5-14 Rev.’ D-37

Page 111: Bell 206A - Flight Manual

Manufacturer’s 206A FLIGHT MANUAL Section, 5 Data

BHT-206A-FM-1 HYDRAULIC FLUIDS (Cont)

HYDRAULIC SYSTEM SERVICING

Reservoir capacity: 1.0 U.S. pint (0.5 liter).

The hydraulic reservoir is located on top of the fuselage forward of the transmission and under the forward fairing. A sight glass is provided to determine quantity of hydraulic fluid in reservoir.

Service the hydraulic system as follows:

1. Open and support top of forward fairing.

2. Remove cap and fill reservoir until sight glass is full of hydraulic fluid.

3. Secure cap and fairing.

Table 5-4. Hydrulic fluids

MIL-H-5606 (NATO H-515) HYDRAULIC FLUIDS

FLUID VENDOR MIL-H-5606 PRODUCT NAME

Bray Oil

American Oil and Supply PQ 2863 PQ 2890 PQ 2903 PQ 2905 PQ 2950 PQ 3808 PQ 4140 PQ 4328

Brayco 756E. 756ES. 756F Brayco 757B Brayco Micronic 756ES

Rev. D-37 5-15

Page 112: Bell 206A - Flight Manual

Manufacturer’s Data

Section 5 206A FLIGHT MANUAL

BHT-206A-FM-1

HYDRAULIC FLUIDS (Cont)

Table 5-4. Hydraulic fluids (Cont) -

MIL-H-5606 (NATO H-515) HYDRAULIC FLUIDS (Cont)

FLUID VENDOR MIL-H-5606 PRODUCT NAME ,

Castrol Oils Castrol Hyspin A

Chevron U.S.A. Chevron Aviation Hydraulic Fluid D (PED 5225)

Mobil Oil Mobil Aero HFD

MZF Associates 25606

Penreco Petrofluid 4146 Petrofluid 4606 Petrofluid 4607

Rohm & Haas PA 4394

Royal Lubricants Royco 756C (C730-4) Royal 756D, 756E DS-437

Shell International Aeroshell Fluid 41

Stauffer Chemical Stauffer Aero Hydroil500

Texaco Aircraft Hydraulic Oil 15 TL-1071 IA

5-16 Rev. D-37

Page 113: Bell 206A - Flight Manual

Manufacturer’s Data

206A FLIGHT MANUAL Section 6

I BHT-206A-FM-1

MANUFACTURER’S

INTRODUCTION

The charts and tables contained on the following pages are intended to provide useful information, in this handbook, that normally is located in various and numerous other sources. The prime intent of fur- nishing this data is to assist in flight planning, op- erations and, for purposes other than flight, trans- posing available information to the typedesired.

Rev. D-37 6-1

Page 114: Bell 206A - Flight Manual

I Section 6

BHT-206A-FM-1

206A FLIGHT MANUAL Manufacturer’s Data

STANDARD ATMOSPHERE TABLE

15°c (59°F) 29.921 IN Hg (2115.215 LB/SO FT) 0.0023759 SLUGS/CU FT

PEED OF SOUND 1116.99 FT/SEC (661.7 KNOTS1

TEMPERATURE FEET RATIO

-C

0 1 0000 1 0000 15.000 59.000 1000 09711 10146 13.019 55 434 2000 0 9428 1 0299 11038 51 866 3000 0 9151 1.0454 9 056 49 302 4000 0.8881 1.0611 7 076 44 735 5000 0.8617 1 0773 5 094 41 169

CONVERSION FACTORS: 1 IN. Hg = 70.727 LB/SQ FT 1 IN Hg = 0.49116 LB/SQ IN. 1 KNOT = 1.151 M.P.H. , KNOT = 1 669 FT/SEC

PRESSURE PRESSURE

661.7 29.921 1 .oooo 659 5 28.956 0 9644 657.2 27.621 0 9296 654 9 26.917 0.8962 652 6 26.842 0.8637 660 3 24 996 0.8320

6000 0 8359 1 0938 3 113 37 603 648 7 23.978 0.8014 7000 0 8106 11107 1 132 34 037 645 6 23 088 0.7716 8000 0 7860 1 1279 -0.850 30.471 643.3 22 225 0.7428 9000 0.7620 1.1456 -2 831 26.905 640.9 21.388 0.7148

10.000 0 7385 1 1637 -4812 23 338 638 6 20.577 0.6877

11.000 0 7156 1 1822 -6.793 19.772 636.2 19791 0.6614 12.000 0 6932 1.2011 -8 774 16 206 633 9 19.029 0.6360 13.000 06713 1 2205 -10.756 12 640 631 5 18 292 0.6113 14.000 0 6500 1 2403 -12.737 9 074 629 0 17.577 0.5875 15.000 0 6292 1 2606 -14 718 5.508 626.6 16.886 0.5643

16.000 0.6090 1.2815 -16 699 1 941 624 2 16 216 0.5420 17.000 0 5892 1 3028 -18 580 -1 625 621 8 15.569 0 5203 18.000 0 5699 1 3246 -20.662 -5 191 619.4 14.942 0.4994 19.000 05611 1 3470 -22 643 -8 757 6170 14.336 0.4791 20.000 0 5328 1 3700 -24 624 -12 323 6146 13.750 0.4695

21.000 0 5150 1 3935 -26 606 -15.899 6121 13.184 0.4406 22.000 0 4976 , 4176 -28 587 -19456 609.6 12 636 0.4223 23.000 0 4806 1 4424 -30 566 -23 022 607.1 12 107 0.4046 24.000 0 4642 1 4678 -22 549 -26.588 604.6 11.597 0 3874 25.000 0 4481 1 4938 -34.530 -30 154 602 1 11103 03711

6-2 Rev. D-37

.

Page 115: Bell 206A - Flight Manual

Manufacturer’s Data

206A FLIGHT MANUAL Section 6

BHT-206A-FM-1

TEMPERATURE - o C

,

- _

:-

P -

I -

-_

_-

I-

;-

I-

:-

-_

i-

i

Rev. D-37 6-3

Page 116: Bell 206A - Flight Manual

I Section 6 206A FLIGHT MANUAL Manufacturer’s Data

BHT-POGA-FM-1

CENTIGRADE-FAHRENHEIT CONVERSION TABLE

C. F. C. F.

-62.2 -56.7 -51.1 -45.6

-34.4

-80 -112.0 -70 - 94.0 -60 - 76.0 -50 - 58.0 -40 - 40.0 -30 - 22.0

-31.7 -25 - 13.0 -28.9 -20 - 4.00 -26.1 -15 + 5.0 -23.3 -10 14.0 -20.6 -5 23.0

-17.8 0 32.0 -15.0 5 41.0 -12.2 10 50.0 - 9.4 15 59.0 - 6.7 20 68.0

- 3.9 25 77.0 - 1.1 30 86.0

1.1 35 95.0 4.4 40 104.0 7.2 45 113.0

10.0 50 122.0 12.8 55 131.0 15.6 60 140.0 18.3 65 149.0 21.1 70 158.0

23.9 75 167.0 26.7 80 176.0 29.4 85 185.0 32.2 90 194.0 35.0 95 203.0 37.8 100 212.0

C. F. C.

40.6 105 43.3 110 46.1 115 48.9 120 51.7 125

54.4 130 57.2 135 60.0 140 62.8 145 65.6 150

221.0 i 230.0 239.0 248.0 257.0

266.0 275.0 284.0 293.0 302.0

68.3 155 311.0 71.1 160 . 320.0 73.9 165 329.0 76.7 170 338.0 79.4 175 347.0

82.2 180 356.0 85.0 185 365.0 87.8 190 374.0 90.6 195 383.0 93.3 200 392.0

96.1 205 401.0 98.9 210

10l.7 410.0

215 104.4 220

419.0 428.0

107.2 225 437.0 110.0 230 446.0 112.8 235 455.0 115.6 240 464.0 118.3 245 473.0 121.1 250 482.0 126.7 260 500.0

132.2 270 518.0

6-4 Rev.D-37

Page 117: Bell 206A - Flight Manual

Manufacturer’s Data

206A FLIGHT MANUAL Section 6

BHT-206A-FM-1 I CONVERSION TABLE (Continued)

C. F. C. F. C. F. C. F.

137.8 143.3 148.9 154.4 160.0 165.6 171.1 176.7 182.2 187.8 193.3 198.9 204.4 210.0 215.6 221.1 226.7 232.2 237.8 243.3 248.9 254.4 260.0 265.6 271.1 276.7 282.2 287.8 293.3 298.9 204.4 310.0 315.6 326.7 337.8 348.9 360.0 371.1 382.2 393.3 404.4 415.6

280 290 300 310 320 330 340 350 360 370 380 390 400 410 420 430 440 450 460 470 480 490 500 510 520 530 540 550 560 570 580 590 600 620 640 660 680 700 720 740 760 780

536.0 426.7 800 1472.0 554.0 437.8 820 1508.0 572.0 454.4 850 1562.0 590.0 482.2 900 1652.0 608.0 510.0 950 1742.0 626.0 537.7 1000 1832.0 644.0 565.5 1050 1922.0 662.0 593.3 1100 2012.0 680.0 621.1 1150 2102.0 698.0 648.8 1200 2192.0 716.0 676.6 1250 2282.0 734.0 704.4 1300 2372.0 752.0 732.2 1350 2462.0 770.0 760.0 1400 2552.0 788.0 787.7 1450 2642.0 806.0 815.5 1500 2732.0 824.0 843.3 1550 2822.0 842.0 871.1 1600 2912.0 860.0 898.8 1650 3002.0 878.0 926.6 1700 3092.0 896.0 954.4 1750 3182.0 914.0 982.2 1800 3272.0 932.0 1010.0 1850 3362.0 950.0 1037.7 1900 3452.0 968.0 1065.5 1950 3542.0 986.0 1093.3 2000 3632.0

1004.0 1121.1 2050 3722.0 1022.0 1148.8 2100 3812.0 1040.0 1176.6 2150 3902.0 1058.0 1204.4 2200 3992.0 1076.0 1232.2 2250 4082.0 1094.0 1260.0 2300 4172.0 1112.0 1287.7 2350 4262.0 ' 1148.0 1315.5 2400 4352.0 1184.0 1343.3 2450 4442.0 1220.0 1371.1 2500 4532.0 1256.0 1398.8 2550 4622.0 1292.0 1426.6 2600 4712.0 1328.0 1454.4 2650 4802.0 1364.0 1482.2 2700 4892.0 1400.0 1510.0 2750 4982.0 1436.0 1537.7 2800 5072.0

Rev. D-37 6-5

Page 118: Bell 206A - Flight Manual

Section 6

BHT-206A-FM-1

206A FLIGHT MANUAL Manufacturer’s Data

C.

1565.5 1593.3 1621.1 1648.8 1676.6 1704.4 1732.2 1760.0 1787.7 1815.5 1843.3 1871.1

CONVERSION TABLE (Continued) F. C. F. C. F. C. F.

2850 5162.0 1898.8 3450 6242.0 2900 5252.0 1926.6 3500 6332.0 2950 5342.0 1954.4 3550 6422.0 3000 5432.0 1982.2 3600 6512.0 3050 5522.0 2010.0 3650 6602.0 3100 5612.0 2037.7 3700 6692.0 3150 5702.0 2065.5 3750 6782.0 3200 5792.0 2093.3 3800 6872.0 3250 5882.0 2121.1 3850 6962.0 3300 5972.0 2148.8 3900 7052.0 3350 6062.0 2176.6 3950 7142.0 3400 6152.0 2204.4 4000 7232.0

6-6 Rev. D-37

Page 119: Bell 206A - Flight Manual

Manufacturer’s Data

206A FLIGHT MANUAL Section 6

I

I VELOCITY CONVERSION TABLE

KNOTS MPH

- I km/HR /lETERS/SEC

5 5.8 9.3 2.6 10 11.5 18.5 5.1 15 17.3 27.8 7.7 20 23.0 37.0 10.3 25 28.8 46.3 12.9 30 34.5 55.6 15.4 35 40.3 64.8 18.0 40 46.0 74.1 20.6 45 51.8 83.3 23.1 50 57.5 92.6 25.7 55 63.3 101.9 28.3 60 69.0 111.1 30.9 65 74.8 120.4 33.4 70 80.6 129.6 36.0 75 86.3 138.9 38.6 80 92.1 148.1 41.2 85 97.8 157.4 43.7 90 103.6 166.7 46.3 95 109.3 175.9 48.9

100 115.1 185.2 51.4 105 120.8 194.4 54.0 110 126.6 203.7 56.6 115 132.3 213.0 59.2 120 138.1 222.2 61.7 125 143.8 231.5 64.3 130 149.6 240.7 66.9 135 155.4 250.0 69.4 140 161.1 259.3 72.0 145 166.9 268.5 74.6 150 172.6 277.8 77.2

222900-2A

Rev. D-37 6-7/6-8

Page 120: Bell 206A - Flight Manual

Manufacturer’s Data

206A FLIGHT MANUAL Section 7

BHT-206A-FM-1 I

FLIGHT MANUAL SUPPLEMENTS REQUIRED WHEN OPTIONAL EQUIPMENT KITS ARE INSTALLED

NAME OF DATE FAA CURRENT EQUIPMENT KIT NUMBER APPROVED REVISION

BHT-206A-FMS-1 Float Landing Gear - Standard Type

BHT-206A-FMS-2 Rotor Brake

BHT-206A-FMS-3 High-Skid Gear with Emergency Flotation

BHT-206A-FMS-4 High-Skid Landing Gear

BHT-206A-FMS-5 External Cargo Hook

BHT-206A-FMS-6 Fixed Cargo Hook

206-706-008 2-23-67

206-706-009 206-706-032

206-706-010

l-5-67

l-lo-68

206-706-010 12-29-67

206-706-101 l-5-67

206-706-104 5-3-67

Rev. D-38

4

3

3

3

3

3

7-1

Page 121: Bell 206A - Flight Manual

Section 7 206A FLIGHT MANUAL Manufacturer’s Data

BHT-206A-FM-1

FLIGHT MANUAL SUPPLEMENTS REQUIRED WHEN OPTIONAL EQUIPMENT KITS ARE INSTALLED (Cont)

NAME OF DATE FAA CURRENT EQUIPMENT KIT NUMBER APPROVED REVISION

BHT-206A-FMS-7 Cabin Heater

206-706-106 12-22-66 1

BHT-206A-FMS-8 206-706-122 5-15-68 1 Litter Kits 206-706-324

I

BHT-206A-FMS-9 Night Flying

Incorporated in Flight Manual

BHT-206A-FMS-10 Stability and Control Augmentation System

Section I

206-706-305 5-3-67 1

BHT-206A-FMS-11 Snow Winterization - Air Induction System

206-706-027 g-10-68

BHT-206A-FMS-12 Fire Extinguisher - Engine Compartment

206-706-310 12-19-68 1

BHT-206A-FMS-13 Fire Detector

206-706-309 6-6-69 1

7-2 Rev. D-38

Page 122: Bell 206A - Flight Manual

Manufacturer’s Data

206A FLIGHT MANUAL Section 7

BHT-206A-FM-1

FLIGHT MANUAL SUPPLEMENTS REQUlRED WHEN OPTIONAL EQUIPMENT KITS ARE INSTALLED (Cont)

NAME OF DATE CURRENT EQUIPMENT KIT NUMBER APPROVED REVISION

BHT-206A-FMS-14 External Hoist

BHT-206A-FMS-15 High Skid Landing Gear - Tubular Type

BHT-206A-FMS-16 Water Alcohol Power Augmentation

BHT-206A-FMS-17 Fuel Filter

BHT-206A-FMS-18 Snow Particle Separator Engine Air Induction System

BHT-206A-FMS-19 Dust Particle Separator Engine Air Induction System

BHT-206A-FMS-20 Heavy Duty Battery

206-706-124 7-25-69 2 206-706-126

206-706-031 g-10-69 3

206-706-400 11-26-69 1

206-706-603 l-13-70 2

206-706-200-9 7-23-70 6 206-706-201-17

206-706-200-11 7-23-70 4 206-706-201-19

206-706-319 8-6-70 2

Rev. D-43 7-3

Page 123: Bell 206A - Flight Manual

Section 7

BHT-206A-FM-1

206A FLIGHT MANUAL Manufacturer’s Data

FLIGHT MANUAL SUPPLEMENTS REQUIRED WHEN OPTIONAL EQUIPMENT KITS ARE INSTALLED (Cont)

NAME OF DATE CURRENT ’ EQUIPMENT KIT NUMBER APPROVED REVISION

BHT-206A-FMS-21 Auxiliary Battery 13 Amp Hour

206-706-330

BHT-206A-FMS-22 Cargo Hook 1500 Pound Capacity

206-706-335

1-8-71 2

6-16-72 2

BHT-206A-FMS-23 Emergency Flotation on High Skid Gear with Preflight System Test Feature

206-706-010 7-28-72 2

BHT-206A-FMS-24 266-706-136 Deflector Kit

11-20-72 3

BHT-206A-FMS-25 Engine (Automatic) Re-Ignition

206-706-038 12-15-72

BHT-206A-FMS-26 Dual Rotor Brake System

206-706-034 4-23-74 2

BHT-206A-FMS-27 STC No. 6-21-74 Loudhailer SH1683SW

1

1

74 Rev. D-43

Page 124: Bell 206A - Flight Manual

Manufacturer’s Data

206A FLIGHT MANUAL Section 7

BHT-206A-FM-1

FLIGHT MANUAL SUPPLEMENTS REQUIRED WHEN OPTIONAL EQUIPMENT KITS ARE INSTALLED (Cont)

NAME OF DATE FAA CURRENT EQUIPMENT KIT NUMBER APPROVED REVISION

BHT-206A-FMS-28 206-706-211 6-26-84 1 Lightweight Emergency Flotation Landing Gear

BHT-206A-FMS-29 206-075-676 12-10-84 0 Fuel Pressure Gage

Rev. D-38 7-5/7-6

Page 125: Bell 206A - Flight Manual

BHT-206A-FMS-1

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-008

FLOAT LANDING GEAR STANDARD TYPE

FAA APPROVED FEBRUARY 23, 1967

This supplement shall be attached to Model 206A Flight Manual when the 206-706-008 Float Landing Gear Standard Type has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

Bell A Subsidiary of Textron Inc

POST OFFICE BOX 462 l FORT WORTH, TEXAS 76101

23 FEBRUARY 1967 REVISION 4 - 2 SEPTEMBER 1986

Page 126: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

BHT-206A-FMS-1

LOG OF PAGES

PAGES REVISION

NO. PAGES REVISION

NO.

Title ............... .4 A-B .............. .4 i/ii. ................ .3 1 .................. 4 2 .................. 3 3 . . . . . . . . . . . . . . . . . . 4-c. . . . . . . . . . . . . .

4 .3

9/10. .............. .3

Rev. 4 A

Page 127: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-1

LOG OF REVISIONS

NO. DATE

Basic.. . . . . . . . . .23 Feb 67 Reissue . . . . . . . .15 May 70 1 . . . . . . . . . . . . . . 23 Jul 70 2 . . . . . . . . . . . . . 08 Nov 63 3 . . . . . . . . . . . . . 13 Sep 85 4 . . . . . . . . . . . . . 02 Sep 86

NO. DATE

APPROVED:

MANAGER

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 4

Page 128: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Introduction

BHT-206A-FMS-1

INTRODUCTION

The Bell Float Landing Gear Kit No. 206-706-008, consists of two streamlined multi-cell, inflatable floats, float mounting tubes, mount cross tubes, adapters for relocating the navigation lights, attachment fittings and all hardware required to equip the helicopter for water operation. A triangular plate is also included in the kit and mounts on the tail skid. The plate is required for controllability purposes and also partially protects the tail rotor in the event of a tail low landing on the water. Relocation of the navigation lights to the end of the float forward cross tube will permit the helicopter to be operated under day or night VFR flight conditions.

Rev. 3 i/ii

Page 129: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

BHT-206A-FMS-1

AIRSPEED LIMITATIONS

Vne, 120 mph (104 knots) sea level to 3000 feet. Above 3000 feet altitude, decrease Vne 5.0 mph (4.4 knots) per 1000 feet.

WEIGHT LIMITATIONS

Maximum approved gross weight is 2900 pounds.

ALTITUDE LIMITATIONS

Maximum operating pressure altitude is 15,000 feet.

CENTER OF GRAVITY LIMITS Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight cg within allowable limits.

TYPE OF OPERATION

This helicopter, with standard float landing gear installed, is certified for water operations under day or night VFR nonicing conditions.

INTENTIONAL POWER-OFF LANDINGS ON LAND ARE PROHIBITED. I

Flight operations requiring use of the external hoist are PROHIBITED and the system SHALL BE DEACTIVATED.

Refer to Particle Separator Supplement when the Particle Separator is installed.

Rev. 4 1

Page 130: Bell 206A - Flight Manual

Section 2 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-1

Section 2

SERVICING DATA

FLOAT PRESSURE

BASE ALTITUDE

DIFFERENTIAL ALTITUDE

Float pressure 1.5 psi.

8000 feet, 4 psi.

FLIGHT TO LOWER ALTITUDE

Increase pressure 0.5 psi per 1000 feet BELOW base altitude, to minimum operating altitude.

FLIGHT TO HIGHER ALTITUDE

Limit climbing flight to 8000 feet differential pressure altitude. ABOVE 8000 feet differential altitude REDUCE float pressure 0.5 psi per 1000 feet.

ENGINE STARTING AND RUN-UP

Anchor or moor helicopter prior to starting the engine to prevent rotating, due to torque, before tail rotor reaches effective rpm.

2 Rev. 3

Page 131: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 2

BHT-206A-FMS-1

TAXIING

Taxi at slow speed to prevent float bows from nosing under.

NOTE

Safe operation can be accomplished in waves up to 18 inches (trough to crest) and 360 degree turns can be executed in winds up to 20 mph.

IN-FLIGHT OPERATIONS

Operation over land is not recommended.

ENGINE FAILURE

Over land emergency power-off landing will require touchdown at zero (0) ground speed.

Maximum airspeed for steady state autorotation - 100 mph (87 knots).

ENGINE FAILURE - NIGHT

Establish an autorotative glide at 60 mph, for minimum rate of descent, and turn on landing light.

At 100 feet execute a moderate cyclic flare to reduce airspeed to approximately 30 mph.

Adjust collective and cyclic pitch sufficiently to perform a low speed cushioned touchdown at a slight noseup attitude.

NOTE Night autorotative touchdown landings have been demonstrated at airspeeds to 35 mph.

Rev. 4 3

Page 132: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-1

Section 3

AIRSPEED INSTALLATION CORRECTION TABLE

FLOAT LANDING GEAR

INDICATED CALIBRATED AIRSPEED MPH AIRSPEED MPH

40 42

45 46

50 50.5

60 60

70 69

80 78

90 88

100 98

110 107.5

123 120

4 Rev. 3

Page 133: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-1

RATE OF CLIMB

Reduce basic MAXIMUM RATE OF CLIMB, ANTI-ICE ON and MAXIMUM RATE OF CLIMB, ANTI-ICE OFF performance data 400 FEET PER MINUTE, when operating with Float Landing Gear.

