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BHT-407-FM-1 ROTORCRAFT FLIGHT MANUAL

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Bell 407 - Flight Manual POH*For enthusiast purposes only, always refer to the up-to-date manual in the aircraft*

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Page 1: Bell 407 - Flight Manual, POH

BHT-407-FM-1

ROTORCRAFTFLIGHT MANUAL

Page 2: Bell 407 - Flight Manual, POH

BHT-407-FM-1

COPYRIGHT NOTICE

COPYRIGHT 2005

BELL ® HELICOPTER TEXTRON INC.

AND BELL HELICOPTER TEXTRON

CANADA LTD.

ALL RIGHTS RESERVED

ROTORCRAFTFLIGHT MANUAL

TYPE CERTIFICATE NO. ________

REGISTRATION NO. ______________________ SERIAL NO. ____________________

APPROVED BY DATE ______________________

DIRECTOR — AIRCRAFT CERTIFICATION BRANCHDEPARTMENT OF TRANSPORT

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

U.S. REGISTERED HELICOPTERS ARE APPROVED BY THE FAA IN ACCORDANCE WITH THE PROVISIONS OF 14 CFR SECTION 21.29 ON

THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS

H-92

9 FEBRUARY 1996

23 FEBRUARY 1996

REISSUE — 17 DECEMBER 2002REVISION 4 — 29 JUNE 2005

Page 3: Bell 407 - Flight Manual, POH

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COPYRIGHTCOPYRIGHTBELL ® HELICOPTER TEXTRON INC.® HELICOPTER TEXTRON INC.AND BELLAND BELL HELICOPTER TEXTRON INC.HELICOPTER TEXTRON INC.A DIVISION OF TEXTRON CANADADIVISION OF TEXTRON CANADA LTD.

ALL RIGHTS RESERRIGHTS RESERVED

2002

COPYRIGHT NOTICE

A Subsidiary of Textron Inc.

POST OFFICE BOX 482 FORT WORTH, TEXAS 76101

Bell Helicopter

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Page 4: Bell 407 - Flight Manual, POH

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Page 5: Bell 407 - Flight Manual, POH

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Page 6: Bell 407 - Flight Manual, POH

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Page 7: Bell 407 - Flight Manual, POH

ROTORCRAFTFLIGHT MANUAL

TEMPORARY REVISION FOR THEINCORPORATION OF OIL COOLER BLOWER

INLET DUCTS AND BEARINGAIRFLOW SHIELDS

This Temporary Revision supersedes and replaces in its entirety, TemporaryRevision for Sustained Hover and Vertical Takeoff/Landing Operations withTailwind, TR-9 dated 15 January 2002, when Oil Cooler Blower Inlet Ducts andBearing Airflow Shields have been incorporated. DO NOT incorporate thisTemporary Revision into manual or remove previously issued TR-9, untilmodifications 407-799-057 (Inlet Ducts) and 407-799-055 (Bearing AirflowShields) or ASB 407-02-54 has been accomplished.

Helicopter S/N 53519 and subsequent will have these modificationsincorporated as basic configuration.

Insert these Temporary Revision pages next to like-number pages in the basicFlight Manual.

DO NOT remove existing pages. DO NOT remove temporary pages untilreplacement pages are received or temporary pages are canceled.

NOTE

For tracking purposes, Temporary Revisions are now being numbered. ThisTemporary Revision is issued as TR-10 Revision 1, following previouslyissued Temporary Revisions.

THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS

COPYRIGHTBELL ® HELICOPTER TEXTRON INC.® HELICOPTER TEXTRON INC.AND BELLAND BELL HELICOPTER TEXTRON INC.HELICOPTER TEXTRON INC.A DIVISION OF TEXTRON CANADADIVISION OF TEXTRON CANADA LTD.

ALL RIGHTS RESERRIGHTS RESERVED

2002

COPYRIGHT NOTICE

A Subsidiary of Textron Inc.