Rev. 3 5

Page 134: Bell 206A - Flight Manual

!sectbn3 206A FLIGHT MANUAL FAA APPRDVED SUPPLEMENT

BHT-206A-FMS-1

Page 135: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Section 3

BHT-206A-FMS-1

HOVER CEILING IN GROUND EFFECT

GENERATOR 22.3 AMPS ANTI-ICE OFF

206706-153A

Rev. 3 7

Page 136: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-1

HOVER CEILING IN GROUND EFFECT

GENERATOR 22.3 AMPS ANTI-ICE OFF FLOAT HEIGHT 3.0 FT (0.9 METERS) ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 330 LBS (150 kg) LESS

-30-20-10 0 10 20 24 28

GROSS WEIGHT 206706-154

8 Rev. 3

Page 137: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-1

HOVER CEILING IN GROUND EFFECT

GROSS WEIGHT 206706-155A

Rev. 3 g/10

Page 138: Bell 206A - Flight Manual

BHT-206A-FMS-2

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-009 206-706-032

ROTOR BRAKE

FAA APPROVED

JANUARY 5, 1967

This supplement shall be attached to Model 206A Flight Manual when 206-706-009 or 206-706-032 Rotor Brake kit has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

A Subsidiary of Textron Inc

POST OFFICE BOX 482 l FORT WORTH, TEXAS 76101

5 JANUARY 1967 REVISION 3 - 3 JUNE 1987

Page 139: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

LOG OF PAGES

REVISION PAGES NO.

Title . . . . . . . . . . . . . . . . . 3 A-B . . . . . . . . . . . . . . . 3 i/ii . . . . . . . . . . . . . . . . . . 2 1/2 . . . . . . . . . . . . . . . . . 3

PAGES REVISION

NO.

Rev. 3 A

Page 140: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-2

LOG OF REVISIONS

NO. DATE

Basic . . . . 05 Jan 67 Reissue . 15 May 70 1 . . . . . . . 20 Aug 70 2 . . . . . . . 13 Sep 85 3 . . . . . . . . 03 Jun 87

NO. DATE

APPROVED:

MANAGER

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE:, Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 3

Page 141: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Introduction

INTRODUCTION

The Bell Rotor Brake Kits, Nos. 206-706-009 and 206-706-032 each consist of a disc type brake, valve, operating handle, and the tubing and fittings required for attachment. Installation of the rotor brake permits rapid deceleration of the rotor after shutdown.

Rev. 2 i/ii

Page 142: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Sections I, 2 & 3 SUPPLEMENT

BHT-206A-FMS-2

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight CG to within allowable limits.

PLACARDS

Section 2

ENGINE SHUT-DOWN

Apply rotor brake between 50% and 40% rotor RPM.

No change from basic Flight Manual.

Rev. 3 1/2

Page 143: Bell 206A - Flight Manual

BHT-206A-FMS-3

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-010

HIGH-SKID GEAR WITH EMERGENCY FLOTATION

FAA APPROVED JANUARY 10, 1968

This supplement shall be attached to Model 206A Flight Manual when the 206-706-010 High-Skid Gear with Emergency Flotation has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

Bell A Subsidiary of Textron Inc

POST OFFICE BOX 482 l FORT WORTH. TEXAS 76101

10 JANUARY 1968 REVISION 3 - 13 SEPTEMBER 1985

Page 144: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

LOG OF PAGES

‘AGES REVISION

NO. PAGES REVISION

NO.

A-B . . . . . . . . . . . . . . . 3 i/ii. . . . . . . . . . . . . . . . . .3 1-8. . . . . . . . . . . . . . .3 9/10. . . . . . . . . . . . . . . .3

Rev. 3 A

Page 145: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-3

LOG OF REVISIONS

DATE DATE

Basic .......... Reissue ....... .15 May 70 1 ............. 12 Mar 71 2 ............. 08 Nov 83 3 ............. 13 Sep 85

APPROVED:

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 3

Page 146: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Introduction

INTRODUCTION

The Bell High-Skid Gear with Emergency Flotation, Kit No. 206-706-010, consists of a high-skid landing gear, emergency floats attached to the main skid panels, inflation system, navigation lights, and attaching hardware. Installation of this kit permits operation over land or water. Float inflation time is approximately 5 seconds.

NOTE

On Serial Numbers 4 through 153, Service Instruction No. 206-36 (Landing Gear Support Doublers) must be accomplished prior to installation of Kit.

Rev. 3 i/ii

Page 147: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

BHT-206A-FMS-3

WEIGHT LIMITATIONS Maximum approved gross weight is 2900 pounds.

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight cg within allowable limits.

TYPE OF OPERATION

Operation with the emergency floats inflated is limited to flight to a servicing facility for repacking and recharging the system.

The floats and covers must be installed for all flight operations.

Flight operations over land or water are approved.

Refer to Particle Separator Supplement when the Particle Separator is installed.

-- AIRSPEED LIMITATIONS

Floats stowed, covers installed - Same as basic helicopter.

Maximum inflated airspeed - 100 MPH (87 knots).

Maximum inflated airspeed with one or both aft doors off - 60 MPH (52 knots).

Maximum airspeed during float inflation - 70 MPH (61 knots).

Rev. 3 1

Page 148: Bell 206A - Flight Manual

Sections 1 & 2 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-3

I PLACARDS

WHEN FLOTATION EQUIP. IS INSTALLED REDUCE ALLOWABLE WEIGHT BY 60 LBS. (Located on inside of baggage compartment door.)

FLOAT INFLATION ABOVE 70 MPH PROHIBITED (Located on instrument panel)

Section 2

EXTERIOR CHECK

Floats stowed.

Float covers clean and secured.

Nitrogen bottle - Pressure - 2800 to 2900 psi.

BEFORE TAKE-OFF AND LANDING

OVER WATER OPERATION

Float power switch - ON.

Float power caution light - ON.

OVER LAND OPERATION

Float power switch - OFF.

2 Rev. 3

Page 149: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 2

BHT-206A-FMS-3

LANDING - TOUCHDOWN

[WARNING

-- RUN-ON LANDINGS on other than a HARD FIRM SURFACE should be exercised with CAUTION, due to the increased ground contact area of the skid panels.

NOTE

TAIL-LOW RUN-ON LANDINGS should be avoided to prevent nosedown pitching.

EMERGENCY PROCEDURES

ENGINE FAILURE - OVER WATER

Maximum inflation airspeed - 70 mph.

Float power caution light - Check ON.

Float inflation switch - Pull ON.

NOTE

With float power switch ON, float inflation system is automatically armed when ENGINE OUT light is illuminated and AUDIO is on.

DO NOT inflate floats more than 5000 feet above anticipated landing terrain.

Rev. 3 3

Page 150: Bell 206A - Flight Manual

Section 2 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

l BHT-206A-FMS-3

MANUAL ARMING - INFLATION SYSTEM

The manual inflation arming system will override or backup the automatic inflation arming system. This system can be used, when desired or necessary, to perform a water landing for precautionary reasons and shall be accomplished as follows:

Maximum inflation airspeed - 70 mph.

Float power caution light - Check ON.

Manual arm switch - Lift guard and move switch to ON.

Float inflation switch - Pull ON.

AFTER EMERGENCY WATER LANDING

After landing, check helicopter for possible damage.

If malfunction was cause of landing, correct malfunction.

If no damage has occurred to helicopter and malfunction has been corrected, the aircraft can be ferried to the nearest- maintenance facility to repack floats and charge system. The ferrying airspeed is restricted to 100 mph with all doors on or to 60 mph with door or doors Off.

ENGINE FAILURE - NIGHT

Establish an autorotative glide at 60 mph, for minimum rate of descent, and turn on landing light.

At 100 feet execute a moderate cyclic flare to reduce airspeed to approximately 30 mph.

Adjust collective and cyclic pitch sufficiently to perform a low speed cushioned touchdown at a slight noseup attitude.

NOTE

Night autorotative touchdown landings have been demonstrated at airspeeds to 35 mph.

4 Rev. 3

Page 151: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-3 1

HOVER CEILING

Out-of-ground effect hovering performance is the same as basic helicopter. In-ground-effect hovering performance is shown on the following graphs.

Rev. 3 5

Page 152: Bell 206A - Flight Manual

Section3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

1 BHT-206A-FMS-3

6 Rev. 3

Page 153: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

HOVER CEILING IN GROUND EFFECT

GENERATOR 22.3 AMPS ANTI-ICE OFF ENGINE RPM 100%

BASIC SHIP WITH HIGH SKID GEAR

010203040 20 24

GROSS WEIGHT 206706-137

Rev. 3 7

Page 154: Bell 206A - Flight Manual

Section 3

I BHT-206A-FMS-3

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

HOVER CEILING IN GROUND EFFECT

GENERATOR 22.3 AMPS ANTI-ICE OFF ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 330 LB (150 kg) LESS

BASIC SHIP WITH HIGH SKID GEAR

GROSS WEIGHT 206706

8 Rev. 3

Page 155: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

HOVER CEILING IN GROUND EFFECT

GENERATOR 22.3 AMPS ANTI-ICE OFF ENGINE RPM 100%

BASIC SHIP WITH HIGH SKID GEAR

GROSS WEIGHT 206706-139

Rev. 3 9/10

Page 156: Bell 206A - Flight Manual

BHT-206A-FMS-4

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-010

HIGH-SKID LANDING GEAR

FAA APPROVED December 29, 1967

This supplement shall be attached to Model 206A Flight Manual when the 206-706-010 High-Skid Landing Gear has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

Bell A Subsidiary of Textron Inc

POST OFFICE BOX 482 l FORT WORTH, TEXAS 76101

29 DECEMBER 1967 REVISION 3 - 13 SEPTEMBER 1985

Page 157: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Log of Pages

LOG OF PAGES

PAGES REVISION

NO. PAGES REVISION

NO.

Title . . . . . . . . . . . . . . . .3 A-B.. . . . . . . . . . . . . .3 i/ii. . . . . . . . . . . . . . . . . .3 1-6.. . . . . . . . . . . . . .3

Page 158: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-4

LOG OF REVISIONS

NO. DATE

Basic . . . . . . . . . .29 Dec 67 Reissue . . . . . . . .15 May 70 1 . . . . . . . . . . . . . . 23 Jul 70 2 . . . . . . . . . . . . . 08 Nov 83 3 . . . . . . . . . . . . . 13 Sep 85

NO. DATE

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 3

Page 159: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Introduction

INTRODUCTION

The Bell High-Skid Landing Gear, Kit No. 206-706-010, consists of two main skid panels, skid panel fairings, two curved tubular cross tubes, steps, and attaching hardware.

NOTE

On Serial Numbers 4 through 153, Service Instruction No. 206-36 (Landing Gear Support Doublers) must be accomplished prior to installation of high-skid gear.

Rev. 3 i/ii

Page 160: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Section 1

WEIGHT LIMITATIONS

Maximum approved gross weight is 2900 pounds.

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight cg within allowable limits.

TYPE OF OPERATlON

The hard cover skid panel fairings must be installed for all flight operations.

Refer to Particle Separator Supplement when the Particle Separator is installed.

Rev. 3 1

Page 161: Bell 206A - Flight Manual

Sections 2 & 3 206A FLIGHT MANUAL FAA APPROVED . SUPPLEMENT

I BHT-206A-FMS-4

LANDING -TOUCHDOWN

RUN-ON LANDINGS on other than a HARD FIRM SURFACE should be exercised with CAUTION, due to the increased ground contact area of the skid panels.

NOTE

TAIL-LOW RUN-ON LANDINGS should be avoided to prevent nosedown pitching.

HOVER CEILING

Out-of-ground effect hovering performance is the same as basic helicopter. In-ground-effect hovering performance is shown on the following graphs.

2 Rev. 3

Page 162: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL section 3

SUPPLEMENT

BHT-206A.FM.54 I

Page 163: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-4

4

HOVER CEILING IN GROUND EFFECT

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 3.0 FT (0.9 METERS) ENGINE RPM 100%

BASIC SHIP WITH HIGH SKID GEAR

III

GROSS WEIGHT 206706-137

Rev. 3

Page 164: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

HOVER CEILING IN GROUND EFFECT MAX. CONTINUOUS POWER 5° TO -25°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 3.0 FT (0.9 METERS) ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 330 LB (150 kg) LESS

BASIC SHIP WITH HIGH SKID GEAR

-30-20-10 0 10 20 24 28 32

GROSS WEIGHT 206706-l38

Rev. 3 5

Page 165: Bell 206A - Flight Manual

Section 3

I BHT-206A-FMS-4

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

HOVER CEILING IN GROUND EFFECT MAX. CONTINUOUS POWER 5° TO 37.8°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 3.0 FT (0.9 METERS) ENGINE RPM 100%

BASIC SHIP WITH HIGH SKID GEAR

LB x 100

GROSS WEIGHT 206706-139

6 Rev. 3

Page 166: Bell 206A - Flight Manual

BHT-206A-FMS-5

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-101

EXTERNAL CARGO HOOK

FAA APPROVED JANUARY 5, 1967

This supplement shall be attached to Model 206A Flight Manual when the 206-706-101 External Cargo Hook has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

Bell COPYRIGHT NOTICE

COPYRIGHT 1995

AND BELL HELICOPTER TEXTRON, A DIVISION OF TEXTRON CANADA LTD.

ALL RIGHTS RESERVED

A Subsidiary of Textron Inc

POST OFFICE BOX 482 l FORT WORTH. TEXAS 76101

REISSUE - 13 SEPTEMBER 1995

Page 167: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Log of Pages SUPPLEMENT

BHT-206A-FMS-5

LOG OF PAGES

REVISION PAGES NO.

Title . . . . . . . . . . . . . . . 0 A-B . . . . . . . . . . . . . . . 0 i/ii. . . . . . . . . . . . . . . . . 0 1 - 12.. . . . . . . . . . . . 0 13/14. . . . . . . . . . . . . . 0

PAGES REVISION

NO.

A

Page 168: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-5

LOG OF REVISIONS

NO. DATE

Basic . . . . . . . . . .05 Jan 67

Reissue . . . . . . . 15 May 70

1.. . . . . . . . . . . .23 Jul 70

2 . . . . . . . . . . . . . 08 Nov 83

3 . . . . . . . . . . . . . 13 Sep 85 Reissue. . . . . . . . 13 Sep 95

NO. DATE

ROTORCRAFT CERTIFICATION OFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B

Page 169: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Introduction

BHT-206A-FMS-5

INTRODUCTION

The Bell Cargo Hook Kit No. 206-706-101 consists of two A-frame mountings, a main cross beam and an integral cargo hook, designed to carry loads of 1200 pounds. The cargo is suspended from the aircraft center of gravity and the design is such that oscillatory moments of a free swinging cargo do not impart motion to the airframe. The system contains an electrical and manual emergency release. Provisions for stowing the kit when flight without cargo is anticipated, are provided. OPERATIONS with cargo on the hook SHALL BE CONDUCTED IN ACCORDANCE WITH APPROPRIATE OPERATING RULES.

NOTE

1. Two bumper assemblies, 206-070-585-1, must be installed per Bell Service Letter No. 206A-74 when external cargo hook is used with float equipped helicopters.

2. A swivel link is not supplied with the Cargo Hook Kit; however, it is recommended that a link be installed between the suspension cable and the cargo hook.

i/ii

Page 170: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 1 SUPPLEMENT

BHT-206A-FMS-5

WEIGHT LIMITATIONS

Maximum approved gross weight is 3350 pounds.

Loads that result in gross weights above 3000 pounds shall be carried on cargo hook and shall not be imposed on landing gear.

Cargo hook structural loading limit 1200 pounds.

CENTER OF GRAVITY LIMITS

3000 TO 3350 LBS EXTERNAL LOAD CENTER OF GRAVITY vs GROSS WEIGHT

3350

3200

3000

2800

I

LONGITUDINAL CENTER OF GRAVITY FUSELAGE STATION

1

Page 171: Bell 206A - Flight Manual

Section 1 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-5

AIRSPEED LIMITATIONS

Vne 91 MPH (78 knots) for gross weights above 3000 pounds.

Extreme caution should be exercised when carrying cargo loads as controllability may be affected, due to the size and shape of the cargo load.

TYPE OF OPERATION

Operation of the helicopter with no load on the external cargo hook is authorized under the standard airworthiness certificate without removing the unit from the helicopter.

External cargo operations shall be conducted in accordance with appropriate operating rules for external loads under VFR conditions.

Refer to Particle Separator Supplement when the Particle Separator is installed.

Page 172: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Section 2

BHT-206A-FMS-5

Section 2 FLIGHT PLANNING

Instruct ground personnel to discharge helicopter static electricity, before attaching cargo sling, by touching airframe with a ground wire. If a metal sling is used, hook up ring can be struck against cargo hook to discharge static electricity. If contact has been lost after initial grounding, helicopter should be electrically regrounded and, if possible, contact maintained until hook up is complete.

Instruct ground personnel to check primary load ring and secondary load ring for condition and proper size (table 2-l). Check for correct rigging.

Use of multiple rings, slings, or shackles on the load beam or the primary load ring or use of an oversize secondary load ring is like using a primary load ring smaller than nominal size. This can cause the load to hang up during release.

Failure to comply with these instructions may impair cargo hook ring interface operation, resulting in potential problems.

Check that only one primary ring is captured in the load beam and only one secondary ring with correct cross-section dimension is captured in the primary ring. Additional rings, slings, or shackles shall be attached to the secondary load ring. See figure 2-1.

3

Page 173: Bell 206A - Flight Manual

Section 2 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-5

CORRECT RIGGING

BEAM

PRIMARY RING CROSS-SECTION

t * INSIDE DIAMETER

SECONDARY RING

TO LOAD(S)

* SEE TABLE 2-1

INCORRECT RIGGING INCORRECT RIGGING

LOAD BEAM

SECONDARY

206A-FS5-2-1

Figure 2-1. External load rigging

4

Page 174: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Sections 2 & 3

BHT-206A-FMS-5

Table 2-l. Ring sizes - cargo hook P/N 14027-2

MAXIMUM CROSS PRIMARY RING PRIMARY RING SECTION OF INSIDE DIAMETER CROSS SECTION SECONDARY RING

2.38 to 2.50 in. 0.625 in. 0.438 in. (60.45 to 63.50 mm) (15.88 mm) (11.12 mm)

2.50 to 2.75 in. 0.625 in. 0.625 in. (63.50 to 69.85 mm) (15.88 mm) (15.88 mm)

OPERATION

ACTIVATE circuit by pushing CARGO HOOK circuit breaker - IN.

Engage CARGO switch on cyclic control stick, to release cargo.

EMERGENCY RELEASE

Pull mechanical manual release control HANDLE to drop cargo in the event of an electrical failure.

5

Page 175: Bell 206A - Flight Manual

Section3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FM-i-5

Page 176: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-5

HOVER CEILING IN GROUND EFFECT TAKEOFF POWER 5° TO 37.8°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT: LOW SKID GEAR 4.0 FT ENGINE RPM 100%

(1.2 METERS) HIGH SKID GEAR 3.0 FT (0.9 METERS)

0 10 20 30 40 20 24 28 32 36

GROSS WEIGHT 206-706-109A

7

Page 177: Bell 206A - Flight Manual

.section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-5

OAT-‘%

8

Page 178: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-5

HOVER CEILING OUT-OF- GROUND EFFECT TAKEOFF POWER

5° TO 37.8°C

GENERATOR 22.3 AMPS SKID HEIGHT 40 FT. (12.2 METERS)

ANTI-ICE OFF ENGINE RPM 100%

LB x 100

GROSS WEIGHT 206706-113

9

Page 179: Bell 206A - Flight Manual

Section 3

BHT-206A-FMS-5

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

HOVER CEILING IN GROUND EFFECT MAX. CONTINUOUS POWER 5° TO -25°C

GENERATOR 22.3 AMPS SKID HEIGHT: LOW SKID GEAR 4.0 FT

(1.2 METERS)

ANTI-ICE OFF ENGINE RPM 100%

HIGH SKID GEAR 3.0 FT (0.9 METERS) WITH ANTI-ICE ON GROSS WEIGHT IS 330 LBS (150 kg) LESS

Page 180: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-5

HOVER CEILING IN GROUND EFFECT MAX. CONTINUOUS POWER 5° TO 37.8°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT: LOW SKID GEAR 4.0 FT ENGINE RPM 100%

Il.2 METERS) HIGH SKID GEAR 3.0 FT (0.9 METERS)

LB x 100

GROSS WEIGHT 206-706.111A

11

Page 181: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-5

HOVER CEILING OUT-OF- GROUND EFFECT MAX. CONTINUOUS POWER

5° TO -25°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 40 FT. (12.2 METERS) ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 310 LBS (141 kg) LESS

0 10 16 20 24 28 32 36 LB x 100

GROSS WEIGHT Kg x 100 206706-114

12

Page 182: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-5

OUT-OF- HOVER CEILING

GROUND EFFECT MAX. CONTINUOUS 5° TO 37.8°C

POWER

GENERATOR 22.3 AMPS SKID HEIGHT 40 FT. (12.2 METERS)

ANTI-ICE OFF ENGINE RPM 100%

GROSS WEIGHT

Page 183: Bell 206A - Flight Manual

BHT-206A-FMS-6

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-104

FIXED CARGO HOOK FAA APPROVED

May 3, 1967

This supplement shall be attached to Model 206A Flight Manual when the 206-706-104. Fixed Cargo Hook has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

A Subsidiary of Textron Inc

POST OFFICE BOX 482. FORT WORTH. TEXAS 78101

COPYRIGHT NOTICE

1995

REISSUE - 13 SEPTEMBER 1995

Page 184: Bell 206A - Flight Manual

.

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

BHT-206A-FMS-6

LOG OF PAGES

REVISION PAGES NO.

Title . . . . . . . . . . . . . . . .0 A-B . . . . . . . . . . . . . . . 0 i/ii. . . . . . . . . . . . . . . . . .0 l-12 . . . . . . . . . . . . . . 0 13/14. . . . . . . . . . . . . . .0

PAGES REVISION

NO.

Page 185: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-6

LOG OF REVISIONS

NO. DATE

Basic. . . . . . . . . .03 May 67 Reissue . . . . . . . .15 May 70 1 . . . . . . . . . . . . . 23 Jul 70 2 . . . . . . . . . . . . . 08 Nov 83 3 . . . . . . . . . . . . . 13 Sep 85 Reissue. . . . . . . . .13 Sep 95

NO. DATE

APPR

MANAGER

ROTORCRAFT CERTIFICATION OFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B

Page 186: Bell 206A - Flight Manual

.

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Introduction

BHT-206A-FMS- 6

INTRODUCTION

The Bell Cargo Hook Kit No. 206-706-104, consists of a frame and hook assembly, electrical and manual (emergency) release system, and attaching hardware. A bungee shock cord is attached to the cargo hook which provides automatic stowing when hook is not in use. Operations with cargo on the hook shall be conducted in accordance with appropriate operating rules.

NOTE

A swivel link is not supplied with the Cargo Hook Kit; however, it is recommended that a link be installed between the suspension cable and the cargo hook.

i/ii

Page 187: Bell 206A - Flight Manual

.

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Section 1

BHT-206A-FMS-6

-

WEIGHT LIMITATIONS

Maximum approved gross weight is 3350 pounds.

Loads that result in gross weights above 3000 pounds shall be carried on cargo hook and shall not be imposed on landing gear.

Cargo hook structural loading limit 1200 pounds.

AIRSPEED LIMITATIONS -

Vne 91 MPH (78 knots) for gross weights above 3000 pounds.

Extreme caution should be exercised when carrying cargo loads as controllability may be affected, due to the size and shape of the cargo load.

Page 188: Bell 206A - Flight Manual

Section1 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-6

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight cg to within allowable limits.

3000 TO 3350 LBS EXTERNAL LOAD CENTER OF GRAVITY vs GROSS WEIGHT

3200 I

3000

2800

3350

105 106 107 108 109 110 111 112 113 114 115 116

LONGITUDINAL CENTER OF GRAVITY. FUSELAGE STATION

TYPE OF OPERATION

Operation of the helicopter with no load on the external cargo hook is authorized under the standard airworthiness certificate without removing the unit from the helicopter.

External cargo operations shall be conducted in accordance with appropriate operating rules for external loads under VFR conditions.

Refer to Particle Separator Supplement when the Particle Separator is installed.

2

Page 189: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 2

. BHT-206A-FMS-6

Section 2

FLIGHT PLANNING

Instruct ground personnel to discharge helicopter static electricity, before attaching cargo sling, by touching airframe with a ground wire. If a metal sling is used, hook up ring can be struck against cargo hook to discharge static electricity. If contact has been lost after initial grounding, helicopter should be electrically regrounded and, if possible, contact maintained until hook up is complete.

Instruct ground personnel to check primary load ring and secondary load ring for condition and proper size (table 2-l). Check for correct rigging.

Use of multiple rings, slings, or shackles on the load beam or the primary load ring or use of an oversize secondary load ring is like using a primary load ring smaller than nominal size. This can cause the load to hang up during release.

Failure to comply with these instructions may impair cargo hook ring interface operation, resulting in potential problems.

Instruct ground personnel to check that only one primary ring is captured in the load beam and only one secondary ring with correct cross-section dimension is captured in the primary ring. Additional rings, slings, or shackles shall be attached to the secondary load ring. See figure 2-l.

3

Page 190: Bell 206A - Flight Manual

Section 2 206A FLIGHT MANUAL

BHT-206A-FMS-6

FAA APPROVED SUPPLEMENT

CROSS-SECTION

LOAD

* MAXIMUM CROSS-SECTION OF - SECONDARY RING

TO LOAD(S)

* SEE TABLE 2-1

INCORRECT RIGGING INCORRECT RIGGING

TO LOAD(S)

SECONDARY

206A-FS6-2-1

Figure 2 - 1. External load rigging

4

Page 191: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Sections 2, & 3

BHT-206A-FMS-6

Table 2-1. Ring sizes - cargo hook P/N 14027-2

MAXIMUM CROSS PRIMARY RING PRIMARY RING SECTION OF INSIDE DIAMETER CROSS SECTION SECONDARY RING

2.38 to 2.5 in. 1.0 in. 0.438 in. (60.452 to 63.50 mm> (25.4 mm) (11.12 mm)

2.5 to 2.75 in. 1.0 in. 0.625 in. (63.50 to 69.85 mm) (25.4 mm) (15.88 mm)

OPERATION

ACTIVATE circuit by pushing CARGO HOOK circuit breaker IN.

Engage CARGO switch on cyclic control stick, to release cargo.

EMERGENCY RELEASE

Pull mechanical manual release control HANDLE to drop cargo in the event of an electrical failure.

Page 192: Bell 206A - Flight Manual

section 3

BHT-206A-FMS-6

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

Page 193: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-6

HOVER CEILING IN GROUND EFFECT TAKEOFF POWER 5° TO 37.8°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT: LOW SKID GEAR 4.0 FT ENGINE RPM 100%

Il.2 METERS) HIGH SKID GEAR 3.0 FT (0.9 METERS)

H EXTERNAL CARGO 0

LB x 100 OAT-°C

GROSS WEIGHT 206706-101A

7

Page 194: Bell 206A - Flight Manual

Section 3

BHT-206A-FMS- 6

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

Page 195: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-6

HOVER CEILING OUT OF GROUND EFFECT TAKEOFF POWER

5° TO 37.8°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 40 FT. (12.2 METERS) ENGINE RPM 100%

LB x 100 OAT-°C

Kg x 100 GROSS WEIGHT

206706-103

9

Page 196: Bell 206A - Flight Manual

Section 3

BHT-206A-FMS-6

206A FLIGHT MANUAL FAA APPROVED . SUPPLEMENT

HOVER CEILING IN GROUND EFFECT MAX. CONTINUOUS POWER 5° TO -25°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT: LOW SKID GEAR 4.0 FT ENGINE RPM 100%

(1.2 METERS) HIGH SKID GEAR 3.0 FT (0.9 METERS)

WITH ANTI-ICE ON GROSS WEIGHT IS 330 LBS (150 kg) LESS

EXTERNAL CARGO ONLY

LB x 100 OAT-°C

GROSS WEIGHT Kg x 100 206706-104A

10

Page 197: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Section 3

HOVER CEILING IN GROUND EFFECT MAX. CONTINUOUS POWER 5° TO 37.8°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT: LOW SKID GEAR 4.0 FT ENGINE RPM 100%

(1.2 METERS) HIGH SKID GEAR 3.0 FT (0.9 METERS)

TO 3350 LBS (1519.5 kg)

OAT-°C

GROSS WEIGHT 206706-105A

11

Page 198: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-6

HOVER CEILING OUT-OF-GROUND-EFFECT MAX. CONTINUOUS POWER 5° TO -25°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 40 FT. (12.2 METERS] ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 310 LBS (141 kg) LESS

OAT-°C

GROSS WEIGHT Kg x 100 206706-106

12 Rev. 3

Page 199: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-6

13/14

Page 200: Bell 206A - Flight Manual

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-106

CABIN HEATER

FAA APPROVED

DECEMBER 22, 1966

This supplement shall be attached to Model 206A Flight Manual when 206-706-106 Cabin Heater has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

Bell A Subsidiary of Textron Inc

POST OFFICE BOX 462 l FORT WORTH. TEXAS 76101

22 DECEMBER 1966 REVISION 1 - 13 SEPTEMBER 1985

Page 201: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

LOG OF PAGES

REVISION PAGES NO.

Title . . . . . . . . . . . . . . . .1 A-B... . . . . . . . . . . . .1 i/ii. . , . . . . . . . . . . . . . . .1 l-4.. . . . . . . . . . . . . .1

PAGES REVISION

NO.

Rev. 1 A

Page 202: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL

I BHT-206A-FMS-7

FAA APPROVED SUPPLEMENT

LOG OF REVISIONS

NO. DATE

Basic . . . . . . . . . .22 Dec 66 Reissue. . . . . . . . .06 Oct 71 1 . . . . . . . . . . . . . 13 Sep 85

NO. DATE

APPROVED:

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 1

Page 203: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

lntroduction

INTRODUCTION

The Bell Cabin Heater Kit, No. 206-706-106, consists of a combustion heater, blower, ducts, fuel system, electrical system, adjustable valves, and heater controls. The heater is designed to operate while the helicopter is on the ground or airborne.

Rev. 1 i/ii

Page 204: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight CG to within allowable limits.

Rev. 1 1

Page 205: Bell 206A - Flight Manual

Section 2 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

HEATER PRE-START CHECK

FUEL BOOST circuit breaker - IN.

FUEL VALVE circuit breaker - IN.

HTR PWR circuit breaker - IN.

HTR CONT circuit breaker - IN.

FIREWALL SHUT OFF RELEASE PULL knob - IN.

BAT switch - ON.

FUEL VALVE switch - ON.

HEATER FAIL light. (Light is press-to-test type.)

HEATER START AND OPERATION

NOTE

Heater ignition difficulty may be experienced at -20°F (-29°C) and below when using ASTM Type A or A - l (JP-5) fuel..

HEAT-VENT switch - HEAT

(Combustion air blowers should operate and HEATER FAIL light should be ON.)

2 Rev. 1

Page 206: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 2

BHT-206A-FMS-7 1

HEATER START AND OPERATION (Cont)

HTR START button switch - Press and HOLD. (Ignition should occur within 5 seconds and not more than 10 seconds.)

HEATER FAIL light should go OUT when heater ignites.

Regulate TEMP CONT knob for desired temperature.

Place HEAT-VENT switch in OFF position, to shut down heater.

NOTE

When HEAT-VENT switch in OFF position, the combustion air blower will continue to operate, cooling and purging the heater, and cutting off automatically when the heater has cooled. If accelerated cooling and purging is desired place switch in VENT position, then return switch to OFF

HEATER MALFUNCTION

A malfunction in the heater or heater unit controls will cause the heater to become inoperative and result in illumination of the HEATER FAIL light. If the malfunction occurs, proceed as follows:

FIREWALL SHUT OFF RELEASE PULL knob - OUT

HEAT-VENT switch - OFF

HTR PWR circuit breaker - OUT.

HTR CONT circuit breaker - OUT.

Rev. 1 3

Page 207: Bell 206A - Flight Manual

Section 3

I BHT-206A-FMS-7

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

Section 3

No change from basic Flight Manual.

4 Rev. 1

Page 208: Bell 206A - Flight Manual

BHT-206A-FMS-8

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-122 206-706-324

LITTER KITS

FAA APPROVED MAY 15, 1968

This supplement shall be attached to Model 206A Flight Manual when 206-706-122 or 206-706-324 Litter Kits have been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

Bell A Subsidiary of Textron Inc

POST OFFICE BOX 462 . FORT WORTH, TEXAS 76101

15 MAY 1968 REVISION 1 - 13 SEPTEMBER 1985

Page 209: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

LOG OF PAGES

REVISION PAGES NO.

Title . . . . . . . . . . . . . . . .1 A-B.. . . . . . . . . . . . . .1 i/ii. . . . . . . . . . . . . . . . . .1 1-6.. . . . . . . . . . . . . .1

PAGES REVISION

NO.

Rev. 1 A

Page 210: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL

I BHT-206A-FMS-8

FAA APPROVED SUPPLEMENT

LOG OF REVISIONS

NO. DATE NO. DATE

Basic ......... .15 May 68 Reissue ....... .15 May 70 1 ............. 13 Sep 85

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 1

Page 211: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Introduction

INTRODUCTION

The Bell Litter Kits Nos. 206-706-122 and 206-706-324, each consist of two litter assemblies mounted longitudinally in the left side of crew and passenger compartments, and all attachment fittings, supports and hardware as installed and secured by Service Instructions Nos. 206-7 and 206-68.

Rev. 1 i/ii

Page 212: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

LITTER PATIENT

Patients must be restrained by litter straps.

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after the kit is installed and ballast readjusted, if necessary, to return empty weight CG to within allowable limits.

LOADING DATA

SPECIAL INSTRUCTIONS

The litter location weight allowable and litter location weight required charts are “Mileage Type” charts. Correct use of the information presented will assure proper load distribution but will not prevent exceeding the 3000 pound gross weight.

With more than 100 pounds in the baggage compartment, the maximum 250 pound litter location weight for each location is allowable.

“Litter location weight” includes litter, patient, belts, splints, etc., supported by the resting points of the litter.

Rev. 1 1

Page 213: Bell 206A - Flight Manual

Section 1

I BHT-206A-FMS-8

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

LOADING DATA (Cont)

The litter provisions kit is included in weight empty and the helicopter should have a permissible weight empty center of gravity with this kit installed.

Depending on helicopter weight and fuel loading, the following combinations can exceed 3000 pounds gross weight which is not permissible.

LOADING CHARTS

EXAMPLE NO. 1

A 200 pound pilot and a 150 pound doctor have 50 pounds in the baggage compartment. What is the maximum litter load allowable?

Using the litter location weight allowable chart for 50 pounds baggage compartment weight, the allowable weight at the intersection of the 200 pound pilot weight column and the 150 pound attendant line is 495 pounds.

LITTER LOCATION WEIGHT ALLOWABLE CHARTS

“0” LBS. BAGGAGE COMPARTMENT WEIGHT

PILOT WEIGH - T (LBS)

2 Rev. 1

Page 214: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

LOADING CHARTS (Cont)

LITTER LOCATION WEIGHT ALLOWABLE CHARTS (Cont)

50 LBS. BAGGAGE COMPARTMENT WEIGHT

LITTER ATTENDANT WEIGHT (APT R.H. SEAT)

PILOT WEIGHT (LBS)

150 175 200 225 250

0 500 500 500 465 415 150 500 500 495 450 405 200 500 500 490 445 400 250 500 500 485 440 395

100 LBS. BAGGAGE COMPARTMENT WEIGHT

PILOT WEIGHT (LBS)

150 175 200 225 250

LITTER 0 500 500 500 500 500 ATTENDANT 150 500 500 500 500 495 WEIGHT 200 500 500 500 500 490 (AFT R.H. SEAT) 250 500 500 500 500 485

EXAMPLE NO. 2

A 150 pound pilot has 150 pounds in the baggage compartment.

1. How much litter location weight is required with the back seat empty?

2. How much litter location weight is required with a 200 pound passenger in the back seat?

Using the litter location weight required chart for 150 pounds in the baggage compartment, the required weight is 185 pounds for each.

Rev. 1 3

Page 215: Bell 206A - Flight Manual

Section 1 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-8

LOADING CHARTS (Cont)

LITTER LOCATION WEIGHT REQUIRED CHARTS (To Maintain C.G. Control)

50 LBS. BAGGAGE COMPARTMENT WEIGHT -

PILOT WEIGHT (LBS)

150 175 200 225 250

LITTER 0 55 15 0 0 0 ATTENDANT 150 0 0

I 0 0 0

WEIGHT 200 0 0 0 0 0 (AFT R.H. SEAT) 250 0 0 0 0 0

150 LBS. BAGGAGE COMPARTMENT WEIGHT

PILOT WEIGHT (LBS)

150 175 200 225 250

LITTER 0 185 135 90 45 0 ATTENDANT 150 185 135 90 35 0 WEIGHT 200 185 135 90 35 0 (AFT R.H. SEAT) 250 185 135 90 35 0

250 LBS. BAGGAGE ,

COMPARTMENT WEIGHT

PILOT WEIGHT (LBS)

150 175 200 225 250

LITTER 0 395 345 300 250 200 ATTENDANT 150 405 360 310 260 205 WEIGHT 200 390 350 305 265 210 (AFT R.H. SEAT) 250 375 335 295 250 210

4 Rev. 1

Page 216: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

LOADING CHARTS (Cont)

Depending on helicopter weight and fuel loading, the preceding combinations can exceed 3000 pounds gross weight which is not permissible.

NOTE

Weight required to be centered in litter area at station 84 (approximately 11 inches aft of crew compartment bulkhead).

Rev. 1 5

Page 217: Bell 206A - Flight Manual

Sections 2 & 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-8

Section 2

No change from basic Flight Manual.

Section 3

No change from basic Flight Manual.

6 Rev. 1

Page 218: Bell 206A - Flight Manual

BHT-206A-FMS-10

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-305

STABILITY AND CONTROL AUGMENTATION SYSTEM

FAA APPROVED MAY 3, 1967

This supplement shall be attached to Model 206A Flight Manual when 206-706-305 Stability and Control Augmentation System (SCAS) has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

Bell A Subsidiary of Textron Inc

POST OFFICE BOX 482. FORT WORTH. TEXAS 78101

3 MAY 1967 REVISION 1 - 13 SEPTEMBER 1985

Page 219: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

LOG OF PAGES

REVISION PAGES NO.

Title . . . . . . . . . . . . . . . .1 A-B.. . . . . . . . . . . . . .1 i/ii. . . . . . . . . . . . . . . . . .1 1-4.. . . . . . . . . . . . . .1

PAGES REVISION

NO.

Page 220: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

LOG OF REVISIONS

NO. DATE

Basic . . . . . . . . . 03 May 87

Reissue . . . . . . . .15 May 70 1 . . . . . . . . . . . . . 13 Sep 85

NO. DATE

APPROVED:

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 1

Page 221: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Introduction

INTRODUCTION

The Bell Stability and Control Augmentation System Kit No. 206-706-305, consists of a sensor-amplifier unit, servo cylinders, transducer assembly, control head and panel, electrical cables, circuit breaker switches, and the required hardware.

Rev. 1 i/ii

Page 222: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Section 1

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight CG to within allowable limits.

Rev. 1 1

Page 223: Bell 206A - Flight Manual

Section 2 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I ENGINE RUNUP CHECK

SAS INVerter circuit breaker - IN.

SAS CONTrol circuit breaker - IN.

POWER switch - PUSH IN (YELLOW light - ON).

Warm up until RED light goes OUT.

CYCLIC switch - PUSH IN (GREEN light - ON).

YAW switch - PUSH IN (GREEN light - ON).

BEFORE TAKEOFF

SAS DISengage button switch on cyclic stick-PRESS & RELEASE. (CYCLIC and YAW lights should extinguish - NO GO lights above cyclic and yaw switches should be steady or flashing RED.)

CYCLIC and YAW switches - PUSH IN (GREEN lights - ON).

IN-FLIGHT OPERATION

SAS can be manually overridden or disengaged during any phase of flight.

2 Rev. 1

Page 224: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 2

BHT-206A-FMS-10 I

IN-FLIGHT OPERATION (Cont)

To disengage SAS during flight, depress SAS DISengage button.

To reactivate SAS during flight, push CYCLIC and YAW switches IN.

NOTE

If system is to be disengaged for an extended period during flight, push SAS POWER switch IN.

EMERGENCY PROCEDURES

1. ERRATIC PITCH, ROLL or YAW OSCILLATIONS.

DISengage SAS. If condition still exists, land as soon as practical.

2. HYDRAULIC ACTUATOR FAILURE (lost motion in control).

DISengage SAS. Land as soon as practical (touch down with slow forward speed).

ENGINE SHUTDOWN

Place all SAS switches in the OFF position prior to engine shutdown.

Rev. 1 3

Page 225: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

Section 3

No change from basic Flight Manual.

4 Rev. 1

Page 226: Bell 206A - Flight Manual

BHT-206A-FMS-1 1

206A

ROTORCRAFTFLIGHT MANUAL

SUPPLEMENT FOR206-706-027

SNOW WINTERIZATION-AIR INDUCTION SYSTEM

CERTIFIEDSEPTEMBER 10, 1968

This supplement shall be attached to Model 206AFlight Manual when the 206-706-027 SnowWinterization - Air Induction System has beeninstalled.

Information contained herein supplementsinformation of basic Flight Manual. For Limitations,Procedures, and Performance Data not contained inthis supplement, or other applicable supplements,. consult basic Flight Manual.

Bell Helicopter TextronA Subsidiary of Textron Inc

POST OFFICE BOX 482 * FORT WORTH, TEXAS 76101

COPYRIGHT NOTICE

COPYRIGHT 2000BELL ® HELICOPTER TEXTRON INC.AND BELL HELICOPTER TEXTRON,A DIVISION OF TEXTRON CANADA LTD.

ALL RIGHTS RESERVED REISSUE - 6 OCTOBER 2000

Page 227: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Log of PagesSUPPLEMENT

BHT-206A-FMS-11

LOG OF PAGES

REVISION REVISIONPAGES NO. PAGES NO.

Title .................. 0A - B ................ 0i/ii ....................1-6 . ................ 0

October 6, 2000 A

Page 228: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-11

LOG OF TC APPROVED REVISIONS

REVISION REVISIONNO. DATE NO. DATE

Basic ........... 10 Sep 68Reissue ........ 15 May 701 ............... 13 Sep 85Reissue ........ 13 Sep 95Reissue ........ 06 Oct 00

APPROVED:

CHIEF, FLIGHFORDIRECTOR - AIRCRAFT CERTIFICATIONTRANSPORT CANADA

NOTE: Revised text is indicated by a black vertical line.Insert latest revision pages; dispose of superseded pages.

B October 6, 2000

Page 229: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL GeneralSUPPLEMENT Information

BHT-206A-FMS-11

GENERAL INFORMATION

The Bell Snow Winterization Kit, No. 206-706-027, modifies theengine air induction system intake area and insulates the inductonsection of the engine cowling. The kit consists of sections ofinsulation, adapters, sheet metal parts, hardware and materialsrequired for a complete installation. The modified cowling section,when installed, will allow flight operations to be conducted in fallingsnow.

October 6, 2000 i/ii

Page 230: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 1SUPPLEMENT

BHT-206A-FMS-11

Section 1

AMBIENT TEMPERATURE OPERATING LIMITS

Maximum 70°F (21.1°C) with complete snow winterization kitinstalled. ABOVE 70°F (21.1°C) remove forward shield assembly, PartNo. 206-060-848-1, and both aft adapters, Part Nos. 206-060-847-1 and206-060-847-2, from the engine air intake cowling.

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after the kit is installed andballast readjusted, if necessary, to return empty weight CG to withinallowable limits.

TYPE OF OPERATION

The Engine (Automatic) Re-Ignition System (BHT-206A-FMS-25) shallbe installed in conjunction with Snow Winterization Kit whenconducting flight operations in falling and/or blowing snow and the. following limits apply:

1. Take-off is prohibited with any snow or ice present in inlet orplenum areas.

2. Ground operations and hover flight time is limited to 20 minutestotal duration per occurrence. Ground operations at idle power(twist grip at idle) shall not exceed five (5) minutes. If five (5)minutes idle power time limit is exceeded or ground and hoveroperations exceed 20 minutes total, helicopter shall be shut downand inspected per Section 2, EXTERIOR CHECK.

3. Flight operations are prohibited when visibility in falling and/orblowing snow is less than one-half (1/2) mile.

October 6, 2000 1

Page 231: Bell 206A - Flight Manual

Section 2 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-11

Section 2

EXTERIOR CHECK

FUSELAGE - CENTER SECTION

Engine air inlet area - Remove forward shield assembly and both aftadapters when ambient temperature is above 70°F (21.1°C).

BEFORE EACH FLIGHT WHEN OPERATING IN SNOWCONDITIONS

Immediately before each flight, thoroughly check cabin roof,transmission and engine air inlet area. All areas must be free ofaccumulated snow, slush, and ice before each flight.

Open inspection doors at top of compartment and check engine inlet,screen and firewall insulation for accumulation of ice and snow. Cleanareas thoroughly before each flight.

AFTER EXITING HELICOPTER IN FALLING OR BLOWINGSNOW

FAILURE TO INSTALL ENGINE INLETCOVERS COULD ALLOW FALLING/BLOWINGSNOW TO ENTER THE ENGINE INLET.

Install protective covers (engine inlet, exhaust, and pitot tube) duringany exposure to falling and/or blowing snow during non-engineoperation.

2 October 6, 2000

Page 232: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 2SUPPLEMENT

BHT-206A-FMS-11

POWER CHECK CHART

SNOW WINTERIZATION KIT INSTALLED

ANTI-ICE OFF ZERO AIRSPEEDGENERATOR OFF ENGINE RPM 100%

Page 233: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-11

Section 3

PERFORMANCE

The Snow Winterization Kit causes a decrease in engine inlet pressure(with respect to the standard inlet) which reduces the power availablewhen operating at turbine outlet temperature limits. Thus, wheneverthe ambient conditions are such that the torque pressure limits cannotbe obtained because of turbine outlet temperature limits, theperformance obtainable with the Snow Winterization Kit installed isless than that which is obtainable with the standard inlet.

A chart for Performance Determination is provided to determinewhether or not standard inlet performance is obtainable. This chart isused as Follows:

Determine the intersection of the desired pressure altitude andambient temperature.

Using a power condition, point (A), for which the chart curve liesto the right of the altitude/temperature intersection, theperformance obtainable is as published for the standard inlet.

NOTE

The standard inlet performance is as published eitherin the basic Flight Manual or in the appropriateSupplement (other than this Supplement) for thedesired power condition.