POST OFFICE BOX 482 FORT WORTH, TEXAS 76101

Bell Helicopter

BHT-407-FM-1

09 FEBRUARY 1996TEMPORARY REVISION (TR-10) — 15 FEBRUARY 2002

REVISION 1 —25 JULY 2002

Page 8: Bell 407 - Flight Manual, POH

BHT-407-FM-1

LOG OF REVISIONS

Temporary (TR-10).............................15 FEB 02 Revision ...................... 1 .....................25 JUL 02

LOG OF PAGES

REVISION REVISIONNO. NO.PAGE PAGE

Title ...........................................................1A ................................................................1C-D ............................................................1

1-7 ......................................... Temporary (TR-10)2-3 ......................................... Temporary (TR-10)2-5 — 2-6 .............................. Temporary (TR-10)

TEMPORARY REVISION (TR-10) — 15 FEB 2002 A

CHANGED INFORMATION IN THIS TEMPORARY REVISION APPEARS IN BOLD TYPE.ALL OTHER INFORMATION IS OUTLINED.

NOTICE

REVISION 1 — 25 JULY 2002

Page 9: Bell 407 - Flight Manual, POH

BHT-407-FM-1

APPROVED DATE

CHIEF, FLIGHT TESTFORDIRECTOR — AIRCRAFT CERTIFICATIONTRANSPORT CANADA

DATE

LOG OF TC APPROVED REVISIONS

Temporary (TR-10).............................15 FEB 02 Revision ...................... 1 .....................25 JUL 02

TEMPORARY REVISION (TR-10) — 15 FEB 2002 C

CHIEF, FLIGHT TESTFORDIRECTOR — AIRCRAFT CERTIFICATION BRANCHDEPARTMENT OF TRANSPORT

REVISION 1 — 25 JULY 2002

Page 10: Bell 407 - Flight Manual, POH

BHT-407-FM-1

LOG OF FAA APPROVED REVISIONS

Temporary (TR-10) ............................ 22 FEB 02 Revision ..................... 1..................... 25 JUL 02

D TEMPORARY REVISION (TR-10) — 15 FEB 2002REVISION 1 — 25 JULY 2002

Page 11: Bell 407 - Flight Manual, POH

BHT-407-FM-1

The following Warning is not applicable to helicopters on which all kits and customizinginstallations have been qualified and approved by Bell Helicopter.

WARNING

THE HELICOPTER MAY CONTAIN INSTALLATIONS, PARTS, ORPROCESSES CERTIFIED BY PARTIES OTHER THAN BELLHELICOPTER TEXTRON. BELL HELICOPTER CAN NOTCONFIRM THAT SUCH INSTALLATIONS HAVE BEEN FULLYQUALIFIED OR CONFORMED TO BELL HELICOPTER DESIGNCRITERIA. AS A RESULT OF SUCH INSTALLATIONS, BELLHELICOPTER SUPPLIED DATA MAY NOT BE VALIDCONCERNING IN-FLIGHT HANDLING QUALITIES, WEIGHT ANDBALANCE, OR HELICOPTER PERFORMANCE. IF MULTIPLE STCKITS OR SIMILAR INSTALLATIONS ARE INCORPORATED,THERE MAY BE NOT VALID TEST DATA TO QUALIFY THEHELICOPTER AS MODIFIED BY THESE INSTALLATIONS. FORREVISED DATA, CONTACT THE OWNER OF THE INSTALLEDSTC OR THE SUPPLIER FOR THE APPLICABLE APPROVAL OFEACH INSTALLATION.