4 October 6, 2000

Page 234: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-11

PERFORMANCE (Cont)

Using a power condition, point (B), for which the chart curve lies. to the left of the altitude/temperature intersection, theperformance obtainable is less than is published for the aircraftwith standard inlet as follows:

For any gross weight:

Rate of climb is 300 ft/min. less

Hover-ceiling is 2000 ft. less

POWER DETERMINATION

(A) WHEN POWER CONDmON CURVE IS TO RIGHT OFALTITUDE/TEMPERATURE INTERSECTION, NOLOSS OF PERFORMANCE FROM STANDARD INLET.

10(B) WHEN POWER CONDITION CURVE IS TO LEFT OF

ALTITUDE/TEMPERATURE INTERSECTION, HOVERCEILNG IS 2000 FT LESS, AND RATE OF CUMB IS300 FT/MIN LESS THAN STANDARD INLET

8 PERFORMANCE-

:

-50 -40 -30 -20 -10 0 10 20OAT - *C

October 6, 2000 5

Page 235: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-11

PERFORMANCE (Cont)

EXAMPLE - HOVER PERFORMANCE

1. Pressure altitude: 5000 feet.

2. Ambient temperature (OAT): 15°C

3. Desired flight condition: Hover IGE

4. Desired power condition: T.O.P. Anti-Ice OFF.

5. Configuration (other than Snow Winterization Kit): Basic.

6. Find the maximum gross weight for the above conditions.

7. From Performance Determination chart, it is noted that thehover ceiling will be 2000 feet less, since the power conditioncurve is to the left of the altitude/temperature intersection, point(B).

8. Add pressure altitude and loss: 5000 + 2000 = 7000 feet

9. From Basic Flight Manual, find the gross weight for 7000 feetand 15°C = 2850 pounds. This is the maximum gross weight atwhich it is possible to hover for the given conditions.

EXAMPLE - RATE OF CLIMB

1. Find the rate of climb for the above conditions.

2. From the Basic Flight Manual:

Rate of Climb at 2600 lbs GW = 1410 ft/min.Rate of Climb at 3000 lbs GW = 930 ft/min.Difference: 400 lbs 480 ft/min.

Desired GW 2850 lbsLower GW 2600 lbsDifference 250 lbs

Basic Rate of Climb at 2850 = 1410 - 250/400 (480)= 1110 ft/min.

3. Snow Winterization Kit loss = 300 ft/min.

Therefore, Snow Winterization Kit rate of climb = 1110 - 300= 810 ft/min.

6 October 6, 2000

Page 236: Bell 206A - Flight Manual

BHT-206A-FMS-12

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-3 10

FIRE EXTINGUISHER - ENGINE COMPARTMENT

FAA APPROVED DECEMBER 19, 1968

This supplement shall be attached to Model 206A Flight Manual when 206-706-310 Fire Extinguisher - Engine Compartment has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

A Subsidiary of Textron Inc

POST OFFICE BOX 482. FORT WORTH, TEXAS 78101

19 DECEMBER 1968 REVISION 1 - 13 SEPTEMBER 1985

Page 237: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Log of Pages

LOG OF PAGES

REVISION PAGES NO.

Title . . . . . . . . . . . . . . . .1 A-B.. . . . . . . . . . . . . .1 i/ii. . . . . . . . . . . . . . . . . .1 l-2 . . . . . . . . . . . . . . . 1 3/4. . . . . . . . . . . . . . . . .1

PAGES REVISION

NO.

Rev. 1 A

Page 238: Bell 206A - Flight Manual

i

Log of Revisions

I

- .

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-12

LOG OF REVISIONS

NO. DATE

Basic . . . . . . . . . .19 Dec 68

Reissue . . . . . . . .15 May 70 1 . . . . . . . . . . . . . 13 Sep 85

NO. DATE

APPROVED:

MANAGER

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 1

Page 239: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Introduction

INTRODUCTION

The Bell Fire Extinguisher Kit, No. 206-706-310, when installed will provide the pilot with a cockpit controlled, fire fighting system for use in the event of a fire occuring in the engine compartment section of the airframe. The kit consists of a pressurized extinguishing agent bottle, discharge tubing and nozzles, supports, brackets, electrical components and all hardware to complete the installation. The system also includes a charged-discharged indicator that can be visually checked externally

Rev. 1 i/ii

Page 240: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

BHT-206A-FMS-12

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight C.G. within allowable limits.

Rev. 1 1

Page 241: Bell 206A - Flight Manual

Section 2 206A FLIGHT MANUAL FAA APPROVED

I

SUPPLEMENT BHT-206A-FMS-12

Section 2

NORMAL PROCEDURES

EXTERIOR CHECK

FUSELAGE - CENTER RIGHT SIDE

Fire extinguisher bottle pressure - Check GREEN range.

Fire extinguisher indicator disc - Check RED.

INTERIOR CHECK

FIRE EXTinguisher switch - OFF, guard DOWN.

EMERGENCY PROCEDURES

I

ENGINE FIRE In the event of fire in the engine compartment as indicated by illumination of the FIRE warning light (if installed) proceed as follows:

I

Enter autorotation (inflight).

Throttle - Closed.

Main fuel switch - OFF

FIRE EXTinguisher switch - UP for ON.

I Execute an autorotative landing (inflight).

2 Rev. 1

Page 242: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

No change from basic Flight Manual.

Rev. 1 3/4

Page 243: Bell 206A - Flight Manual

BHT-206A-FMS-13

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-309

FIRE DETECTOR

FAA APPROVED JUNE 6, 1969

This supplement shall be attached to Model 206A Flight Manual when 206-706-309 Fire Detector has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

A Subsidiary of Textron Inc

POST OFFICE BOX 482 l FORT WORTH. TEXAS 78101

6 JUNE 1969 REVISION 1 - 13 SEPTEMBER 1985

Page 244: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

BHT-206A-FMS-13

LOG OF PAGES

REVISION PAGES NO.

Title . . . . . . . . . . . . . . . .1 A-B. . . . . . . . . . . . . . .1 i/ii. . . . . . . . . . . . . . . . . .1 1-2... . . . . . . . . . . . . . .1 3/4.. . . . . . . . . . . . . . . .1

PAGES REVISION

NO.

Rev. 1 A

Page 245: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-13

LOG OF REVISIONS

NO. DATE

Basic. . . . . . . . . . .06 Jun 69

Reissue . . . . . . . .15 May 70

1 . . . . . . . . . . . . . 13 Sep 85

NO. DATE

B Rev. 1

Page 246: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Introduction

INTRODUCTION

The Bell Fire Detector Kit, No. 206-706-309, when installed, will provide the pilot with a FIRE warning indicator, which will illuminate if a fire develops in the engine compartment. The kit consists of two fire detector elements, amplifier, warning light, edge lit panel or post light, electrical components and all hardware required to complete the installaton.

Rev. 1 i/ii

Page 247: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Section 1

BHT-206A-FMS-13

-- CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight CG within allowable limits.

--

Rev. 1 1

Page 248: Bell 206A - Flight Manual

Section 2 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-13

NORMAL PROCEDURES

BEFORE TAKEOFF

FIRE DETECTOR SYSTEM CHECK

Prior to takeoff perform system functional check as follows:

FIRE DETECT TEST switch - Move switch to UP (No. 1) position, FIRE warning light should illuminate, return switch to CENTER position.

FIRE DETECT TEST switch - Move switch to DOWN (No. 2) position, FIRE warning light should illuminate, return switch to CENTER position.

EMERGENCY PROCEDURES

CAUTION SYSTEM

WARNING LIGHT FAULT AND REMEDY

FIRE OR FIRE WARNING Fire in engine compartment.

Enter autorotation (inflight).

Throttle - Closed.

Main fuel switch - OFF

FIRE EXTinguisher switch (if installed) - UP for ON.

Execute an autorotative landing (inflight).

2 Rev. 1

Page 249: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

No change from basic Flight Manual.

Rev. 1 314

Page 250: Bell 206A - Flight Manual

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-124 206-706-126

EXTERNAL HOIST

FAA APPROVED JULY 25, 1969

This supplement shall be attached to Model 206A Flight Manual when 206-706-124 or ,206-706-126 External Hoist has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

A Subsidiary of Textron Inc

POST OFFICE BOX 402 l FORT WORTH, TEXAS 76101

25 JULY 1969 REVISION 2 - 26 JULY 1988

Page 251: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

BHT-206A-FMS-14

LOG OF PAGES

REVISION PAGES NO.

Title. . . . . . . . . . . . . . . . . .2 A-B.. . . . . . . . . . . . . . . .2 i/ii . . . . . . . . . . . . . . . . . . .1 1 .l 2-6...................2

PAGES REVISION

NO.

Rev. 2 A

Page 252: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-14

LOG OF REVISIONS

NO. DATE

Basic . . . . . . . . . . .25 Jul 69 Reissue. . . . . . . . .26 Jun 72 1 . . . . . . . . . . . . . 13 Sep 65

2 . . . . . . . . . . . . . 26 Jul 88

NO. DATE

APPROVED:

MANAGER

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 2

Page 253: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Introduction

INTRODUCTION

The Bell Hoist Kit, No. 206-706-124 or 206-706-126, consists of a hoist motor and winch assembly, mounting frame, master control panel, crew member’s pendant control, electrical components, wiring, and all the hardware necessary to complete the installation. The winch unit of the 206-706-124 Hoist Kit contains 100 feet and the winch unit of the 206-706-126 Hoist Kit contains 110 feet of usable cable. Each winch unit when actuated has a rate of cable travel of 50 feet per minute. The control panel is edge lighted and contains a Power Selector switch, for pilot or crew member hoist operation, and a Cable Cut switch for use in the event of an emergency. The control panel of the 206-706-124 Hoist Kit also contains an Overheat Warning light which when illuminated indicates an overtemp condition of the hoist motor. Installation of the hoist will allow the pilot or crew member to deliver or pick up cargo from areas that are not suitable for landing the helicopter.

Rev. 1 i/ii

Page 254: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

BHT-206A-FMS-14

AIRSPEED LIMITATIONS

The object being hoisted shall be completely in the cabin before forward flight is established.

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight C.G. within allowable limits.

TYPE OF OPERATION

Hoist operations shall be conducted under the appropriate operating rules for external loads.

Passenger operations with hoist installed are approved if the hoist is not used and the hoist electrical system is deactivated.

Flight operations requiring use of the hoist ARE PROHIBITED and the system SHALL BE DEACTIVATED when the Float Kit, 206-706-008, is installed.

Simultaneous use of the hoist and the external cargo hook is prohibited.

LOADING LIMITATIONS

Hoist loading - Maximum 300 pounds.. (Refer to Section IV, Hoist Loading Nomograph.)

Rev. 1 1

Page 255: Bell 206A - Flight Manual

Section 2

BHT-206A-FMS-14

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

Section 2

NORMAL PROCEDURES

EXTERIOR CHECK

FUSELAGE CABIN - LEFT SIDE

I Hoist - Condition, security, wiring connected. Ensure hook firmly seated against bumper pad.

Aft cabin door - Removed, if hoist is to be used.

INTERIOR CHECK

Crew member’s hoist control -Installed, stowed, wiring connected.

BEFORE TAKEOFF

I

NOTE

Perform hoist power check if hoist operations are anticipated.

HOIST POWER CHECK

Prior to takeoff perform hoist operation functional check as follows:

HOIST POWER and CABLE CUT circuit breakers - IN.

HOIST POWER switch - PILOT position.

2 Rev. 2

Page 256: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Section 2

BHT-206A-FMS-14

BEFORE TAKEOFF (Cont)

HOIST POWER CHECK (Cont)

HOIST OVERHEAT WARNING light - PRESS TO TEST (light ON) then release (206-706-124 Hoist Kit ONLY).

HOIST switch, pilot’s - PRESS switch DN (down) to lower hook approximately two feet, then UP to raise hook.

HOIST POWER switch - CREW position.

HOIST switch, crew member - PRESS switch DN (down) to lower hook approximately two feet, then UP to raise hook.

HOIST POWER switch - OFF position.

Pilot or crewmember - Ensure hook firmly seated against bumper pad. I

IN-FLIGHT OPERATIONS

HOIST OPERATING PROCEDURE

HOIST POWER switch - PILOT or CREW position.

Establish zero ground speed over pickup location.

HOIST switch - DN (Down) to lower hook.

NOTE

Allow a 30 second rest period between each 1/2 cycle (i.e. full up or full down) of operation. Lift hoist load slightly above contact surface, by application of collective pitch, to obtain a sense of control feel.

HOIST switch - UP to raise hoist load.

Rev. 2 3

Page 257: Bell 206A - Flight Manual

Section 2 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-14

IN-FLIGHT OPERATIONS (Cont)

HOIST OPERATING PROCEDURE (Cont)

To prevent overheating and damage to the hoist motor ONLY three (3) consecutive cycles (i.e. full up and full down) are permitted. After three (3) full cycles of operation allow a 40 minute period for cooling. Overheating of the 206-706-124 winch motor will be indicated by illumination of the OVERHEAT WARNING light.

HOIST POWER switch - OFF after completing hoist operation.

Pilot or crewmember - Ensure hook firmly seated against bumper pad.

AFTER EXITING HELICOPTER

POST FLIGHT CHECK

Hoist - Condition and security. Ensure hook firmly seated against bumper pad.

NOTE

After last flight of the day, if the hoist has been used, maintenance action is required.

EMERGENCY PROCEDURE

In the event of an emergency, LIFT CABLE CUT switch guard I and actuate SWITCH to cut cable and drop hoist load.

4 Rev. 2

Page 258: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-14

No change from basic Flight Manual.

Rev. 2 5

Page 259: Bell 206A - Flight Manual

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

Section 4

BHT-206A-FMS-14

Section 4

HOIST LOADING NOMOGRAPH

MAXIMUM NOTES: HOIST LOAD (LBS) 1. Fuel loads shown must be the least amount HORIZONTAL HORIZONTAL

available while load is on the hoist. c G’ RANGE C.G. RANGE

2. Gross Weight must not exceed max. allowable. STA. 106.0-108.0 STA. 108.0-114.2

EXAMPLE A - - - - 200 Lb. pilot and 150 Lb. load in the left seat - for a horizontal C.G. range of 106.0 to 106.0 and a fuel load of 20 Gal., the hoist loading allowable is 200 pounds. For a horizontal C.G. range of 106.0 to 114.2 and a fuel load of 60 gallons the hoist loading allowable is 300 pounds.

PILOT WEIGHT (LBS)

I 6 Rev. 2

L.H. SEAT LOAD (LBS)

60 93 107 152 170 189

100 113 127 172 190 209

120 133 147 192 210 229

140 153 167 212 230 249

160 173 187 232 250 269

180 193 207 252 270 289

200 213 227

220 233 247

240 253 267

260 273 287

300 LBS. 300 MAXIMUM

ALLOWABLE HOIST LOAD

FUEL LOAD-GALLONS

Page 260: Bell 206A - Flight Manual

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-031

HI-SKID LANDING GEAR TUBULAR TYPE

FAA APPROVED SEPTEMBER 10, 1969

This supplement shall be attached to Model 206A Flight Manual when the 206-706-031 Hi-Skid Landing Gear Tubular Type hasbeen installed in accordance with Bell Drawing number 206-706-031.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

Bell A Subsidiary of Textron Inc

POST OFFICE BOX 482 l FORT WORTH. TEXAS 76101

10 SEPTEMBER 1969 REVISION 3 - 13 SEPTEMBER 1985

Page 261: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

BHT-206A-FMS-15

LOG OF PAGES

REVISION PAGES NO.

Title . . . . . . . . . . . . . . . .3 A-B.. . . . . . . . . . . . ..3 i/ii. . . . . . . . . . . . . . . . . .3 1-6.. . . . . . . . . . . . . .3

PAGES REVISION

NO.

Rev. 3 A

Page 262: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-15

LOG OF REVISIONS

NO. DATE

Basic . . . . . . . . . .lOSep69

Reissue . . . . . . . .15May70 1 . . . . . . . . . . . . . . 23 Jut 70 2 . . . . . . . . . . . . . 08 Nov 83 3 . . . . . . . . . . . . . 13Sep85

NO. DATE

APPROVED:

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 3

Page 263: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Introduction

INTRODUCTION

The Bell Hi-Skid (Tubular Type) Landing Gear Kit No. 206-706-031, when installed will provide an approximate 13 additional inches of ground clearance which will permit landings to be accomplished in rough terrain areas. The kit consists of fore and aft cross tubes, skid tubes, four fuselage mounted cabin steps and the necessary hardware to complete the installation.

Rev. 3 i/ii

Page 264: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Section 1

BHT-206A-FMS-15 I

WEIGHT LIMITATIONS

Maximum approved gross weight is 2900 pounds.

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight CG to within allowable limits.

TYPE OF OPERATION

Flight operations are prohibited with the rear passenger steps installed when the helicopter is equipped with the combination of the External Cargo Hook Kit, No. 206-706-101, and the Hi-Skid Landing Gear.

Flight operations are prohibited with the left rear passenger step installed when the helicopter is equipped with the combination of the External Hoist Kit, No. 206-706-124, and the Hi-Skid Landing Gear.

The four steps, installed as part of the Hi-Skid Landing Gear Kit, are not approved for use with any other type of landing gear.

Refer to Particle Separator Supplement when the Particle Separator is installed.

Rev. 3 1

Page 265: Bell 206A - Flight Manual

Sections 2 & 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-15

Section 2 .

LANDING TOUCHDOWN

Tail low run-on landings should be avoided to prevent nose-down pitching.

RUN-ON LANDINGS on other than a HARD FIRM SURFACE should be exercised with CAUTION.

OUT OF GROUND EFFECT hovering performance is the same as the basic helicopter.

IN GROUND EFFECT hovering performance is shown on the following performance charts.

2 Rev. 3

Page 266: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL section3 SUPPLEMENT

BHT-ZOBA-FMS-15 1

6.000 FT. DEN. MT,

2 LB” 100

OAT-T r I 1 I I 9 10 11 12 13 14 Kgr 100

GROSS WEIGHT 2067oCIU

Rev. 3

Page 267: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-15

HOVER CEILING IN GROUND EFFECT TAKEOFF POWER 5° TO 37.8°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 3.0 FT. (0.9 METERS) ENGINE RPM 100%

0 10 20 30 40 20 24 28 32 LB x 100 OAT-°C

GROSS WEIGHT 206706-149

4 Rev. 3 ’

Page 268: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Section 3

HOVER CEILING IN GROUND EFFECT MAX. CONTINUOUS POWER 5° TO -25°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 3.0 FT. (0.9 METERS) ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 330 LBS (150 kg) LESS

BASIC SHIP WITH HIGH SKID GEAR

LB x 100

OAT-°32

GROSS WEIGHT 206706151

Rev. 3 5

Page 269: Bell 206A - Flight Manual

Section 3

I BHT-206A-FMS-15

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

HOVER CEILING IN GROUND EFFECT MAX. CONTINUOUS POWER 5° TO 37.8°C

GENERATOR 22.3 AMPS SKID HEIGHT 3.0 FT (0.9 METERS)

ANTI-ICE OFF ENGINE RPM 100%

BASIC SHIP WITH HIGH SKID GEAR

DEN. ALT-

OAT-°C 100

GROSS WEIGHT 206706-150

6 Rev. 3

Page 270: Bell 206A - Flight Manual

BHT-206A-FMS-16

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-400

WATER ALCOHOL POWER AUGMENTATION

FAA APPROVED NOVEMBER 26, 1969

This supplement shall be attached to Model 206A Flight Manual when 206-706-400 Water-Alcohol Augmentation System has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

Bell A SubsdIary of Textron Inc

POST OFFICE BOX 402 l FORT WORTH, TEXAS 76101

26 NOVEMBER 1969 REVISION 1 - 13 SEPTEMBER 1985

Page 271: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

LOG OF PAGES

REVISION PAGES NO.

Title . . . . . . . . . . . . . . . .1 A-B.. . . . . . . . . . . . . .1 i/ii. . . . . . . . . . . . . . . . . .1 l-6 . . . . . . . . . . . . . . . . 1 7/8. . . . . . . . . . . . . . . . .1

PAGES REVISION

NO.

Rev. 1 A

Page 272: Bell 206A - Flight Manual

Log of Revisions

I BHT-206A-FMS-16

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

LOG OF REVISIONS

NO. DATE

Basic . . . . . . . . . .26 Nov 69 Reissue . . . . . . . .15 May 70 1 . . . . . . . . . . . . . 13 Sep 85

NO. DATE

APPROVED:

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 1

Page 273: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL

INTRODUCTION

introduction

The Water-Alcohol Power Augmentation Kit, No. 206-706-400, when installed and used by the pilot will provide increased hot day performance. The performance increase is obtained by injecting a water-alcohol mixture into the engine inlet to reduce turbine outlet temperature and thereby results in additional power available. The additional power available is limited by the torque red line or the turbine outlet temperature red line, whichever occurs first. The kit consists of a three gallon tank (pressurized by engine bleed air), solenoid valve, tubing, injector nozzles, indicator lights, switches, wiring and all the hardware required to complete the installation.

ATTENTION

The Allison Model 250-C18B engine MUST BE INSTALLED in the helicopter when the Water Alcohol Kit is installed.

Rev. 1 i/ii

Page 274: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

AIRSPEED LIMITATIONS

Vne 60 MPH (52 knots) when using water-alcohol injection.

POWER PLANT LIMITATIONS

Allison Model 250-C18B.

WATER-ALCOHOL INJECTION FLUID

The water-alcohol injection fluid mixture shall consist of one (1) part alcohol and two (2) parts water and shall meet Allison specifications as follows:

WATER - Allison specification EMS 120A. (Commercial Equivalent - Purified distilled water.)

ALCOHOL, Synthetic Methyl - Allison specification EMS 125D. (Commercial Equivalent - Menthanol in concentrations not less than I 99.85% by weight.)

TEMPERATURE OPERATING LIMITS

Ambient temperature - Use of water - alcohol injection is PROHIBITED at temperatures BELOW + 40°F (4.4°C).

Rev. 1 1

Page 275: Bell 206A - Flight Manual

Section 1 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-16

ENGINE POWER LIMITATIONS

Engine torque and turbine outlet temperature limits shall not be exceeded when the water - alcohol power augmentation system is used. DO NOT USE water - alcohol injection below 693°C TOT.

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight CG to within allowable limits.

FRONT SEAT TOTAL WEIGHT LIMITS

Minimum - 165 pounds, with water-alcohol tank filled to 3 gallons capacity

LOADING LIMITATIONS

BAGGAGE LOADING LIMITS

Maximum 210 pounds, when Water -Alcohol Kit is installed.

PLACARDS (located on water - alcohol tank)

WHEN WATER - ALC KIT IS INSTALLED

REDUCE ALLOWABLE WEIGHT BY 40 LBS.

DO NOT REMOVE FILLER CAP DURING

ENGINE OPERATION AND/OR ONE (1) MINUTE AFTER ENGINE SHUTDOWN

2 Rev. 1

Page 276: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL

PLACARDS (Cont)

Section 1

DO NOT PUT IGNITION SOURCES (i.e. ELECTRICAL EQUIPMENT) IN BAGGAGE

COMPARTMENT WHEN WATER -ALCOHOL

TANK IS INSTALLED

3.0 GALLON CAPACITY MIXTURE TO BE ONE (1) PART BY VOLUME

OF ALCOHOL PER ALLISON SPEC. EMS - 125 AND TWO (2) PARTS BY VOLUME OF WATER PER ALLISON SPEC. EMS - 120

TYPE OF OPERATION

The Water-Alcohol Power Augmentation System SHALL BE MADE INOPERATIVE when the Particle Separator kit is installed.

Rev. 1 3

Page 277: Bell 206A - Flight Manual

Section 2 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-16

NORMAL PROCEDURES -

I EXTERIOR CHECK

FUSELAGE - CABIN LEFT SIDE.

Do not remove cap from the water - alcohol tank until ONE MINUTE after engine shutdown, as the tank is pressurized by engine bleed air.

Water-alcohol tank - Filled, if desired, cap secured.

Tank Capacity - 3.0 U.S. gallons, consisting of one (1) part, by volume of Alcohol and two (2) parts, by volume of water.

WATER - ALCOHOL INJECTION PROCEDURE

NOTE

The available injection time is approximately two (2) to three (3) minutes, depending upon the flow rate. When the tank quantity is depleted to approximately one - half (1/2) gallon the W/A LOW LEVEL light will illuminate.

4 Rev. 1

Page 278: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 2

WATER-ALCOHOL INJECTION PROCEDURE (Cont)

WATER-ALCOHOL switch - ON.

Turbine outlet temperature (TOT) - Minimum 693°C.

NOTE

When performing the following procedural step the green flow light will be ON and a TOT temperature decrease will be noticeable. This will constitute a system functional check.

W/A INJECT switch (Collective stick) - ON (green flow light ON), monitor TOT and torque instruments and adjust power as required to maintain engine operation within red line operating limits.

When the W/A LOW LEVEL light illuminates the remaining fluid will provide approximately 20 seconds of water-alcohol injection time.

W/A LOW LEVEL light - When light illuminates schedule the use of the remaining fluid and be prepared to reduce power to prevent exceeding the TOT limit.

If engine is being operated at TOT red line, with water injection, and fluid supply becomes depleted (green flow light goes OUT) an over-temperature TOT will occur. Reduce power as necessary to prevent TOT from exceeding 749°C.

Prior to terminating W/A injection flow, reduce power and TOT.

W/A INJECT switch - OFF, adjust power and TOT as required.

WATER - ALCOHOL switch - OFF

Rev. 1 5

Page 279: Bell 206A - Flight Manual

Section 3

I BHT-206A-FMS-16

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

HOVER PERFORMANCE INCREASE WITH WATER -ALCOHOL INJECTION

Hovering capability of the helicopter is substantially improved, due to the power available increase, both In and Out of Ground Effect, when water - alcohol injection is used. This performance increase is shown on the IGE and OGE Hover Ceiling Increase Chart, that is to be used as follows:

EXAMPLE:

Determine the gross weight pounds at which the helicopter can hover in ground effect at 6000 feet pressure altitude and an ambient air temperature of 35°C.

Enter bottom of chart at 35°C and proceed vertically to intersection of the in ground effect curve, then move left to the altitude scale and read 2800 feet. (2800 feet is the hovering IGE performance altitude increase when using water - alcohol injection.)

Subtract the 2800 foot altitude increase from the existing 6000 feet pressure altitude to obtain an adjusted equivalent operating pressure altitude of 3200 feet.

Refer to Basic Flight Manual chart for Hovering Ceiling, T.O. Power, IGE, Anti - Ice Off for use as an example.

Enter altitude scale at the adjusted pressure altitude of 3200 feet and move right to the intersection of the 35°C temperature curve, then

6 Rev. 1

Page 280: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 3 SUPPLEMENT

HOVER PERFORMANCE INCREASE WITH WATER-ALCOHOL INJECTION (Cont)

drop vertically to the gross weight scale and read 2830 pounds. This is the maximum IGE hovering gross weight in zero wind using T.O. power and water - alcohol injection.

NOTE

2510 pounds is the IGE hovering ceiling G.W. for the basic helicopter at 6000 feet and 35°C without W/A injection. If a G.W. increase is not required the IGE hovering ceiling will be 8800 feet at 35°C when W/A injection is used, i.e. 6000 feet plus 2800 feet equals 8800 feet pressure altitude.

IGE AND OGE HOVER CEILING INCREASE USING T.O. POWER AND W/A INJECTION

4000

3000

1000

0 5 10 15 20 25 30 35 40 45 50

AMBIENT AIR TEMPERATURE - °C

Rev. 1 718

Page 281: Bell 206A - Flight Manual

BHT-206A-FMS-17

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-603

FUEL FILTER

FAA APPROVED JANUARY 13, 1970

This supplement shall be attached to Model 206A Flight Manual when 206-706-603 Fuel Filter has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

A Subsidiary of Textron Inc

POST OFFICE BOX 482 l FORT WORTH, TEXAS 76101

13 JANUARY 1970 REVISION 2 - 13 SEPTEMBER 1985

Page 282: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

LOG OF PAGES

REVISION NO.

Title . . . . . . . . . . . . . . . .2 A-6.. . . . . . . . . . . . . .2 i/ii. . . . . . . . . . . . . . . . . .2 I-2.. . . . . . . . . . . . . .2 3/4. . . . . . . . . . . . . . . . .2

PAGES REVISION

NO.

Rev. 2 A

Page 283: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-17

LOG OF REVISIONS

NO. DATE

Basic.. . . . . . . . . .13 Jan 70

Reissue . . . . . . . .15 May 70 1 . . . . . . . . . . . . . 14 Feb 79 2 . . . . . . . . . . . . . 13 Sep 85

NO. DATE

APPROVED:

MANAGER

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 2

Page 284: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Introduction

BHT-206A-FMS-17

INTRODUCTION

The Bell Fuel Filter Kit, 206-706-603, when installed will eliminate the requirement of adding the anti-icing additive to the fuel supply when temperatures are below 40°F (4°C). The kit consists of the fuel filter unit, mounting bracket, hose assemblies, electrical cable assemblies, indicator light and the required hardware to make a complete installation.

--

Rev. 2 i/ii

Page 285: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Section 1

POWER PLANT LIMITATIONS

FUEL

The fuel supply DOES NOT REQUIRE the addition of the anti-icing additive, MIL-27686 (PFA-55MB), at temperatures below 40°F (4°C) when the Fuel Filter is installed in the fuel system.

Rev. 2 1

Page 286: Bell 206A - Flight Manual

Section 2 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-17

NORMAL PROCEDURES

I EXTERIOR CHECK

FUSELAGE - CENTER RIGHT SIDE.

A/F Fuel Filter - Drain and check before first flight of the day as follows:

Battery switch - ON.

Fuel valve switch - ON.

Fuel boost pumps - ON.

Fuel filter drain valve - Open, drain sample, then close.

2 Rev. 2

Page 287: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Sections 2 & 3

BHT-206A-FMS-17

I EXTERIOR CHECK (Cont)

NOTE

Filter test switch is located on top of fuel filter.

Fuel filter test switch - Depress and check A/F FUEL FILTER caution light on. Release switch and check light out.

Fuel valve switch - OFF.

Battery switch - OFF.

EMERGENCY PROCEDURES

CAUTION SYSTEM

CAUTION LIGHT FAULT AND REMEDY

A/F FUEL FILTER - Fuel filter clogged, land as soon as practical.

No change from basic Flight Manual.

Rev. 2 3/4

Page 288: Bell 206A - Flight Manual

BHT-206A-FMS-1 8

MODEL206A

ROTORCRAFTFLIGHT MANUAL

SUPPLEMENT FOR206-706-200-9 AND 206-706-201-17

SNOW PARTICLESEPARATOR

ENGINE AIR INDUCTIONSYSTEMS

CERTIFIEDJULY 23, 1970

This supplement shall be attached to Model 206AFlight Manual when the 206-706-200-9 or206-706-201-17 Snow Particle Separator Engine AirInduction System has been installed.

Information contained herein supplementsinformation of basic Flight Manual. For Limitations,Procedures, and Performance Data not contained inthis supplement, or other applicable supplements,consult basic Flight Manual.

Bell Helicopter TextronA Subsidiary of Textron Inc

POST OFFICE BOX 482 * FORT WORTH, TEXAS 76101

COPYRIGHT NOTICE

COPYRIGHT 2000BELL ® HELICOPTER TEXTRON INC.AND BELL HEUCOPTER TEXTRON,A DMSION OF TEXTRON CANADA LTD.

ALL RIGHTS RESERVED REISSUE -6 OCTOBER 2000

Page 289: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Log of PagesSUPPLEMENT

BHT-206A-FMS-18

LOG OF PAGES

REVISION REVISIONPAGES NO. PAGES NO.

Title .................. 0A-B . ............... 0i/ii .................... 01 - 46 ................ 047/48 ................. 0

October 6, 2000 A

Page 290: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

LOG OF TC APPROVED REVISIONS

NO. DATE NO. DATE

Basic ............ 23 Jul 701 ............... 04 Sep 702 ............... 18Oct713 ............... 08 Nov 834 ............... 13 Sep 855 ............... 14Oct886 ............... 22 Feb 89Reissue ........ 06 Oct 00

APPROVED:

CHIEF, FLIGHT TESTFORDIRECTOR - AIRCRAFT CERTIFICATIONTRANSPORT CANADA

NOTE: Revised text is indicated by a black vertical line.Insert latest revision pages; dispose of superseded pages.

B October 6, 2000

Page 291: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL GeneralSUPPLEMENT Information

BHT-206A-FMS-18

GENERAL INFORMATION

The Bell Snow Particle Separator Kits, No. 206-706-201-17 or206-706-200-9, consist of the particle separator, bleed air tubing andhose, electrical cable and the required hardware to complete theinstallation.

October 6, 2000 i/ii

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TC APPROVED 206A FLIGHT MANUAL Section 1SUPPLEMENT

BHT-206A-FMS-18

Section 1

TEMPERATURE OPERATING LIMIT

Maximum is 80°F (26.7°C) with Snow Particle Separator installed.

Refer to Dust Particle Separator Supplement (BHT-206A-FMS-19) forWeight Limitations and Performance Charts at OAT of 80°F (26.7°C) andabove.

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed andballast readjusted, if necessary, to return empty weight cg withinallowable limits.

TYPE OF OPERATION

The Deflector Kit (BHT-206A-FMS-24) and the Engine (Automatic)Re-Ignition System (BHT-206A-FMS-25) shall be installed inconjunction with Snow Particle Separator Kit when conductingoperations in falling and/or blowing snow and the following limitsapply:

1. Take-off is prohibited with any snow or ice present in the inlet orplenum areas.

*O 2. Ground operations and hover time is limited to 20 minutestotal duration per occurrence. Ground operations at idle power(twist grip at idle) shall not exceed five (5) minutes. If five (5)minutes idle power time limit is exceeded or ground and hover. operations exceed 20 minutes total, helicopter shall be shut downand inspected per Section 2, EXTERIOR CHECK.

NOTE

Particle separator is more efficient at 100% rpm andhover power than at idle.

October 6, 2000 1

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Section 1 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

TYPE OF OPERATION (Cont)

3. Flight operations are prohibited when visibility in falling and/orblowing snow is less than one-half (1/2) statute mile.

OPTIONAL EQUIPMENT LIMITATIONUse basic helicopter performance data when Particle Separator isremoved and the engine air intake screen is reinstalled.

The Deflector Baffles shall be removed if the Snow Particle Separatoris removed.

The Particle Separator and Deflector Kits shall be removed from thehelicopter when the Water-Alcohol kit is installed and operative.

2 October 6, 2000

Page 294: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 2SUPPLEMENT

BHT-206A-FMS-18

Section 2EXTERIOR CHECK

BEFORE EACH FLIGHT WHEN OPERATING IN SNOWCONDITIONS

Immediately before each flight, thoroughly check cabin roof,transmission cowling, deflector baffles and engine air intake areas. Allareas checked must be clean and free of accumulated snow, slush andice before each flight.

Check engine air plenum chamber through the plexiglass windows oneach side of the inlet cowling for snow, slush or ice, paying particularattention to the firewalls, rear face of the Snow Particle Separator,bottom corners and flow vanes. Clean thoroughly before each flight.

ENGINE SHUTDOWN

Engine inlet covers must be installed whenever the helicopter is parkedoutside and shall be removed prior to flight.

AFTER EXITING HELICOPTER

WARNING

FAILURE TO INSTALL ENGINE INLETCOVERS COULD ALLOW FALLING/BLOWINGSNOW TO ENTER THE PARTICLESEPARATOR PLENUM.

Install protective covers (engine inlet, exhaust, and pitot tube) duringany exposure to falling and/or blowing snow during non-engineoperation.

October 6, 2000 3

Page 295: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 2SUPPLEMENT

BHT-206A-FMS-1 8

CENTER OF GRAVITY vs GROSS WEIGHT

HIGH SKIDAND

FLOAT LANDING GEAR

3000

2900 2900 LBS MAX.

2800

2600

2400

2200 LATERAL C. G. LIMITS4.0" RIGHT

0 LONGITUDINAL LATERAL C. G. LIMITSOctober 3.0" LEFT

2000

1800

1600

1400 -

105 106 107 108 109 110 111 112 113 114 115 116

LONGITUDINAL CENTER OF GRAVITY. FUSELAGE STA

4 October 6, 2000

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TC APPROVED 206A FLIGHT MANUAL Section 2SUPPLEMENT

BHT-206A-FMS-18

CENTER OF GRAVITY vs GROSS WEIGHT

STANDARD

SKID LANDING GEAR

I I3000 LBS MAX. 112.1

3000

2800

2600

0 2400

1600

1400

105 106 107 108 109 110 111 112 113 114 115 116

October 6, 2000 5

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Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

Sction_ 3With the particle separator kits, the maximum power available isslightly less than the obtainable with a standard inlet, when operatingat TOT limit. The helicopter performance is, therefore, also less with theparticle separator kits installed. This power loss is caused by anincreased pressure drop in the inlet, and the compressor bleed air usedto purge the particle separator.

Performance charts with the particle separator installed are providedin this section for the clean, float, high skid and external cargoconfigurations.

With Deflector Baffles installed, reduce resulting Power Check charttorque by 3% to determine minimum torque available at hover.

6 October 6, 2000

Page 298: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING IN GROUND EFFECTTAKEOFF POWER WITH SNOW PARTICLE SEPARATOR INSTALLED

50 TO -25°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 2.0 FT (0.6 METERS) ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 290 LBS (132 kg) LESS

. 16,000 FT. DEN. ALT

AREA A

October 6,200206706-119

October 6, 2000 9

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BHT-206A-FMS-18

HOVER CEILING OUT OF GROUND EFFECTTAKEOFF POWER WITH SNOW PARTICLE SEPARATOR INSTALLED

5' TO 27°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 40 FT (12.2 METERS) ENGINE RPM 100%

16,000 FT. DEN. ALT

AREAA

GROSS WEIGHT 206706-116

10 October 6, 2000

Page 300: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING OUT OF GROUND EFFECTTAKEOFF POWER WITH SNOW PARTICLE SEPARATOR INSTALLED

5° TO -25°CGENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 40 FT (12.2 METERS) ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 260 LBS 1118 kg) LESS

16,000 FT. DEN. ALT-

-30 -10 10 20 24 28 32 LB 100OATC --.- C

91 10 1 12 13 14 Kgx 100GROSS WEIGHT

206 706-117

October 6, 2000 11October 6, 2000 11

Page 301: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING IN GROUND EFFECTMAX. CONTINUOUS POWER WITH SNOW PARTICLE SEPARATOR INSTALLED

TO -25°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 2.0 FT (0.6 METERS) ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 390 LBS (177 kg) LESS

16,000 FT. DEN. ALT

AREA A

-30 -20-10 0 10 16 20 24 28 32 LB x 100

7 8 9 10 1 12 13 14 Kg x 100GROSS WEIGHT 206706.121

12 October 6, 2000

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BHT-206A-FMS-18

HOVER CEILING IN GROUND EFFECTMAX. CONTINUOUS POWER WITH SNOW PARTICLE SEPARATOR INSTALLED

50 TO 27°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 2.0 FT (0.6 METERS) ENGINE RPM 100%

16.000 FT. DEN. ALT

10 0 20 30 40 16 20 24 28 32 LB x 100

7 8 9 10 11 12 3 14 Kgx 100GROSS WEIGHT 2067061201

October 6, 2000 13

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BHT-206A-FMS-18

HOVER CEILING OUT OF GROUND EFFECTMAX. CONTINUOUS POWER WITH SNOW PARTICLE SEPARATOR INSTALLED

50 TO -250 C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 40 FT (12.2 METERS) ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 320 LBS (145 kg) LESS

16.000 FT. DEN. ALT

GROSS WEIGHT

14 October 6, 2000

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TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING OUT OF GROUND EFFECTMAX. CONTINUOUS POWER WITH SNOW PARTICLE SEPARATOR INSTALLED

50 TO 27°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 40 FT (12.2 METERS) ENGINE RPM 100%

- 16.000 FT. DEN. ALT-

) 10 20 30 40 16 20 24 28 32 LB x 100OAT -C

7 8 9 10 11 12 13 14Kgx100GROSS WEIGHT

206706-123

October 6, 2000 15

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BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMTAKE-OFF POWER

ANTI-ICE OFFSNOW PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTSGROSS WEIGHT 2000 LB ENGINE RPM 100%

20,000

RATE OF CLIMB -FT./MIN

16 October 6, 2000

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BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMTAKE-OFF POWER

ANTI-ICE OFFSNOW PARTICLE SEPARATOR INSTALLED

Veal 55 MPH - 47 KNOTSGROSS WEIGHT 2300 LB ENGINE RPM 100%

16.000

400 800 000 1200 1600 2000 2400 2800 3200

October 6, 2000 17

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BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMTAKE-OFF POWER

ANTI-ICE OFF

SNOW PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTSGROSS WEIGHT 2600 LB ENGINE RPM 100%

0 400 800 1200 1600 2000 2400 2800 3200

RATE OF CLIPB- FT./MIN.

18 October 6, 2000

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BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMTAKE-OFF POWER

ANTI-ICE OFFSNOW PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTSGROSS WEIGHT 2900 LB ENGINE RPM 100%

20,000

8.000- -

16.000

6000

October 6, 2000 19

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Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMTAKE-OFF POWER

ANTI-ICE OFFSNOW PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTSGROSS WEIGHT 3000 LB ENGINE RPM 100%

20,000

16,00018,000

4.00

0 200 400 600 800 1000 1200 1400 1600

RATE OF CLIMB. FT./MIN.

20 October 6, 200020 October 6, 2000

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BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMMAXIMUM CONTINUOUS POWER

ANTI-ICE OFFSNOW PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTSGROSS WEIGHT 2000 LB ENGINE RPM 100%

0 400 800 1200 1600 2000 2400 2800 3200

RATE OF CLIMB FT./MIN.

October 6, 2000 21

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BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMMAXIMUM CONTINUOUS POWER

ANTI-ICE OFFSNOW PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTSGROSS WEIGHT 2300 LB ENGINE RPM 100%

20,00016.000 -

18.000

16.000

14.000

2000

0 400 800 1200 1600 2000 2400 2800 3200

RATE OF CLIMB -FT./MIN.

22 October 6, 2000

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TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMMAXIMUM CONTINUOUS POWER

ANTI-ICE OFFSNOW PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTSGROSS WEIGHT 2600 LB ENGINE RPM 100%

2000

RATE OF CLIMB . FT./MIN.

October 6, 2000 23

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Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMMAXIMUM CONTINUOUS POWER

ANTI-ICE OFF

SNOW PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTS

GROSS WEIGHT 2900 LB ENGINE RPM 100%

0 200 400 600 800 1000 1200 1400 1600

RATE OF CLIMB -FT./MIN.

24 October 6, 2000

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BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMMAXIMUM CONTINUOUS POWER

ANTI-ICE OFFSNOW PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTSGROSS WEIGHT 3000 LB ENGINE RPM 100%

2 0 ,000

18.000

16.000

14.000

12.000-

10.000

6000

4000

2000

0 200 400 600 800 1000 1200 1400 1600

RATE OF CLIMB- FT./MIN.

October 6, 2000 25

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Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-1 8

RATE OF CLIMB-MAXIMUMTAKE-OFF POWER

ANTI-ICE ONSNOW PARTICLE SEPARATOR INSTALLED

Veal 55 MPH - 47 KNOTSGROSS WEIGHT 2000 LB ENGINE RPM 100%

20.000

14.000

12.000

2000

26 October 6, 2000

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TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMTAKE-OFF POWER

ANTI-ICE ONSNOW PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTSGROSS WEIGHT 2300 LB ENGINE RPM 100%

16,000

14.000

--

1000 -

8000

4000

2000

0 400 800 1200 1600 2000 2400 2800 3200

RATEOFCLIMB FT./MIN.

October 6, 2000 27

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BHT-206A-FMS-1 8

RATE OF CLIMB-MAXIMUMTAKE-OFF POWER

ANTI-ICE ONSNOW PARTICLE SEPARATOR INSTALLED

Veal 55 MPH - 47 KNOTSGROSS WEIGHT 2600 LB ENGINE RPM 100%

20,000

16.000

14.000

6000

4000

2000

0 400 800 1200 1600 2000 2400 2800 3200

RATE OF CLIMB -FT./MIN.

28 October 6, 2000

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TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMTAKE-OFF POWER

ANTI-ICE ONSNOW PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTSGROSS WEIGHT 2900 LB ENGINE RPM 100%

20.000

16,000

14,000

8000

RATE OF CLIMB -FT./MIN.

October 6, 2000 29October 6, 2000 29

Page 319: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMTAKE-OFF POWER

ANTI-ICE ONSNOW PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTSGROSS WEIGHT 3000 LB ENGINE RPM 100%

RATE OF CLIMB FT./MIN.

30 October 6, 200030 October 6, 2000

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BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMMAXIMUM CONTINUOUS POWER

ANTI-ICE ONSNOW PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTSGROSS WEIGHT 2000 LB ENGINE RPM 100%

18.000

16.000

12,000

0 400 800 1200 1600 2000 2400 2800 3200

RATE OF CLIMB -FT/MIN.

October 6, 2000 31

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Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMMAXIMUM CONTINUOUS POWER

ANTI-ICE ONSNOW PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTSGROSS WEIGHT 2300 LB ENGINE RPM 100%

20.000

18.000

16.000

14.000

12.000

10.4000

800 1200 1600 2000 2400 2800---

RATE OF CLIMB -FT./MIN.

32 October 6, 2000

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TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-1 8

RATE OF CLIMB-MAXIMUMMAXIMUM CONTINUOUS POWER

ANTI-ICE ONSNOW PARTICLE SEPARATOR INSTALLED

Veal 55 MPH - 47 KNOTSGROSS WEIGHT 2600 LB ENGINE RPM 100%

20.000

16.000

14.000

12.000

0 200 400 600 800 1000 1200 1400 1600

RATE OF CLIMB -FT./MIN.

October 6, 2000 33

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Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMMAXIMUM CONTINUOUS POWER

ANTI-ICE ONSNOW PARTICLE SEPARATOR INSTALLED

Veal 55 MPH - 47 KNOTSGROSS WEIGHT 2900 LB ENGINE RPM 100%

18.000

16.000

14.000

8000

6000

2000

0 200 400 600 800 1000 1200 1400 1600

RATE OF CLIMB FT./MIN

34 October 6, 2000

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TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-18

RATE OF CLIMB-MAXIMUMMAXIMUM CONTINUOUS POWER

ANTI-ICE ONSNOW PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTSGROSS WEIGHT 3000 LB ENGINE RPM 100%

20,000

18.000

16.000

12.000

10.000

4000

2000

0 200 400 600 800 1000 1200 1400 1600

RATE OF CLIMB.- FT./MIN.