NP 17 DEC 2002

Additional copies of this publication may be obtained by contacting:Commercial Publication Distribution Center

Bell Helicopter Textron Inc.P. O. Box 482

Fort Worth, Texas 76101-0482

NOTICE PAGE

Page 12: Bell 407 - Flight Manual, POH

BHT-407-FM-1

NOTE

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

LOG OF REVISIONSOriginal........................0 ...................09 FEB 96Revision .....................1 ...................08 MAR 96Revision ......................2 ...................09 MAY 96Revision .....................3 ...................30 JUL 96Revision .....................4 ...................04 NOV 96Revision ......................5 ................... 24 JUN 97Revision ......................6 ................... 03 JUL 98

Revision ...................... 7................... 04 SEP 98Revision ...................... 8................... 17 APR 00Reissue ....................... 0................... 17 DEC 02Revision ...................... 1................... 10 MAR 04Revision ...................... 2................... 29 NOV 04Revision ...................... 3................... 26 APR 05Revision ...................... 4................... 29 JUN 05

LOG OF PAGES

REVISION REVISIONNO. NO.PAGE PAGE

Cover......................................................... 0Title............................................................ 4NP.............................................................. 0A/B............................................................. 4C/D............................................................. 4E/F ............................................................. 4i — ii .......................................................... 0iii/iv ............................................................ 01–1— 1–5 .................................................. 01–6 ............................................................. 31–7 — 1–13 ............................................... 01–14 ........................................................... 31–15 — 1–19 ............................................. 01-20............................................................ 32–1/2–2...................................................... 0

2–3 — 2–5................................................. 02-6 ............................................................. 22-7 — 2-10 ................................................ 02-11 ........................................................... 42-12 — 2-16 .............................................. 02–17/2–18 ................................................. 03–1/3–2 ..................................................... 03–3 — 3–20............................................... 04–1/4–2 ..................................................... 04–3 — 4–50............................................... 04–51 /4–52 ................................................ 05–1 — 5–18............................................... 05–19/5–20 ................................................. 0A–1/A–2 .................................................... 0A–3 — A–4................................................ 2

29 JUN 2005 Rev. 4 A/B

Page 13: Bell 407 - Flight Manual, POH

BHT-407-FM-1

LOG OF TC APPROVED REVISIONS

Original ....................... 0................... 09 FEB 96Revision ..................... 1................... 08 MAR 96Revision...................... 2................... 09 MAY 96Revision...................... 3................... 30 JUL 96Revision...................... 4................... 04 NOV 96Revision...................... 5................... 24 JUN 97Revision...................... 6................... 03 JUL 98

Revision ......................7 ...................04 SEP 98Revision ......................8 ...................17 APR 00Reissue........................0 ...................17 DEC 02Revision ......................1 ...................10 MAR 04Revision ......................2 ...................29 NOV 04Revision ......................3 ...................26 APR 05Revision ......................4 ...................29 JUN 05

29 JUN 2005 Rev. 4 C/D

APPROVED DATE

CHIEF, FLIGHT TESTFORDIRECTOR — AIRCRAFT CERTIFICATIONTRANSPORT CANADA

Page 14: Bell 407 - Flight Manual, POH

BHT-407-FM-1

LOG OF FAA APPROVED REVISIONS

Original ....................... 0....................09 FEB 96Revision ..................... 1....................08 MAR 96Revision...................... 2....................09 MAY 96Revision...................... 3....................30 JUL 96Revision...................... 4....................04 NOV 96Revision...................... 5....................24 JUN 97Revision...................... 6....................18 MAY 99

Revision ......................7 ................... 18 MAY 99Revision ......................8 ................... 05 MAY 00Reissue........................0.................... 24 SEP 03Revision ......................1.................... 11 MAR 04Revision ......................2 ................... 07 DEC 04Revision ......................3 ................... 04 MAY 05Revision ......................4 ....................30 JUN 05

29 JUN 2005 Rev. 4 E/F

Page 15: Bell 407 - Flight Manual, POH

BHT-407-FM-1

GENERAL INFORMATION

ORGANIZATION

This Rotorcraft Flight Manual is divided intofive sections and an appendix as follows:

Sections 1 through 4 contain TransportCanada (TC) approved data necessary tooperate basic helicopter in a safe andefficient manner.

Section 5 contains weight and balance datanecessary for flight planning.