October 6, 2000 35

Page 325: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING IN GROUND EFFECTTAKEOFF POWER 5° TO -25°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT: LOW SKID GEAR 4.0 FT ENGINE RPM 100%

(1.2 METERS)HIGH SKID GEAR 3.0 FT (0.9 METERS)

WITH ANTI-ICE ON GROSS WEIGHT IS 310 LBS (141 kg) LESS

SNOW PARTICLE SEPARATOR WITH CARGO HOOK

16.000 FT. DEN. ALT

AREA

-25

-15

AREA A

G.W. ABOVE 2900 LB (1315.4 kg)WITH EXTERNAL CARGO ONLY

-30-20-10 0 10 20 24 28 32 36LB 100

OAT C 9 10 11 12 13 14 15 16Kgx 100GROSS WEIGHT

206706-124A

36 October 6, 2000

Page 326: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING IN GROUND EFFECTTAKEOFF POWER 5° TO 27°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT: LOW SKID GEAR 4.0 FT ENGINE RPM 100%

(1.2 METERS)HIGH SKID GEAR 3.0 FT (0.9 METERS)

SNOW PARTICLE SEPARATOR WITH CARGO HOOK

16.000 FT. DEN. ALT-

09 10 11 12 13 14 15 16 Kg x 100GROSS WEIGHT

October 6,2000 37

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Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING OUT OF GROUND EFFECTTAKEOFF POWER 5° TO -25°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 40 FT (12.2 METERS) ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 260 LBS (118 kg) LESS

SNOW PARTICLE SEPARATOR WITH CARGO HOOK

16000 FT. DEN. ALT

(1360.5 kg) FOREXTERNAL CARGO ONLY

-30 -20-10 0 10 20 24 28 32 36 LBx 100

OAT ~ °C9 10 11 12 13 14 15 16Kgx100

GROSS WEIGHT 206706-135

38 October 6, 2000

Page 328: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING OUT OF GROUND EFFECTTAKEOFF POWER 5° TO 27°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 40FT (12.2 METERS) ENGINE RPM 100%

SNOW PARTICLE SEPARATOR WITH CARGO HOOK

16.000 FT. DEN. ALT

AREAA

EXTERNAL CARGO ONLY

0 10 20 30 40 20 24 28 32 36 LB x 100

OAT ~ C10 11 12 13 14 15 16Kgx100

GROSS WEIGHT 206706134

October 6, 2000 39

Page 329: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING IN GROUND EFFECTMAX. CONTINUOUS POWER 5° TO -25OC

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT: LOW SKID GEAR 4.0 FT ENGINE RPM 100%

(1.2 METERS)HIGH SKID GEAR 3.0 FT (0.9 METERS)

WITH ANTI-ICE ON GROSS WEIGHT IS 370 LBS (168 kg) LESS

SNOW PARTICLE SEPARATOR WITH CARGO HOOK

-16.000 FT. DEN. ALT

WITH EXTERNAL CARGO ONLY

-30-20-10 0 10 20 24 28 32 36 LB x 100

9 10 11 12 13 14 15 16Kgx100GROSS WEIGHT 206706133A

40 October 6, 2000

Page 330: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING IN GROUND EFFECTMAX. CONTINUOUS POWER 5° TO 27°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT: LOWSKIDGEAR4.0FT ENGINE RPM 100%

(1.2 METERS)HIGH SKID GEAR 3.0 FT (0.9 METERS)

SNOW PARTICLE SEPARATOR WITH CARGO HOOK

16.000 FT. DEN. ALT

GROSS WEIGHT

October 6, 2000 41

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Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING OUT OF GROUND EFFECTMAX. CONTINUOUS POWER 5° TO -25°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 40 FT 12.2 METERS) ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 320 LBS 1145 kg) LESS

SNOW PARTICLE SEPARATOR WITH CARGO HOOK

-16,000 FT. DEN. ALT

/

G.W. ABOVE 3000 LBS(1360.5 kg) FOREXTERNAL CARGO ONLY

OAT-- C7 8 9 10 11 12 13 14 Kg x 100

GROSS WEIGHT 206706-131

October 6, 2001

42 October 6, 2000

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TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING OUT OF GROUND EFFECTMAX. CONTINUOUS POWER 5

° TO 27°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 40 FT (12.2 METERS) ENGINE RPM 100%

SNOW PARTICLE SEPARATOR WITH CARGO HOOK

16,000 FT. DEN. ALT

G.W. ABOVE 3000 LBS(1360.5 kg) FOREXTERNAL CARGO ONLY

0 10 20 30 40 16 20 24 28 32 LB x 100

OAT ~ °C7 8 9 10 11 12 13 14Kg 100

GROSS WEIGHT206706-130

October 6, 2000 43

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Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING IN GROUND EFFECTTAKEOFF POWER 5° TO -25°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 3.0 FT 10.9 METERS) ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 310 LBS (141 kg) LESS

SNOW PARTICLE SEPARATOR WITH HIGH SKID GEAR

16.000 FT. DEN. ALT

AREA A9 10 11 12 13 14Kgx100GROSS WEIGHT

206706 129

44 October 6, 2000

Page 334: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING IN GROUND EFFECTTAKEOFF POWER 5° TO 27°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 3.0 FT (0.9 METERS) ENGINE RPM 100%

SNOW PARTICLE SEPARATOR WITH HIGH SKID GEAR

16,000 FT. DEN. ALT

AREAA

0 10 20 30 40 20 24 28 32 LB x 100

9 10 11 12 13 14 Kgx 100GROSS WEIGHT 206706-128

October 6, 2000 45

Page 335: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING IN GROUND EFFECTMAX. CONTINUOUS POWER 5° TO -25°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 3.0 FT (0.9 METERS) ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 370 LBS (168 kg) LESS

SNOW PARTICLE SEPARATOR WITH HIGH SKID GEAR

, 16.000 FT. DEN. ALT

AREA A

-30-20-10 0 10 20 24 28 32LB x 100

9 10 11 12 13 14Kgx100GROSS WEIGHT 206706-127

46 October 6, 2000

Page 336: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING IN GROUND EFFECTMAX. CONTINUOUS POWER 5° TO 27°C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 3.0 FT (0.9 METERS) ENGINE RPM 100%

SNOW PARTICLE SEPARATOR WITH HIGH SKID GEAR

16.000 FT. DEN ALT

AREA A

0 10 20 30 40 16 20 24 28 32 LB x 100

OAT- -COAT - C 8 9 10 11 12 13 14Kgx100

GROSS WEIGHT 206706-1 26October 6, 2000 47/48

Page 337: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-18

POWER CHECK CHART

SNOW PARTICLE SEPARATOR INSTALLED

ANTI-ICE OFF ZERO AIRSPEEDGENERATOR OFF ENGINE RPM 100%

OUTSIDE AIR TEMPERTURE PERCENT TORQUE

October 6, 2000 7

Page 338: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-18

HOVER CEILING IN GROUND EFFECTTAKEOFF POWER WITH SNOW PARTICLE SEPARATOR INSTALLED

50 TO 270 C

GENERATOR 22.3 AMPS ANTI-ICE OFFSKID HEIGHT 2.0 FT (0.6 METERS) ENGINE RPM 100%

16,000 FT. DEN. ALT

OAT - 9C 10 11 12 13 14 Kgx100

GROSS WEIGHT206706-118

8 October 6, 2000

Page 339: Bell 206A - Flight Manual

BHT-206A-FMS-19

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-200-l 1 206-706-20 1 - 19

DUST PARTICLE SEPARATOR

FAA APPROVED JULY 23, 197O

This supplement shall be attached to Model 206A Flight Manual when 206-706-201-19 or 206-706-200- 11 Dust Particle Separator Kit has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

A Subsldiary of Textron Inc

POST OFFICE BOX 462 l FORT WORTH, TEXAS 76101

23 JULY 1970 REVISION 4 - 25 NOVEMBER 1985 1

Page 340: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

LOG OF REVISIONS

NO. DATE

Basic. . . . . . . . .23 Jul 70 1 . . . . . . . . . . . 04 Sep 70 2.. . . . . . . . . .12 Mar 71 3 . . . . . . . . . . . 18 Oct 71 4 . . . . . . . . . . . 25 Nov 85

NO. DATE

APPROVED: .

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

2 Rev. 4

Page 341: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Log of Pages

LOG OF PAGES

REVISION PAGES NO.

I-26.. . . . . . . . . . . .4

PAGES REVISION

NO.

Rev. 4 3

Page 342: Bell 206A - Flight Manual

Introduction

I BHT-206A-FMS-19

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

INTRODUCTION

The Bell Particle Separator Kits, Nos. 206-706-201-19 and 206-706-200-11 protect the engine against the ingestion of sand, dust and other foreign debris, with a minimum power loss. The separator when installed will permit flight operations to be conducted in less than desirable environmental operating conditions. The separator consists of a grouping of tube assemblies arranged in parallel and fixed between two aluminum sheets and is located forward of the . engine air inlet. Each tube assembly consists of a vortex tube, vortex generator and outlet tube. Foreign particles entering each tube assembly are separated by the swirling action of the air passing through the vortex generators. This airflow, called scavenge flow, carries the foreign particles into the scavenge chamber to the ejection boxes to be purged overboard by using engine bleed air and thereby allows only the remaining cleaned air to enter the engine. The kit consists of the particle separator, bleed air tubing and hose, electrical cable and the required hardware to complete the installation.

4 Rev. 4

Page 343: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

WEIGHT LIMITATIONS

STANDARD SKID LANDING GEAR

Maximum approved gross weight 2900 pounds.

HIGH SKID AND FLOAT LANDING GEAR

Maximum approved gross weight 2850 pounds.

TEMPERATURE OPERATING LIMIT

Minimum - 80°F (26.7°C) with Dust Particle Separator installed.

Refer to Snow Particle Separator Supplement for temperatures below 80°F (26.7°C).

PLACARDS

ALLOWABLE GROSS WEIGHT AUX EQUIP. KIT - DUST PART. SEPARATOR STD. SKID GEAR 2900 LBS HIGH SKID GEAR & FLOATS 2850 LBS

Rev. 4 5

Page 344: Bell 206A - Flight Manual

Section 1 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight CG within allowable limits.

TYPE OF OPERATION

The particle separator can be removed and the engine air intake screen reinstalled to attain basic helicopter performance.

Refer to Snow Particle Separator Supplement when flight operations are conducted in falling snow.

The Particle Separator SHALL BE REMOVED from the helicopter when the Water-Alcohol kit is installed and operative.

6 Rev. 4

Page 345: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

CENTER OF GRAVITY vs GROSS WEIGHT

STANDARD

SKID LANDING GEAR

8

2600

2400

2200

1800

1600

105 106 107 108 109 110 111 112 113 114 115 116

LONGITUDINAL CENTER OF GRAVITY. FUSELAGE STA

Rev. 4 7

Page 346: Bell 206A - Flight Manual

Section 1 206A FLIGHT MANUAL

BHT-206A-FMS-19

FAA APPROVED SUPPLEMENT

CENTER OF GRAVITY vs GROSS WEIGHT HIGH SKID

AND FLOAT LANDING GEAR

2900

2850 2800

2600

2400

w

2200

4

W 2000

1800

1600

1400

105 106 107 108 109 110 111 112 113 114 115 116

LONGITUDINAL CENTER OF GRAVITY. FUSELAGE STA

8 Rev. 4

Page 347: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Sections 2 & 3

BHT-206A-FMS-19

No change from basic Flight Manual.

With the particle separator kit, the maximum power available is slightly less than that obtainable with a standard inlet, when operating at TOT limit. The helicopter performance is, therefore, also less with the particle separator kit installed. This power loss is caused by an increased pressure drop in the inlet, and the compressor bleed air used to purge the particle separator.

Performance charts with the particle separator installed are provided in this section for the clean, float, high skid and external cargo configurations.

Rev. 4 9

Page 348: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL, FAA APPROVED SUPPLEMENT

BHT-206A-FMS-19

ANTI-ICE OFF GENERATOROFF

POWER CHECK CHART

DUST ‘PARTICLE SEPARATOR INSTALLED

ZERO AIRSPEED ENGINE RPM 100%

10 Rev. 4

Page 349: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

HOVERING CEILING IN GROUND EFFECT TAKE-OFF POWER

ANTI-ICE OFF DUST PARTICLE SEPARATOR INSTALLED

SKID HEIGHT 2 FT ENGINE RPM 100%

2000

0

1400 1600 1800 2000 2200 2400 2600 2600 3000

GROSS WElGHT POUNDS

Rev.4 11

Page 350: Bell 206A - Flight Manual

Section 3

HT-206A-FMS-19

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

HOVERING CEILING OUT OF GROUND EFFECT

TAKE-OFF POWER ANTI-ICE OFF

DUST PARTICLE SEPARATOR INSTALLED

ENGINE RPM 100%

1

Page 351: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS- 19

HOVERING CEILING IN GROUND EFFECT

MAXIMUM CONTINUOUS POWER ANTI-ICE OFF

DUST PARTICLE SEPARATOR INSTALLED

HEIGHT 2 FT ENGINE RPM 100%

16.000

6000

6000

Y

1.00 1600 1800 2000 2200 2400 2600 2800 3000

GROSS WEIGHT. POUNDS

Rev. 4 13

Page 352: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

HOVERING CEILING OUT OF GROUND EFFECT

MAXIMUM CONTINUOUS POWER ANTI-ICE OFF

DUST PARTICLE SEPARATOR INSTALLED

ENGINE RPM 100%

Page 353: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

RATE OF CLIMB-MAXIMUM TAKE-OFF POWER

ANTI-ICE OFF DUST PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTS GROSS WEIGHT 2000 LB ENGINE RPM 100%

20,000

16.000

16.000

14.000

12.000

10.000

8000

6000

4000

2000

Rev. 4 15

Page 354: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

-

RATE OF CLIMB-MAXIMUM TAKE-OFF POWER

ANTI-ICE OFF DUST PARTICLE SEPARATOR INSTALLED

GROSS WEIGHT 2300 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100%

0 400 800 1200 1600 2000 2400 2800 3200

16 Rev. 4

Page 355: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-19

RATE OF CLIMB-MAXIMUM TAKE-OFF POWER

ANTI-ICE OFF DUST PARTICLE SEPARATOR INSTALLED

GROSS WEIGHT 2600 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100%

16.000

6000

6000

0

0 400 600 1200 1600 2000 2400 2600 3200

Rev. 4 17

Page 356: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

HT-206A-FMS-19

RATE OF CLIMB-MAXIMUM I TAKE-OFF POWER

ANTI-ICE OFF I DUST PARTICLE SEPARATOR INSTALLED I

GROSS WEIGHT 2900 LB Vcal 55 MPH - 47 KNOTS ENGINE RPM 100% ,

20.000

18,000

16,000

14.000

6000

6000

4000

-

0 200 400 600 600 1000 1200 1400 1600 I

18 Rev. 4

Page 357: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 3

RATE OF CLIMB-MAXIMUM MAXIMUM CONTINUOUS POWER

ANTI-ICE OFF DUST PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTS GROSS WEIGHT 2000 LB ENGINE RPM 100%

16.000

14.600

12.006

10.000

0000

6000

RATE OF CLIMB - FT./MlN.

Rev. 4 19

Page 358: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

RATE OF CLIMB-MAXIMUM MAXlMUM CONTINUOUS POWER

ANTI-ICE OFF

DUST PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTS GROSS WEIGHT 2300 LB ENGINE RPM 100%

Rev. 4

Page 359: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

RATE OF CLIMB-MAXIMUM MAXIMUM CONTINUOUS POWER

ANTI-ICE OFF DUST PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTS GROSS WEIGHT 2600 LB ENGINE RPM 100% -

20.000

6000

0 0 200 400 600

Rev. 4 21

Page 360: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED

I RATE OF CLIMB-MAXIMUM

MAXIMUM CONTINUOUS POWER ANTI-ICE OFF

DUST PARTICLE SEPARATOR INSTALLED

Vcal 55 MPH - 47 KNOTS GROSS WEIGHT 2900 LB ENGINE RPM 100%

22 Rev. 4

Page 361: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

HOVERING CEILING OUT OF GROUND EFFECT

TAKE-OFF POWER

ANTI-ICE OFF DUST PARTICLE SEPARATOR WITH CARGO HOOK

ENGINE RPM 100%

I800 2000 2200 2400 2600 2600 3000 3200 3400

GROSS WEIGHT -POUNDS

206706-168

Rev. 4 23

Page 362: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED

I SUPPLEMENT

BHT-206A-FMS- 19

HOVERING CEILING OUT OF GROUND EFFECT

MAXIMUM CONTINUOUS POWER

ANTI-ICE OFF DUST PARTICLE SEPARATOR WITH CARGO HOOK

ENGINE RPM 100%

1600 2000 2200 2400 2600 2600 3000 3200 3400

GROSS WEIGHT. POUNDS

24

206 706-166

Rev. 4

Page 363: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-19

HOVERING CEILING

IN GROUND EFFECT TAKE-OFF POWER

ANTI-ICE OFF DUST PARTICLE SEPARATOR INSTALLED

4 FT. SKID HT. WITH STANDARD GEAR ENGINE RPM 100% 3 FT. SKID HT. WITH HIGH-SKID GEAR

6000

0

1400 1600 1800 2000 2200 2400 2600 2800 3000

GROSS WEIGHT - POUNDS

206706-l70A

Rev. 4 25

Page 364: Bell 206A - Flight Manual

I

Section 3 206A FLIGHT MANUAL FAA APPROVED

BHT-206A-FMS-19 SUPPLEMENT

HOVERING CEILING

IN GROUND EFFECT MAXIMUM CONTINUOUS POWER

ANTI-ICE OFF DUST PARTICLE SEPARATOR INSTALLED

4 FT. SKID HT. WITH STANDARD GEAR ENGINE RPM 100% 3 FT. SKID HT. WITH HIGH-SKID GEAR

206170-l

26 Rev. 4

Page 365: Bell 206A - Flight Manual

BELL MODEL 206A JET RANGER.

FLIGHT MANUAL SUPPLEMENT FOR

206-706-319

HEAVY DUTY BATTERY

FAA APPROVED AUGUST 6, 197O

This supplement shall be attached to Model 206A Flight Manual when 206-706-319 Heavy Duty Battery Kit is installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

A Subsldiary of Textron Inc

POST OFFICE BOX 402 l FORT WORTH. TEXAS 76101

6 AUGUST 1970 REVISION 2 - 13 SEPTEMBER 1985

Page 366: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

LOG OF PAGES

REVISION ‘AGES NO.

Title . . . . . . . . . . . . . . . .2 A-B. . . . . . . . . . . . . . .2 i/ii. . . . . . . . . . . . . . . . . .2 1-2.. . . . . . . . . . . . . .2

PAGES REVISION

NO.

Rev. 2 A

Page 367: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL

BHT-206A-FMS-20

FAA APPROVED SUPPLEMENT

LOG OF REVISIONS

NO. DATE

Basic . . . . . . . . . .O6 Aug 70

1 . . . . . . . . . . . . . 12 Mar 71 2 . . . . . . . . . . . . . .13 Sep 85

NO. DATE

APPROVED:

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 2

Page 368: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Introduction

INTRODUCTION

The Bell Heavy Duty Battery Kit, No. 206-706-319 consists of a 22 amp hour battery, battery disconnect, channel, bushing, stiffener, cables, tubes, brackets, and attaching hardware.

Rev. 2 i/ii

Page 369: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight CG to within allowable limits.

LOADING LIMITATIONS

BAGGAGE LOADING LIMITS

Maximum 200 pounds, when Heavy Duty Battery Kit is installed.

PLACARDS

REDUCE ALLOWABLE WEIGHT IN BAGGAGE COMPARTMENT BY 50 LBS WHEN AUXILIARY BATTERY IS INSTALLED

(Located on the inboard side of the baggage compartment door)

TYPE OF OPERATION

The Heavy Duty Battery SHALL NOT BE INSTALLED concurrently with the Water-Alcohol kit.

Rev. 2

Page 370: Bell 206A - Flight Manual

Sections 2, 3, & 4 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

Section 2

No change from basic Flight Manual.

No change from basic Flight Manual.

I .

BAGGAGE COMPARTMENT LOADING

Reduce the maximum allowable weight in the baggage compartment by 50 pounds when the Heavy Duty Battery Kit is installed.

2 Rev. 2

Page 371: Bell 206A - Flight Manual

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-330

AUXILIARY BATTERY 13 AMP HOUR

FAA APPROVED JANUARY 8,197 1

This supplement shall be attached to Model 206A Flight Manual when 206-706-330 Auxiliary Battery Kit has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

A SubsdIary of Textron Inc

POST OFFICE BOX 462. FORT WORTH, TEXAS 76101

8 JANUARY 1971 REVISION 2 - 13 SEPTEMBER 1985

Page 372: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

LOG OF PAGES

REVISION PAGES NO.

Title . . . . . . . . . . . . . , . .2 A-B.. . . . . . . . . . . . . .2 i/ii. . . . . . . . . . . . . . . . . .2 l-2.. . . . . . . . . . . . . .2

PAGES REVISION

NO.

Rev. 2 A

Page 373: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-21

LOG OF REVISIONS

NO. DATE

Basic . . . . . . . . . . . 08 Jan 71

1 . . . . . . . . . . . . . 12 Mar 71 2 . . . . . . . . . . . . . 13 Sep 85

NO. DATE

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

I3 . Rev. 2

Page 374: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Introduction

INTRODUCTION

The Bell Auxiliary Battery Kit, No. 206-706-330 consists of a 13 amp hour battery, battery disconnect, channel, bushing, stiffener, cables, tubes, brackets, and attaching hardware.

Rev. 2 i/ii

Page 375: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight CG to within allowable limits.

LOADING LIMITATIONS

BAGGAGE LOADING LIMITS

Maximum 220 pounds, when Auxiliary Battery Kit is installed.

PLACARDS

REDUCE ALLOWABLE WEIGHT IN BAGGAGE COMPARTMENT BY 30 LBS WHEN AUXILIARY BATTERY IS INSTALLED

(Located on the inboard side of the baggage compartment door)

TYPE OF OPERATION

The Auxiliary Battery SHALL NOT BE INSTALLED concurrently with the Water-Alcohol kit.

Rev. 2 1

Page 376: Bell 206A - Flight Manual

Sections 2, 3, & 4 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

Section 2

No change from basic Flight Manual.

No change from basic Flight Manual.

Section 4

BAGGAGE COMPARTMENT LOADING

Reduce the maximum allowable weight in the baggage compartment by 30 pounds when the Auxiliary Battery Kit is installed.

2 Rev. 2

Page 377: Bell 206A - Flight Manual

BHT-206A-FMS-22

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-335

CARGO HOOK 1500 POUND CAPACITY

FAA APPROVED JUNE 16, 1972

This supplement shall be attached to Model 206A Flight Manual when the 206-706-335 Cargo Hook, 1500 Pound Capacity has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this Flight Manual.

Bell I COPYRIGHT NOTICE

COPYRlGNl 1995 BELL @ HELICOPTER TEXTRON INC. AND BELL HELICOPTER TEXTRON, A DIVISION OF TEXTRON CANADA LTD.

ML RIGHTS RESERVED

supplement, consult the basic

A Subsidiary of Textron Inc.

POST OFFICE BOX 482 • FORT WORTH. TEXAS 76101

I

REISSUE - 13 SEPTEMBER 1995

Page 378: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

BHT-206A-FMS-22

LOG OF PAGES

REVISION PAGES NO.

Title ............... .O A-B.. ............ .O i/ii. ................ .O I-12.. ........... .0 13114. ............. .0

PAGES REVISION

NO.