Appendix A contains a list of approvedsupplements for optional equipment, whichshall be used in conjunction with basicFlight Manual when respective optionalequipment kits are installed.

Manufacturer's Data manual (BHT-407-MD-1)contains information to be used inconjunction with Flight Manual.Manufacturer's data manual is divided intofour sections:

TERMINOLOGY

WARNINGS, CAUTIONS, AND NOTES

Warnings, cautions, and notes are usedthroughout this manual to emphasizeimportant and critical instructions asfollows:

WARNING

A N OPER A T IN G P RO C ED UR E,PRACTICE, ETC., WHICH, IF NOTCORRECTLY FOLLOWED, COULDRESULT IN PERSONAL INJURY ORLOSS OF LIFE.

CAUTION

A N OPER A T IN G P RO C ED UR E,PRACTICE, ETC., WHICH IF NOTST R IC TL Y O BS ER VED , C OU L DR ESU L T I N DA M A GE T O O RDESTRUCTION OF EQUIPMENT.

NOTE

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

USE OF PROCEDURAL WORDS

Concept of procedural word usage andintended meaning which has been adheredto in preparing this manual is as follows:

SHALL has been used only whenapplication of a procedure is mandatory.

SHOULD has been used only whenapplication of a procedure is recommended.

Section 1 — LIMITATIONSSection 2 — NORMAL PROCEDURESSection 3 — EMERGENCY AND

MALFUNCTION PROCEDURES

Section 4 — PERFORMANCESection 5 — WEIGHT AND BALANCEAppendix A — OPTIONAL EQUIPMENT

SUPPLEMENTS

Section 1 — SYSTEMS DESCRIPTION

Section 2 — HANDLING AND SERVICING

Section 3 — CONVERSION CHARTS AND TABLES

Section 4 — EXPANDED PERFORMANCE

17 DEC 2002 i

Page 16: Bell 407 - Flight Manual, POH

BHT-407-FM-1

MAY and NEED NOT have been used onlywhen application of a procedure is optional.

WILL has been used only to indicatefuturity, never to indicate a mandatoryprocedure.

ABBREVIATIONS, ACRONYMS ANDPLACARDING

Abbreviations, acronyms and placardingused throughout this manual are defined asfollows:

ADF — Automatic direction finder

AIRCOND

— Air conditioner

A/F — Airframe

ALT — Altimeter

ANTICOLL LT

— Anticollision light

ATT — Attitude

AUTO — Automatic

AUX — Auxiliary

BATT — Battery

BIT — Built in test

BL — Buttock line

BLO — Blower

BRT — Bright

°C — Degrees Celsius

CAUT — Caution

CAUT LT — Caution lights

CG — Center of gravity

CKPT — Cockpit

CM — Centimeter (s)

COMM — Communication

CONT — Control

dBA — Decibel, “A” type filter

DC — Direct current

DG — Directional gyro

DOT — Department of Transport

ECS — Environmental control system

ECU — Engine control unit

ELT — Emergency locator transmitter

ENCDG — Encoding

ENG — Engine

ENGANTI ICE

— Engine anti icing

°F — Degrees Fahrenheit

FADEC — Full authority digital engine control

FS — Fuselage station

FT or ft — Foot, feet

FWD — Forward

GEN — Generator

GOV — Governor

GPS — Global positioning system

GPU — Ground power unit

GW — Gross weight

HD — Density altitude

HG — Inches of mercury

HMU — Hydromechanical unit

Hp — Pressure altitude

HYD — Hydraulic

HV — Height-velocity

ICAO — International Civil Aviation Organization

ICS — Intercommunication system

IFL — Inflate

ii 17 DEC 2002

Page 17: Bell 407 - Flight Manual, POH

BHT-407-FM-1

IGE — In ground effect

IGNTR — Ignitor

IN — Inch(es)

INSTRCHK

— Instrument check

INSTR LT — Instrument light

KCAS — Knots calibrated airspeed

KG or kg — Kilogram(s)