A

Page 379: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-22

LOG OF REVISIONS

NO. DATE NO. DATE

Basic ......... .16 Jun 72 1 ............. 08 Nov 63 2 ............. 13 Sep 85 Reissue. ....... . 13 Sep 95

MANAGER

ROTORCRAFT CERTIFICATION OFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

Page 380: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL

INTRODUCTION

Introduction

BHT-206A-FMS-22

The Bell Cargo Hook Kit, No. 206-706-335, is ONLY APPROVED for installation on helicopters Serial Nos. 584 and subsequent and on prior helicopters with Service Letter No. 206-140 incorporated. The kit consists of a frame and hook assembly, electrical and manual (emergency) release system and attaching hardware. A bungee shock cord is attached to the cargo hook which provides automatic stowing when hook is not in use. OPERATIONS with cargo on the hook SHALL BE CONDUCTED IN ACCORDANCE WITH APPROPRIATE OPERATING RULES.

NOTE

A swivel link is not supplied with the Cargo Hook Kit; however, it is recommended that a link be installed between the suspension cable and the cargo hook.

i/ii

Page 381: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

BHT-206A-FMS-22

WEIGHT LIMITATIONS

Maximum approved gross weight is 3350 pounds.

Loads that result in gross weights above 3000 pounds shall be carried on cargo hook and shall not be imposed on landing gear.

Cargo hook structural loading limit 1500 pounds.

AIRSPEED LIMITATIONS

Vne 91 MPH (78 knots) for gross weights above 3000 pounds.

Extreme caution should be exercised when carrying cargo loads as controllability may be affected, due to the size and shape of the cargo load.

Page 382: Bell 206A - Flight Manual

Section 1 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-22

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight cg within allowable limits.

I 3000 TO 3350 LBS EXTERNAL LOAD P. I CENTER OF GRAVITY vs GROSS WEIGHT

3350

3200 I

3000

2800

TYPE OF OPERATION

Operation of the helicopter with no load on the external cargo hook is authorized under the standard airworthiness certificate without removing the unit from the helicopter.

External cargo operations shall be conducted in accordance with appropriate operating rules for external loads under VFR conditions.

Refer to Particle Separator Supplement when the Particle Separator is installed.

2

Page 383: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 2

BHT-206A-FMS-22 .

FLIGHT PLANNING

Instruct ground personnel to discharge helicopter static electricity, before attaching cargo sling, by touching airframe with a ground wire. If a metal sling is used, hook up ring can be struck against cargo hook to discharge static electricity. If contact has been lost after initial grounding, helicopter should be electrically regrounded and, if possible, contact maintained until hook up is complete.

Instruct ground personnel to check primary load ring and secondary load ring for condition and proper size (table 2-l). Check for correct rigging.

Use of multiple rings, slings, or shackles on the load beam or the primary load ring or use of an oversize secondary load ring is like using a primary load ring smaller than nominal size. This can cause the load to hang up during release.

Failure to comply with these instructions may impair cargo hook ring interface operation, resulting in potential problems.

Instruct ground personnel to check that only one primary ring is captured in the load beam and only one secondary ring with correct cross-section dimension is captured in the primary ring. Additional rings, slings, or shackles shall be attached to the secondary load ring. See figure 2-l.

3

Page 384: Bell 206A - Flight Manual

Section 2

BHT-206A-FMS-22

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

LOAD BEAM

* MAXIMUM PRIMARV RING CROSS-SECTION

* MAXIMUM CROSS-SECTION OF - SECONDARY RING

TO LOAD(S)

* SEE TABLE 2-l

INCORRECT RIGGING

LOAD BEAM

TO LOADISI

I

Figure 2- 1.

206A-FS22-2-l

External load rigging

Page 385: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Sections 2, & 3

BHT-206A-FMS-22

Table 2-l. Ring sizes - cargo hook P/N SP-4232-5

MAXIMUM CROSS PRIMARY RING PRIMARY RING SECTION OF INSIDE DIAMETER CROSS SECTION SECONDARY RING

2.38 to 2.5 in. 1.0 in. 0.438 in. (60.45 to 63.50 mm> (25.4 mm) (11.12 mm)

2.5 to 2.75 in. 1.0 in. 0.625 in. (63.50 to 69.85 mm) (25.4 mm) (15.88 mm)

OPERATION

ACTIVATE circuit by pushing CARGO HOOK circuit breaker - IN.

Engage CARGO switch on cyclic control stick, to release cargo.

EMERGENCY RELEASE

Pull mechanical manual release control HANDLE to drop cargo in the event of an electrical failure.

5

Page 386: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-22

Page 387: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-22

HOVER CEILING IN GROUND EFFECT TAKEOFF POWER 5° TO 37.8°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT: LOW SKID GEAR 4.0 FT ENGINE RPM 100%

(1.2 METERS) HIGH SKID GEAR 3.0 FT (0.9 METERS)

x 100 OAT-°C

I I 10

I I 9 11 12

Page 388: Bell 206A - Flight Manual

Section 3

BHT-206A-FMS-22

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

8

Page 389: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-22

HOVER CEILING OUT OF GROUND EFFECT TAKEOFF POWER 5° TO 37.8°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 40 FT (12.2 METERS) ENGINE RPM 100%

10 20 30 40 20 24 28 32 OAT-°C

9

Page 390: Bell 206A - Flight Manual

Section 3

BHT-206A-FMS-22

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

HOVER CEILING IN GROUND EFFECT MAX. CONTINUOUS POWER 5° TO -25°C

GENERATOR 22.3 AMPS SKID HEIGHT: LOW SKID GEAR 4.0 FT

(1.2 METERS)

ANTI-ICE OFF ENGINE RPM 100%

HIGH SKID GEAR 3.0 FT (0.9 METERS) WITH ANTI-ICE ON GROSS WEIGHT IS 330 LBS (150 kg) LESS

OAT-°C

GROSS WEIGHT 206706.144A

10

Page 391: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-22

HOVER CEILING IN GROUND EFFECT MAX. CONTINUOUS POWER 5° TO 37.8°C

GENERATOR 22.3 AMPS SKID HEIGHT: LOW SKID GEAR 4.0 FT

(1.2 METERS) HIGH SKID GEAR 3.0 FT IO.9 METERS)

ANTI-ICE OFF ENGINE RPM 100%

i i i i

G.W. ABOVE 2900 LB (1316.4 kg)

6 OAT-°C LB

I x 100

x 100

GROSS WEIGHT 204706-145A

11

Page 392: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-22

HOVER CEILING OUT OF GROUND EFFECT MAX. CONTINUOUS POWER 5° TO -25°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 40 FT (12.2 METERS) ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 310 LBS (141 kg) LESS

OAT-°C LB x 100

Kg x 100 206706.146

12

Page 393: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL SUPPLEMENT

Section 3

BHT-206A-FMS-22

HOVER CEILING OUT OF GROUND EFFECT MAX. CONTINUOUS POWER 5° TO 37.8°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 40 FT (12.2 METERS) ENGINE RPM 100%

LB

OAT-°C

x 100

GROSS WEIGHT Kg x 100 206706.14

13/14

Page 394: Bell 206A - Flight Manual

BHT-206A-FMS-23

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-010

EMERGENCY FLOTATION ON HIGH-SKID GEAR

WITH PREFLIGHT SYSTEM TEST FEATURE

FAA APPROVED JULY 28, 1972

This supplement shall be attached to Model 206A Flight Manual when the 206-706-010 Emergency Flotation on High Skid Gear with Preflight System Test Feature has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

A Subsidiary of Textron Inc

POST OFFICE BOX 462 l FORT WORTH, TEXAS 76101

28 JULY 1972 REVISION 2 - 13 SEPTEMBER 1985

Page 395: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

LOG OF PAGES

REVISION PAGES NO.

Title . . . . . . . . . . . . . . . .2 A-B.. . . . . . . . . . . . . .2 i/ii. . . . . . . . . . . . . . . . . .2 l-10 . . . . . . . . . . . . . . 2

PAGES REVISION

NO.

Rev. 2 A

Page 396: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-23

LOG OF REVISIONS

NO. DATE

Basic. . . . . . . . . . .28 Jul 72 1 . . . . . . . . . . . . . 08 Nov 83 2 . . . . . . . . . . . . . 13 Sep 85

NO. DATE

APPROVED:

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 2

Page 397: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Introduction

INTRODUCTION

The Bell Emergency Flotation on High Skid Gear Kit No. 206-706-010, consists of a high-skid landing gear, emergency floats attached to the main skid panels, inflation system, navigation lights, and attaching hardware. Installation of this kit permits operation over land or water. Float inflation time is approximately 5 seconds.

NOTE

On Serial Numbers 4 through 153, Service Instruction No. 206-36 (Landing Gear Support Doublers) must be accomplished prior to installation of Kit.

Rev. 2 i/ii

Page 398: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

WEIGHT LIMITATIONS

Maximum approved gross weight is 2900 pounds.

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight cg within allowable limits.

TYPE OF OPERATION

Operation with the emergency floats inflated is limited to flight to a servicing facility for repacking and recharging the system.

The floats and covers must be installed for all flight operations.

Flight operations over land or water are approved.

Accomplish, daily, PREFLIGHT FLOAT SYSTEM CHECK prior to performing over water operations.

Refer to Particle Separator -Supplement when the Particle Separator is installed.

Rev. 2 1

Page 399: Bell 206A - Flight Manual

Section 1 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

AIRSPEED LIMITATIONS

Floats stowed, covers installed - Same as basic helicopter.

Maximum inflated airspeed - 100 MPH (87 knots).

Maximum inflated airspeed with one or both aft doors off - 60 MPH (52 knots).

Maximum airspeed during float inflation - 70 MPH (61 knots).

I PLACARDS

I WHEN FLOTATION EQUIP. IS INSTALLED

(Located on inside of baggage compartment door.)

FLOAT INFLATION ABOVE 70 MPH PROHIBITED (Located on overhead console)

FLOAT ARMING

ABOVE 70 MPH PROHIBITED

(Located on instrument panel)

2 Rev. 2

Page 400: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 2

EXTERIOR CHECK

Floats stowed.

Float covers clean and secured.

Nitrogen bottle - Pressure - 2800 to 2900 psi.

INTERIOR CHECK

PREFLIGHT FLOAT SYSTEM CHECK

Floats manual arm switch - OFF (GUARD CLOSED).

Float power circuit breaker - Check IN.

Float test and armed lights - PUSH TO TEST.

Float test switch - FLOAT TEST position, and HOLD.

Float inflation trigger switch - PULL ON, float test light ON, then release.

Float test switch - RELEASE, test light OUT.

Floats manual arm switch - POWER (GUARD OPEN), float armed light ON, then switch OFF (GUARD CLOSED), light OFF.

Rev. 2 3

Page 401: Bell 206A - Flight Manual

Section 2 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-23

I IN-FLIGHT OPERATIONS

OVER WATER OPERATION

Floats manual arm switch - POWER (GUARD OPEN).

Float armed light - ON.

During flight at altitudes above 500 feet and at airspeed of 70 mph and above the system SHOULD BE DEACTIVATED by positioning the Floats Manual Arm switch in the OFF position (GUARD CLOSED).

Rearm system prior to landing.

OVER LAND OPERATION

Floats manual arm switch - OFF.

LANDING - TOUCHDOWN

RUN-ON LANDINGS on other than a HARD FIRM SURFACE should be exercised with CAUTION, due to the increased ground contact area of the skid panels.

NOTE

TAIL-LOW RUN-ON LANDINGS should be avoided to prevent nosedown pitching.

4 Rev. 2

Page 402: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 2

EMERGENCY PROCEDURES

FLOAT INFLATION PROCEDURE

Maximum inflation airspeed - 70 mph.

Floats manual arm switch - POWER (GUARD OPEN).

Float armed light - ON.

Float inflation trigger switch - PULL ON.

DO NOT inflate floats more than 5000 feet above anticipated landing surface.

AFTER EMERGENCY WATER LANDING

After landing, inspect the aircraft for possible damage.

If malfunction was cause of landing, correct malfunction.

If no damage has occurred to aircraft and malfunction has been corrected, the aircraft can be ferried to the nearest maintenance facility to repack floats and charge system. The ferrying airspeed is restricted to 100 mph with all doors on or to 60 mph with door or doors off.

Rev. 2 5

Page 403: Bell 206A - Flight Manual

Sections 2 & 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-23

ENGINE FAILURE - NIGHT

Establish an autorotative glide at 60 mph, for minimum rate of descent, and turn on landing light.

At 100 feet execute a moderate cyclic flare to reduce airspeed to approximately 30 mph.

Adjust collective and cyclic pitch sufficiently to perform a low speed cushioned touchdown at a slight noseup attitude.

NOTE

Night autorotative touchdown landings have been demonstrated at airspeeds to 35 mph.

I HOVER CEILING

Out-of-ground effect hovering performance is the same as basic helicopter. In-ground-effect hovering performance is shown on the following graphs:

6 Rev. 2

Page 404: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 3 SUPPLEMENT

BHT-206A-FMS-23

Page 405: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-23

8 Rev. 2

Page 406: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-23

HOVER CEILING IN GROUND EFFECT MAX. CONTINUOUS POWER 5° TO -25°C

GENERATOR 22.3 AMPS ANTI-ICE OFF

SKID HEIGHT 3.0 FT (0.9 METERS) ENGINE RPM 100% WITH ANTI-ICE ON GROSS WEIGHT IS 330 LB (150 kg1 LESS

BASIC SHIP WITH HIGH SKID GEAR

OAT-°C 9 10 11 12 13 14 Kg X 100

GROSS WEIGHT 206706.131

Rev. 2 9

Page 407: Bell 206A - Flight Manual

Section 3

BHT-206A-FMS-23

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

HOVER CEILING IN GROUND EFFECT MAX. CONTINUOUS POWER 5° TO 37.8°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 3.0 FT (0.9 METERS) ENGINE RPM 100%

BASIC SHIP WITH HIGH SKID GEAR

I I I I I I I

0 \

/ \\ \\ I

I I

I

GROSS WEIGHT 2067064 39

10 Rev. 2

Page 408: Bell 206A - Flight Manual

BHT-206A-FMS-24

MODEL206A

ROTORCRAFTFLIGHT MANUAL

SUPPLEMENT FOR206-706-136

DEFLECTOR KITCERTIFIED

NOVEMBER 20, 1972

This supplement shall be attached to Model 206AFlight Manual, when 206-706-136 Deflector Kit hasbeen installed.

Information contained herein supplementsinformation of basic Flight Manual. For Limitations,Procedures, and Performance Data not contained inthis supplement, or other applicable supplements,consult basic Flight Manual.

Bell HelicopterA Subsidiary of Textron Inc

POST OFFICE BOX 482 . FORT WORTH, TEXAS 76101

COPYRIGHT NOTICE

COPYRIGHT 2000BELL ® HELICOPTER TEXTRON INC.AND BELL HELICOPTER TEXTRON,A DIVISION OF TEXTRON CANADA LTD.

ALL RIGHTS RESERVED REISSUE - 6 OCTOBER 2000

Page 409: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Log of PagesSUPPLEMENT SUPPLEMENT

BHT-206A-FMS-24

LOG OF PAGES

REVISION REVISIONPAGES NO. PAGES NO.

Title............. 0A- B........... 0i/ii ........... . 01-4 .......... 05/6 ............. 0

October 6, 2000 A

Page 410: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-24

LOG OF TC APPROVED REVISIONS

NO. DATE NO. DATE

Basic ..... 20 Nov 721 ......... 13 Sep 862 .......... 14 Oct 883 ......... 22 Feb 89Reissue .... 06 Oct 00

APPROVED:

CHIEF, FLIGHT TESTFORDIRECTOR - AIRCRAFT CERTIFICATIONTRANSPORT CANADA

NOTE: Revised text is indicated by a black vertical line.Insert latest revision pages; dispose of superseded pages.

B October 6, 2000

Page 411: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL GeneralSUPPLEMENT Information

BHT-206A-FMS-24

GENERAL INFORMATION

The Deflector Kit No. 206-706-136 consists of the Deflector Baffleassemblies, flow vanes, fairing assembly and all required items andhardware to complete the installation.

NOTE

The Deflector Kit is ONLY APPROVED for installation when thehelicopter has the Snow Particle Separator 206-706-200-9 or206-706-201-17 installed.

October 6, 2000 i/ii

Page 412: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 1SUPPLEMENT

BHT-206A-FMS-24

* Section 1TEMPERATURE OPERATING LIMIT

Maximum 80°F (26.7°C) with Deflector Kit installed.

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed andballast readjusted, if necessary, to return weight empty C.G. withinallowable limits.

TYPE OF OPERATION

The Snow Particle Separator Engine Air Induction System(BHT-206A-FMS-18) and Engine (Automatic) Re-ignition System(BHT-206A-FMS-25) shall be installed in conjunction with Deflector Kitwhen conducting operations in falling and/or blowing snow and thefollowing limits apply:

1. Take-off is prohibited with any snow or ice present in the inlet orplenum areas.

2. Ground operations and hover flight time is limited to 20 minutestotal duration per occurrence. Ground operations at idle power(twist grip at idle) shall not exceed five (5) minutes. If five (5)minutes idle power time limit is exceeded or ground and hoveroperations exceed 20 minutes total, helicopter shall be shut downand inspected per Section 2, EXTERIOR CHECKS.

NOTE

Particle separator is more efficient at 100% rpm andhover power than at idle.

3. Flight operations are prohibited when visibility in falling and/orblowing snow is less than one-half (1/2) statute mile.

October 6, 2000 1

Page 413: Bell 206A - Flight Manual

Section 1 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-24

OPTIONAL EQUIPMENT LIMITATIONS

Deflector Baffles shall be removed at OAT of 80°F (26.7°C) and above.Refer to Particle Separator supplement when Deflector Baffles areremoved.

Use basic helicopter performance data when the Particle Separator isremoved and the engine air intake screen is reinstalled.

The Deflector Baffles shall be removed if the Snow Particle Separatoris removed.

The Particle Separator and Deflector Kits shall be removed from thehelicopter when the Water-Alcohol kit is installed and operative.

2 October 6, 2000

Page 414: Bell 206A - Flight Manual

TC APPROVED 206B FLIGHT MANUAL Section 2SUPPLEMENT

BHT-206A-FMS-24

Section 2

EXTERIOR CHECK

BEFORE EACH FLIGHT WHEN OPERATING IN SNOWCONDITIONS

Immediately before each flight, thoroughly check cabin roof,transmission cowling, deflector baffles and engine air intake areas. Allareas checked must be clean and free of accumulated snow, slush andice before each flight.

Check engine air plenum, chamber through the plexiglass windows oneach side of the inlet cowling for snow, slush or ice, paying particularattention to the fire walls, rear face of the Snow Particle Separator,bottom comers and flow vanes. Clean thoroughly before each flight.

ENGINE SHUTDOWN

Engine inlet covers must be installed whenever the helicopter is parkedoutside and shall be removed prior to flight.

AFTER EXITING HELICOPTER

WARNING

FAILURE TO INSTALL ENGINE INLETCOVERS COULD ALLOW FALLING/BLOWINGSNOW TO ENTER THE PARTICLESEPARATOR PLENUM.

Install protective covers (engine inlet, exhaust, and pitot tube) duringany exposure to falling and/or blowing snow during non-engineoperation.

October 6, 2000 3

Page 415: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-24

Section 31Refer to Snow Particle Separator Engine Air Induction System(BHT-206A-FMS-18) for power assurance data.

A chart for Performance Determination is provided to determinewhether or not a performance loss occurs. The chart is used as follows:

Determine the intersection of the desired pressure altitude andambient temperature.

When power condition curve is to the RIGHT of thealtitude/temperature intersection, there is no loss of performancefrom that shown in Snow Particle Separator SupplementPerformance Charts.

When power condition curve is to the LEFT of thealtitude/temperature intersection, hover ceiling is 1000 feet less andrate of climb is 110 ft/min less than that shown in Snow ParticleSeparator Supplement Performance Charts.

EXAMPLE HOVER PERFORMANCE

Find the maximum gross weight for the following conditions:

Pressure altitude 5000 feetAmbient temperature (OAT) 15°CDesired flight condition Takeoff power Anti-ice OFF.Configuration Snow Particle Separator

with Deflector Kit andStandard Skid Gear.

From the Performance Determination Chart it is noted that the powercondition curve is to the left of the altitude/temperature intersection,point B, therefore the hovering ceiling is less by 1000 feet.

Add pressure altitude and loss:

5000 feet, plus 1000 feet = 6000 feet.

From the appropriate lower ceiling in the Snow Particle SeparatorSupplement find the gross weight for 6000 feet and 15°C = 2860 pounds.This is the maximum gross weight at which it is possible to HoverIn-Ground Effect with Takeoff Power, Anti-Ice OFF.

4 October 6, 2000

Page 416: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 3SUPPLEMENT

BHT-206A-FMS-24

DETERMINATIONOF

PERFORMANCE DECREMENTS

ALLISON ENGINE MODEL 250-C18DEFLECTOR KIT WITH PARTICLE SEPARATOR

(A) WHEN POWER CONDITION CURVE IS TO THE RIGHT OF THE ALTITUDE/TEMPERATURE INTERSECTION, THERE IS NO LOSS OF PERFORMANCEFROM THAT SHOWN IN THE SNOW PARTICLE SEPARATOR SUPPLEMENT.

(B) WHEN POWER CONDITION CURVE IS TO THE LEFT OF THE ALTITUDE/TEMPERATURE INTERSECTION, HOVER CEILING IS 1000 FT LESS,AND RATE OF CLIMB IS 110 FT/MIN LESS THAN THAT SHOWN INTHE SNOW PARTICLE SEPARATOR SUPPLEMENT.

10,000

Page 417: Bell 206A - Flight Manual

BHT-206A-FMS-25

MODEL206A

ROTORCRAFTFLIGHT MANUAL

SUPPLEMENT FOR206-706-038

ENGINE(AUTOMATIC)RE-IGNITION

CERTIFIEDDECEMBER 15, 1972

This supplement shall be attached to the Model 206AFlight Manual when 206-706-038, Engine (Automatic)Re-Ignition Kit has been installed.

Information contained herein supplementsinformation of basic Flight Manual. For Limitations,Procedures, and Performance Data not contained inthis supplement, or other applicable supplements,consult the basic Flight Manual.

Bell HelicopterA Subsidiary of Textron Inc.

POST OFFICE BOX 482 FORT WORTH, TEXAS 76101

COPYRIGHT NOTICE

COPYRIGHT 2000BELL ® HELICOPTER TEXTRON INC.AND BELL HELICOPTER TEXTRON,A DIVISION OF TEXTRON CANADA LTD.

ALL RIGHTS RESERVED REISSUE - 6 OCTOBER 2000

Page 418: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Log of PagesSUPPLEMENT

BHT-206A-FMS-25

LOG OF PAGES

REVISION REVISIONPAGES NO. PAGES NO.

Title .................. 0A-B ................ 0i/ii .................... 01- 2. ................ 03/4 ................... 0

October 6, 2000 A

Page 419: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-25

LOG OF TC APPROVED REVISIONS

NO. DATE NO. DATE

Basic ........... 15 Dec 721 ............... 13 Sep 85Reissue ....... 06 Oct 00

APPROVED:

CHIEF, FLIGHT TESTFORDIRECTOR - AIRCRAFT CERTIFICATIONTRANSPORT CANADA

NOTE: Revised text is indicated by a black vertical line.Insert latest revision pages; dispose of superseded pages.