KIAS — Knots indicated airspeed

KTAS — Knots true airspeed

L — Liter(s)

LB(S) or lb(s)

— Pound(s)

LDG LTS — Landing lights

L/FUEL — Left fuel

LT — Light

MAN — Manual

MCP — Maximum continuous power

MD — Manufacturer's Data

MGT — Measured gas temperature

MM or mm

— Millimeter(s)

NAV — Navigation

NG — Gas producer RPM

NP — Power turbine RPM

NR — Rotor RPM

OAT — Outside air temperature

OBS — Omni bearing selector

OGE — Out of ground effect

OVSPD — Overspeed

PARTSEP

— Particle separator

PASS — Passenger(s)

PMA — Permanent Magnetic Alternator

POS LT — Position light

PRESS — Pressure

PSI — Pounds per square inch

PTT — Press to Test

PWR — Power

QTY — Quantity

R/FUEL — Right fuel

RECP — Receptacle

RLY — Relay

RPM — Revolutions per minute

RTR — Rotor

s/w Ver Soft ware version

SEL — Sound exposure level

SHP — Shaft horsepower

SL — Sea level

SPKR — Speaker

Sq — Square

SYS — System

T/R — Tail rotor

TCA — Transport Canada Aviation

TEMP — Temperature

TRQ — Torque

VFR — Visual flight rules

VHF — Very high frequency

VNE — Never exceed velocity

VOR — VHF omnidirectional range

WL — Water line

WARN — Warning

XFR — Transfer

XMSN — Transmission

XPDR — Transponder

17 DEC 2002 iii/iv

Page 18: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 1-1

Section 1LIMITATIONS

111

Paragraph NumberPage

Subject

TABLE OF CONTENTS

INTRODUCTION ......................................................................... 1-1.................... 1-3BASIS OF CERTIFICATION ....................................................... 1-2.................... 1-3TYPES OF OPERATION............................................................. 1-3.................... 1-3

PASSENGERS ...................................................................... 1-3-A................ 1-3CARGO.................................................................................. 1-3-B................ 1-3

FLIGHT CREW ............................................................................ 1-4.................... 1-3CONFIGURATION....................................................................... 1-5.................... 1-3

REQUIRED EQUIPMENT...................................................... 1-5-A................ 1-3 OPTIONAL EQUIPMENT ..................................................... 1-5-B................ 1-4 DOORS REMOVED.............................................................. 1-5-C................ 1-4

WEIGHT AND CENTER OF GRAVITY ....................................... 1-6.................... 1-4WEIGHT................................................................................. 1-6-A................ 1-4CENTER OF GRAVITY ......................................................... 1-6-B................ 1-4

AIRSPEED................................................................................... 1-7.................... 1-4ALTITUDE ................................................................................... 1-8.................... 1-5MANEUVERING .......................................................................... 1-9.................... 1-5

PROHIBITED MANEUVERS................................................. 1-9-A................ 1-5CLIMB AND DESCENT......................................................... 1-9-B................ 1-5SLOPE LANDING ................................................................. 1-9-C................ 1-5

NOT USED .................................................................................. 1-10.................. 1-5AMBIENT TEMPERATURES...................................................... 1-11.................. 1-5ELECTRICAL .............................................................................. 1-12.................. 1-5

GENERATOR ........................................................................ 1-12-A.............. 1-5STARTER .............................................................................. 1-12-B.............. 1-5

POWER PLANT .......................................................................... 1-13.................. 1-5GAS PRODUCER RPM (NG)................................................ 1-13-A.............. 1-6POWER TURBINE RPM (NP) ............................................... 1-13-B.............. 1-6MEASURED GAS TEMPERATURE (MGT) .......................... 1-13-C.............. 1-6ENGINE TORQUE................................................................. 1-13-D.............. 1-6FUEL PRESSURE................................................................. 1-13-E .............. 1-6ENGINE OIL PRESSURE ..................................................... 1-13-F .............. 1-6ENGINE OIL TEMPERATURE.............................................. 1-13-G.............. 1-7

TRANSMISSION ......................................................................... 1-14.................. 1-7TRANSMISSION OIL PRESSURE........................................ 1-14-A.............. 1-7TRANSMISSION OIL TEMPERATURE ................................ 1-14-B.............. 1-7

ROTOR ........................................................................................ 1-15.................. 1-7

Page 19: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

1-2 17 DEC 2002

Paragraph NumberPage

Subject

TABLE OF CONTENTS (CONT)

ROTOR RPM — POWER ON ............................................... 1-15-A.............. 1-7ROTOR RPM — POWER OFF ............................................. 1-15-B.............. 1-7

HYDRAULIC................................................................................ 1-16 ................. 1-7FUEL AND OIL............................................................................ 1-17 ................. 1-7

FUEL ..................................................................................... 1-17-A.............. 1-7OIL......................................................................................... 1-17-B.............. 1-8

ROTOR BRAKE.......................................................................... 1-18 ................. 1-8NOT USED .................................................................................. 1-19 ................. 1-8INSTRUMENT MARKINGS AND PLACARDS........................... 1-20 ................. 1-8

Figure Title Number Number

Page

LIST OF FIGURES

Gross weight longitudinal center of gravity limits ................. 1-1 ................... 1-9Gross weight lateral center of gravity limits ........................... 1-2 .................. 1-11Placards and decals .................................................................. 1-3 .................. 1-13Ambient air temperature limitations ........................................ 1-4 .................. 1-16Instrument markings ................................................................. 1-5 .................. 1-17

Page 20: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 1-3

Section 1LIMITATIONS

11-1. INTRODUCTION

Compliance with l imitat ions sect ion isrequired by appropriate operating rules.Anytime an operating limitation is exceeded,an appropria te entry shal l be made inhelicopter logbook. Entry shall state whichlimit was exceeded, duration of time, extremevalue attained, and any additional informationessential in determining maintenance actionrequired.

In ten t io n a l use o f t ran s i en t l i m i ts i sprohibited.

Torque events shall be recorded. A torqueevent is defined as a takeoff or lift, internal orexternal load (BHT-407-MD-1).

Landings shall be recorded. Run-on landingsshall be recorded separately.

A run-on landing is defined as one wherethe re i s fo r war d g ro u n d t ra ve l o f thehelicopter greater than three feet with theweight on the skids.

1-2. BASIS OF CERTIFICATION

This helicopter is certified under FARs Part 27and 36 , Appendix J. Addit ional ly, i t isapproved under Canadian AirworthinessManual Chapters 516 (ICAO Chapter 11) and527, Sections 1093 (b) (1) (ii) and (iii), 1301-1,1557 (c) (3), 1581 (e) and 1583 (h).

1-3. TYPES OF OPERATION

1-3-A. PASSENGERS

Basic configured helicopter is approved forseven place seating and is certified for land

operation under day or night VFR nonicing

conditions.

1-3-B. CARGO

The maximum allowable cabin deck loadingfor cargo is 75 pounds per square foot (3.7kilograms per 100 square centimeters). Themaximum allowable baggage compartmentdeck loading is 86 pounds per square foot (4.2kilograms per 100 square centimeters) with amaximum allowable weight of 250 pounds(113.4 kilograms). Refer to BHT-407-MD-1 forcargo restraint and tiedown locations.

Cargo must be properly secured by tiedowndevices to prevent the load from shiftingu nd er an t ic i pa ted f l ig h t an d gr ou n doperations. If the mission requires bothpassengers and cargo to be transportedtogether, the cargo must be loaded andsecu r ed s o th a t i t do es n o t ob s t r uc tpassenger access to exits.

1-4. FLIGHT CREW

Minimum flight crew consists of one pilot whoshall operate helicopter from right crew seat.

Left crew seat may be used for an additionalpi lo t when approved dua l contro ls areinstalled.