B October 6, 2000

Page 420: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL GeneralSUPPLEMENT Information

BHT-206A-FMS-25

GENERAL INFORMATION

The Engine Relight Kit (206-706-038) when installed will provideengine automatic re-ignition capability in the event of an engineflameout. The re-ignition of the engine is actuated, when the systemis armed, by decay of engine bleed air as a result of the flameout.

October 6, 2000 i/ii

Page 421: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 1SUPPLEMENT

BHT-206A-FMS-25

WEIGHT LIMITATIONS

Actual weight change shall be determined after kit is installed andballast readjusted, if necessary, to return empty weight CG withinallowable limits.

ALTITUDE LIMITATIONS

Do not activate automatic re-ignition system at altitude above 12,000feet Hp.

TYPE OF OPERATIONS

When conducting operations in falling and/or blowing snow, the Engine(Automatic) Re-Ignition System shall be installed in conjunction witheither of the following kit(s):

1. Particle Separator Engine Air Induction System(BHT-206A-FMS-18) and Deflector System (BHT-206A-FMS-24).

. Or

2. Snow Winterization Air Induction System (BHT-206A-FMS-11).

Engine (Automatic) Re-Ignition System shall be ARMED when conductingoperations in falling and/or blowing snow below 12,000 feet Hp.

October 6, 2000 1

Page 422: Bell 206A - Flight Manual

Section 2 206A FLIGHT MANUAL TC APPROVEDSUPPLEMENT

BHT-206A-FMS-25

NOTE

The engine relight switch has three positions asfollows:

TEST - Up position momentarilyARMED (ON) - Center positionOFF RESET - Lower position

ENGINE PRE-START CHECK

After Rotor Low RPM System Check Add:

Engine Relight Switch - ARMED momentarily, then TEST andhold; check indicator light ON and listen for ignition system ON inapproximately two seconds.

Move switch to OFF RESET; check light out.

BEFORE TAKE-OFF

After Throttle - Full open, add:

Engine Relight Switch - ARMED

NOTE

The system will provide automatic re-ignition as longas switch is in ARMED position.

ENGINE SHUTDOWN

Before Throttle - Flight Idle - etc, add:

Engine Relight Switch - OFF

2 October 6, 2000

Page 423: Bell 206A - Flight Manual

TC APPROVED 206A FLIGHT MANUAL Section 2SUPPLEMENT

BHT-206A-FMS-25

EMERGENCY PROCEDURES

ENGINE AUTOMATIC - RE-IGNITION

1. If automatic re-ignition occurs the indicator light will light.

2. The system is still armed for a new re-ignition when light is ON.

3. To extinguish the light move switch down to OFF/RESETposition, then up to ARMED (ON) position (center).

No change from basic manual.

October 6, 2000 3/4

Page 424: Bell 206A - Flight Manual

BHT-206A-FMS-26

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

206-706-034

DUAL ROTOR BRAKE

FAA APPROVED APRIL 23, 1974

This supplement shall be attached to Model 206A Flight Manual when 206-706-034 Dual Rotor Brake Kit has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

A Subsldlary of Textron Inc

POST OFFICE BOX 462 l FORT WORTH. TEXAS 76101

23 APRIL 1974 REVISION 2 - 3 MARCH 1987

Page 425: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

BHT-206A-FMS-26

LOG OF PAGES

REVISION PAGES NO.

Title . . . . . . . . . . . . . . . .2 A-B. . . . . . . . . . . . . .2 i/ii. . . . . . . . . . . . . . . . . . 1 1 . . . . . . . . . . . . . . . . . . 2 2 . . . . . . . . . . . . . . . . . . 1

PAGES REVISION

NO.

Rev. 2 A

Page 426: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-26

LOG OF REVISIONS

NO. DATE NO. DATE

Basic.. . . . . . . . . .23Apr74 1 . . . . . . . . . . . . . 13Sep85 2 . . . . . . . . . . . . . . 3 Mar 87

APPROVED:

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 2

Page 427: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Introduction

BHT-206A-FMS-26

INTRODUCTION

The Bell dual Rotor Brake System, No. 206-706-034, consists of a brake disc, dual brake assembly, master cylinder, hose assemblies, tube assemblies, operating handle and the required fittings and hardware to complete the installation. The rotor brake system when installed will permit rapid deceleration of the rotor after engine shutdown.

Rev. 1 i/ii

Page 428: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Sections 1 & 2

BHT-206A-FMS-26

PLACARDS

ENGAGE ROTOR BRAKE BETWEEN 38% & 30% ROTOR RPM.

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight CG to within allowable limits.

Section 2

ENGINE PRESTART CHECK

Rotor brake handle - UP and LATCHED.

ENGINE SHUTDOWN

Avoid rapid engagement of rotor brake if helicopter is on ice or other slippery or loose surface to prevent rotation of helicopter.

Apply rotor brake between 38% and 30% rotor RPM.

Rev. 2 1

Page 429: Bell 206A - Flight Manual

Section 3

BHT-206A-FMS-26

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

Section 3

No change from basic Flight Manual.

2 Rev. 1

Page 430: Bell 206A - Flight Manual

BHT-206A-FMS-27

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

LOUDHAILER

SUPPLEMENTAL TYPE CERTIFICATE NO. SH1683SW

FAA APPROVED JUNE 21, 1974

This supplement shall be attached to Model 206A Flight Manual when Loudhailer Equipment has been installed.

_

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

POST OFFICE BOX 482. FORT WORTH. TEXAS 76101

21 JUNE 1974 REVISION 1 - 13 SEPTEMBER 1985

Page 431: Bell 206A - Flight Manual

I\.--

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Pages

BHT-206A-FMS-27

LOG OF PAGES

REVISION ‘AGES NO.

Title . . . . . . . . . . . . . . . .1 4-B.. . . . . . . . . . . . . .1 /ii.. . . . . . . . . . . . . . . . .1 l-4.. . . . . . . . . . . . . .1

PAGES REVISION

NO.

Rev. 1 A

Page 432: Bell 206A - Flight Manual

Log of Revisions 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

I BHT-206A-FMS-27

LOG OF REVISIONS

NO. DATE

Basic. . . . . . . . . . .21 Jun 74

1 . . . . . . . . . . . . . 13 Sep 85

NO. DATE

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

B Rev. 1

Page 433: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Introduction

BHT-206A-FMS-27

-- INTRODUCTION

The LOUDHAILER when installed in accordance with STC No. SH 1683SW will permit the helicopter crew to direct ground personnel while remaining airborne.. The kit contains two speakers, amplifier, power light, switches, microphone and the necessary hardware to complete the installation.

Rev. 1 i/ii

Page 434: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

BHT-206A-FMS-27

AIRSPEED LIMITATIONS

Vne 140 MPH (122 knots) sea level to 5000 feet. Decrease Vne 4.0 MPH (3.5 knots) per 1000 feet above 5000 feet.

ELECTRICAL LOADING LIMITATIONS

All electrical equipment being operated shall not result in a loadmeter reading in excess of 0.7 electrical loading.

PLACARD

- With LOUDHAILER SPEAKERS INSTALLED the Vne is 140 MPH (122 knots).

CENTER OF GRAVITY LIMITS

Actual weight change shall be determined after equipment is installed and ballast readjusted, if necessary, to return empty weight C.G. to within allowable limits.

Rev. 1 1

Page 435: Bell 206A - Flight Manual

Section 1 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-27

--

TYPE OF OPERATION

The helicopter must be equipped with the 206-706-010 High-Skid Landing Gear, 206-706-010 High-Skid Gear with Emergency Flotation or the 206-706-031 Hi-Skid Landing Gear - Tubular Type when the LOUDHAILER (STC No. SH 1683SW) equipment is installed.

The LOUDHAILER is approved for installation in the helicopter (by STC No. SH 1683SW) for use in directing ground personnel. The LOUDHAILER is also approved for installation in conjunction with the NIGHT SUN SEARCHLIGHT

The LOUDHAILER (STC No. SH 1683SW) configuration of the helicopter permits its use as a five place aircraft limited to DAY or NIGHT VFR non-icing conditions.

h

2 Rev. 1

Page 436: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 2

BHT-206A-FMS-27

Section 2

NORMAL PROCEDURES ,

LOUDHAILER SYSTEM - GROUND FUNCTIONAL CHECK

AMPLIFIER CHECK

Battery Switch - ON.

Circuit Breaker - Check IN.

Power Light - PRESS, LIGHT-ON, RELEASE, LIGHT-OUT.

Power Switch - ON and power indicator light ON.

Power Switch - OFF/REMOTE position.

Gain Control Switch - ROTATE to 4-REM position.

REMOTE CONTROL FUNCTIONAL CHECK

Gain Control Switch - OFF position.

Power Switch - ON, indicator light ON. -

Microphone - Speak into mike and slowly rotate gain control until output meter indicator is in approximately midposition. (This will be the gain setting for in-flight use.)

Power Switch - OFF

Rev. 1 3

Page 437: Bell 206A - Flight Manual

Sections 2 & 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-27

IN FLIGHT LOUDHAILER OPERATION

Remote Control Power Switch - ON, light ON.

Microphone - Speak into mike (adjust gain if required).

Remote Control Power Switch - OFF to deactivate system.

No change from basic Flight Manual.

4 Rev. 1

Page 438: Bell 206A - Flight Manual

BHT-206A-FMS-28

BELL MODEL 206A JET RANGER

FLIGHT MANUAL SUPPLEMENT FOR

LIGHTWEIGHT EMERGENCY FLOTATION

LANDING GEAR 206-706-2 11

APPROVED JUNE 26, 1984

This supplement shall be attached to the 206A Flight Manual when the Lightweight Emergency Flotation Landing Gear has been installed. ’

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

Bell A Subsidiary of Textron Inc

POST OFFICE BOX 482. FORT WORTH, TEXAS 76101

26 JUNE 1984 REVISION 1 - 15 JANUARY 1987

Page 439: Bell 206A - Flight Manual

Log of Pages 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-28

LOG OF PAGES

REVISION REVISION PAGES NO. PAGES NO.

l-3 . . . . . . . . . . . . . . .1 4 . . . . . . . . . . . . . . . . . . . 0 5 . . . . . . . . . . . . . . . . . . . 1 6 . . . . . . . . . . . . . . . . . . . 0 7 .1 8-16................0

-

2 Rev. 1

Page 440: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Log of Revisions

BHT-206A-FMS-28

LOG OF REVISIONS

NO. DATE

Original. . . .26 Jun 84 1 . . . . . . . . . . 15 Jan 87

NO. DATE

APPROVED:

AIRCRAFT CERTIFICATION DIVISION FEDERAL AVIATION ADMINISTRATION DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

Rev. 1 3

Page 441: Bell 206A - Flight Manual

Introduction

BHT-206A-FMS-28

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

INTRODUCTION

The Lightweight Emergency Float, Kit No. 206-706-211, consists of a highskid landing gear, emergency floats attached to the main skid panels, inflation system, navigation lights, and attaching hardware. Installation of this kit permits operation over land or water. Float inflation time is approximately 5 seconds.

4

Page 442: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1 ,

BHT-206A-FMS-28

TYPE OF OPERATION

Operation with the pop-out floats inflated is limited to a flight to a servicing facility for repacking and recharging the system. Amphibious operations are not approved.

The floats and covers must be installed and ground handling wheels removed for all flight operations.

Accomplish preflight float system check daily prior to performing over water operations.

Flight operations requiring use of the external hoist are PROHIBITED and the system SHALL BE DEACTIVATED when the floats are installed unless Cable Guard kit 206-706-214 is installed. If Cable Guard kit is installed, hoist cable and hook shall be stowed prior to float inflation. I

AIRSPEED LIMITATIONS

FLOATS STOWED

Floats stowed, covers installed - Same as basic helicopter.

Doors ON or OFF in any combination - Same as basic helicopter.

FLOATS INFLATED

Maximum inflation airspeed - 60 mph (52 knots) IAS.

Rev. 1 5

Page 443: Bell 206A - Flight Manual

Section 1 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-28

AIRSPEED LIMITATIONS (Cont)

During the inflation cycle undesirable pitching will occur at airspeeds above 60 mph (52 knots) IAS.

Maximum allowable airspeed, floats inflated - 80 mph (69 knots) IAS.

Maximum AUTOROTATION airspeed, floats inflated - 70 mph (60 knots) IAS.

RATE OF CLIMB LIMITATIONS

Maximum rate of climb with floats inflated is 1000 feet per minute.

WEIGHT LIMITATIONS

Maximum internal gross weight is 2900 pounds.

CENTER OF GRAVITY LIMITS

Actual weight changes shall be determined after kit is installed and ballast readjusted, if necessary, to return empty weight CG to within allowable limits. Refer to Center of Gravity vs Weight Empty Chart in Maintenance Manual.

6

Page 444: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 1

PLACARDS

FLOAT ARMlNG/lNFLATlON

ABOVE 60 MPH

PROHIBITED

MAXIMUM ALLOWABLE AIRSPEED

FLOATS INFLATED - 80 MPH

(69 KNOTS) IAS

MAXIMUM AUTOROTATION

AIRSPEED, FLOATS INFLATED -

70 MPH (60 KNOTS) IAS

r

BHT-206A-FMS-28

FLOAT

INFLATION

I HOISTCABLE AND HOOK MUST BE

STOWED PRIOR TO FLOAT INFLATION I

2700

2600

2500

2400

2300

2200

2100

2000

1900

1800

CYLINDER PRESSURE LIMITS EMERGENCY FLOTATION

AMBIENT AIR TEMPERATURE -°C

206-073-858-101

206706-171

Rev. 1 7

Page 445: Bell 206A - Flight Manual

Section 2

BHT-206A-FMS-26

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

Section 2

NORMAL PROCEDURES

EXTERIOR CHECK

Floats stowed.

Nitrogen lines - Check for condition and evidence of leakage.

Float covers clean and secured.

Float inflation cylinder - Check for proper temperature and altitude vs inflation pressure. Refer to placard on cylinder. Check cannon plug for security.

INTERIOR CHECK

PREFLIGHT FLOAT SYSTEM CHECK

FLOAT MANUAL ARM switch - OFF (guard closed).

FLOAT POWER circuit breaker - Check IN.

FLOAT TEST and ARMED lights - PUSH TO TEST.

FLOAT TEST switch - FLOAT TEST position, and hold.

FLOAT INFLATION trigger switch - PULL ON, float test light ON, then release.

8

Page 446: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 2

BHT-206A-FMS-28

PREFLIGHT FLOAT SYSTEM CHECK (Cont)

FLOAT TEST switch - RELEASE, test light OUT.

FLOAT MANUAL ARM switch - POWER (guard open), FLOAT ARMED light ON, then switch OFF (guard closed), light OFF.

IN-FLIGHT OPERATIONS

OVER WATER OPERATION

FLOAT MANUAL ARM switch - POWER (guard open).

FLOAT ARMED light - ON.

During flight at altitudes above 500 feet and at airspeeds of 60 mph (52 knots) IAS and above, the system SHOULD BE DEACTIVATED by positioning the FLOAT MANUAL ARM switch in the OFF position (GUARD CLOSED).

Rearm system prior to landing.

OVER LAND OPERATION

FLOAT MANUAL ARM switch - OFF.

Page 447: Bell 206A - Flight Manual

Section 2

BHT-206A-FMS-28

206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

DESCENT AND LANDING - FLOATS STOWED

If the CG is aft of station 112.7, practice of autorotational touchdowns should be avoided due. to nosedown pitching.

Run-on landings on other than a hard, firm surface should be exercised with caution.

NOTE

Tail-low, run-on landings should be avoided to prevent nosedown pitching.

10

Page 448: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 2

BHT-206A-FMS-28

EMERGENCY PROCEDURES

FLOAT INFLATION PROCEDURE

Reduce airspeed below maximum inflation airspeed - 60 mph (52 knots) IAS.

Establish autorotation or low power descent at approximately 500 feet per minute.

FLOAT MANUAL ARM switch - POWER (guard open).

FLOAT ARMED light - ON.

FLOAT INFLATION trigger switch - PULL ON.

DO NOT inflate floats more than 2000 feet above anticipated landing surface.

NOTE

During flight with floats inflated, a random bumping of the skid gear crosstube against the landing gear saddles will occur. Reducing airspeed will reduce bumping.

11

Page 449: Bell 206A - Flight Manual

Sections 2 & 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-28

AFTER EMERGENCY WATER LANDING

After landing, inspect the helicopter for possible damage. If malfunction was cause of landing, correct malfunction.

If no damage has occurred to helicopter and malfunction has been corrected, the helicopter can be ferried to the nearest maintenance facility to repack floats and charge system. The ferrying airspeed is restricted to 80 mph (69 knots) IAS. The maximum rate of climb while ferrying is 1000 feet per minute.

HOVERING CEILING - FLOATS STOWED

Out-of-ground-effect hovering performance is the same as basic helicopter. In-ground-effect hovering performance is shown on the following charts:

12

Page 450: Bell 206A - Flight Manual

FAA APPROVED 206A FLIGHT MANUAL Section 3 SUPPLEMENT

BHT-206A-FMS-28

HOVER CEILING IN GROUND EFFECT TAKEOFF POWER T0 -25°C

Page 451: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-28

HOVER CEILING IN GROUND EFFECT TAKEOFF POWER 5o TO 37.8°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 3.0 FT (0.9 METERS) ENGINE RPM 100%

BASIC SHIP WITH HIGH SKID GEAR

LB x 100 OAT-°C

GROSS WEIGHT 206706-137

14

Page 452: Bell 206A - Flight Manual

FAA APPROVED SUPPLEMENT

206A FLIGHT MANUAL Section 3

BHT-206A-FMS-28

HOVER CEILING IN GROUND EFFECT MAX. CONTINUOUS POWER 5° TO -25°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 3.0 FT (0.9 METERS) ENGINE RPM 100%

WITH ANTI-ICE ON GROSS WEIGHT IS 330 LB (150 kg) LESS

BASIC SHIP WITH HIGH SKID GEAR

I I I I I

6 -

-30-20-10 0 10

OAT-°C

GROSS WEIGHT 206706-138

Page 453: Bell 206A - Flight Manual

Section 3 206A FLIGHT MANUAL FAA APPROVED SUPPLEMENT

BHT-206A-FMS-28

HOVER CEILING IN GROUND EFFECT MAX. CONTINUOUS POWER 5° TO 37.8°C

GENERATOR 22.3 AMPS ANTI-ICE OFF SKID HEIGHT 3.0 FT (0.9 METERS) ENGINE RPM 100%

BASIC SHIP WITH HIGH SKID GEAR

10 20 30 40 20 24 26 OAT-°C

100 GROSS WEIGHT

206706-139

16

Page 454: Bell 206A - Flight Manual

BHT-206A-FMS-29

FLIGHT MANUAL SUPPLEMENT

BELL MODEL 206A JET RANGER

FUEL PRESSURE GAGE 206-075-676

FAA APPROVED 10 DECEMBER 1984

This supplement shall be attached to the Model 206A Jet Ranger Flight Manual when the 206-075-676 Fuel Pressure Gage has been installed.

The information contained herein supplements the information of the basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult the basic Flight Manual.

Bell Helicopter A Subsidlary of Textron Inc

POST OFFICE BOX 462 l FORT WORTH. TEXAS 76101

Page 455: Bell 206A - Flight Manual

BHT-206A-FMS-29 FAA APPROVED

Page LOG OF PAGES

Revision No.

Title ............... .O 1-2 ............... .0 3/4 ............... .0

LOG OF REVISIONS

No. Date

Original . . . . . . . . . . 10 December 1984

AIRCRAFT CERTIFICATION DIVISION ! FEDERAL AVIATION ADMINISTRATION

DEPARTMENT OF TRANSPORTATION SOUTHWEST REGION, FORT WORTH, TEXAS

NOTE: Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superceded pages.

1

Page 456: Bell 206A - Flight Manual

BHT-206A-FMS-29 FAA APPROVED

INTRODUCTION

This supplement provides an extension of the minimum temperature limit for the use of Type A, A-1, or JP-5 fuel to -32°C (-25°F).

Also presented are the minimum fuel pressure and instrument marking requirements when operating with these fuels at temperatures below -18°C (0°F).

2

Page 457: Bell 206A - Flight Manual

BHT-206A-FMS-29 FAA APPROVED

POWER PLANT LIMITATIONS

FUEL LIMITATIONS

Turbine fuel ASTM D-1655, Type A or A-l, or MIL-T-5624, Grade JP-5 limited to ambient temperatures of -32” C (-25°F) and above

FUEL PRESSURE LIMITS

Minimum for use of Type A. A-1, or JP-5 fuel, PSI or any mixture containing one of these, at ambient temperature below -18°C (0°F)

INSTRUMENT MARKINGS

LOADMETER

Page 458: Bell 206A - Flight Manual

BHT-206A-FMS-30

ROTORCRAFT FLIGHT MANUAL

SUPPLEMENT

IMPACT RESISTANT FUEL CELL KIT 206-704-720

CERTIFIED 6 JANUARY 1994

This supplement shall be attached to Model 206A Flight Manual when the 206-704-720 Impact Resistant Fuel Cell Kit has been installed

Information contained herein supplements information of basic Flight Manual. For Limitations, Procedures, and Performance Data not contained in this supplement, consult basic Flight Manual.

COPYRIGHT NOTICE COPYRIGHT 1994

AND BELL HELICOPTER TEXTRON. A DIVISION OF TEXTRON CANADA LTD.

ALL RIGHTS RESERVED

Page 459: Bell 206A - Flight Manual

BHT-206A-FMS-30

NOTICE PAGE

PROPRIETARY RIGHTS NOTICE

Manufacturer’s Data portion of this supplement is proprietary to Bell Helicopter Textron, Inc. Disclosure, reproduction, or use of these data for any purpose other than helicopter operation is forbidden without prior written authorization from Bell Helicopter Textron, Inc.

.

.

Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center

Bell Helicopter Textron P. 0. Box 482

Fort Worth, Texas 761050482

Page 460: Bell 206A - Flight Manual

Original . . . . . . . . . . 0 . . . . . . . . . . . . . .06 JAN 94

BHT-206A-FMS-30 . ,

LOG OF REVISIONS

LOG OF PAGES

REVISION REVISION

PAGE NO. PAGE NO.

FLIGHT MANUAL MANUFACTURER’S DATA

Title - NP . . ............................ 0 3-4.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0 A-B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0 5/6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0 ½ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages.

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Page 461: Bell 206A - Flight Manual

BHT-206A-FM-30

LOG OF APPROVED REVISIONS

ORIGINAL . . . . . . . 0 . . . . . . . . . . . . . .06 JAN 94

APPROVED:

ROTORCRAFT CERTIFICATION OFFICE FEDERAL AVIATION ADMINISTRATION FT. WORTH, TX 76193-0170

FAA APPROVED

Page 462: Bell 206A - Flight Manual

FAA APPROVED BHT-206A-FMS-30

WEIGHT/CENTER OF if necessary, to return empty weight CG to

GRAVITY within allowable limits.

Actual weight change shall be determined after kit is installed and ballast readjusted,

No change from basic manual.

No change from basic manual.

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BHT-206A-FMS-30

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Section 4

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MANUFACTURER’S DATA

Fuel loading tables are provided for helicopters equipped with the 206-704-720 Impact Resistant Fuel Cell kit.

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Page 464: Bell 206A - Flight Manual
Page 465: Bell 206A - Flight Manual

BHT-206A-FMS-30

Section 5 MANUFACTURER’S DATA

FUEL SYSTEM SERVICING Usable capacity: 72 U S gallons (272 liters)

Total capacity: 73 U S gallons (276 liters)

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