1-5. CONFIGURATION

1-5-A. REQUIRED EQUIPMENT

A functional flashlight is required for nightflights.

FADEC system software shall be version5.202.

Page 21: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

1-4 17 DEC 2002

1-5-B. OPTIONAL EQUIPMENT

The snow deflector kit (BHT-407-FMS-4) shallbe in s ta l le d wh en co n du ct i ng f l ig h toperations in falling and/or blowing snow.

R efer to ap p ro p r i a te f l i gh t m anu a lsu pp le men t (s ) (F M S) fo r ad d i t io n a llimitations, procedures, and performancedata for optional equipment.

1-5-C. DOORS REMOVED

NOTE

Indicated altitude may be up to 100 feetlower than actual altitude with crewdoor(s) removed.

Flight with any combination of doors removedis approved. With litter door removed, leftpassenger door shall be removed. Refer toAirspeed limitations.

With door(s) removed, determine weightchange and adjust ballast if necessary. Referto Section 5.

NOTE

All unsecured items shall be removedfrom cabin when any door is removed.

1-6. WEIGHT AND CENTER OF GRAVITY

1-6-A. WEIGHT

Maximum approved internal GW for takeoffand landing is 5000 pounds (2268 kilograms).

Minimum GW for flight is 2650 pounds (1202kilograms).

Minimum weight at fuselage station 65.0 is170 pounds (77.1 kilograms).

Maximum approved GW with jettisonableexternal load for takeoff and landings is 6000pounds (2722 kilograms).

1-6-B. CENTER OF GRAVITY

The pilot is responsible for determiningweight and balance to ensure gross weightand center of gravity will remain within limitsthroughout each flight. Refer to Section 5 forloading tables and instructions.

NOTE

Ballast as required to maintain mostforward or most aft CG within GW flightlimits (Figure 1-1). For standardpassenger and fuel loadings,applicable Weight empty center ofgravity chart in BHT-407-MM-1 may beused to determine required ballast.

For longitudinal CG limits refer to Grossweight longitudinal center of gravity limitschart (Figure 1-1).

For lateral CG limits refer to Gross weightlateral center of gravity limits (Figure 1-2).

1-7. AIRSPEED

Basic VNE is 140 KIAS, sea level to 3000 feet

HD. Decrease VNE for ambient conditions inaccordance with AIRSPEED LIMITATIONSplacards and decals (Figure 1-3).

VNE at 93.5 to 100% TORQUE (takeoff power)is 100 KIAS, not to exceed placarded VNE.

VNE is 100 KIAS or placarded VNE, whicheveris less, when takeoff loading is in shaded areaof the Gross weight lateral center of gravitylimits (Figure 1-2).

VNE is 100 KIAS with any door(s) removed, notto exceed placarded VNE.

VNE is 100 KIAS or placarded VNE, whicheveris less for steady state autorotation.

Page 22: Bell 407 - Flight Manual, POH

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Page 23: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 1-5

Maximum allowable airspeed for sidewardand rearward flight or crosswind hover is 35KTAS.

1-8. ALTITUDEMaximum operating altitude is 20,000 feet HDor 20,000 feet HP, whichever is lower.

1-9. MANEUVERING1-9-A. PROHIBITED MANEUVERS

Aerobatic maneuvers are prohibited.

1-9-B. CLIMB AND DESCENT

Maximum rate of climb is 2,000 feet perminute.

1-9-C. SLOPE LANDING

Slope landings are limited to 10° side slopes,10° nose up slope or 5° nose down slope.

1-10. NOT USED

1-11. AMBIENT TEMPERATURESMaximum sea level ambient air temperaturefor operat ion is +51.7°C (+125°F) anddecreases with HP at standard lapse rate of2°C (3.6°F) per 1000 feet to 20,000 feet. Referto Ambient air temperature limitations chart(Figure 1-4).

Min imum ambient a i r temperature foroperation at all altitudes is −40 °C (−40°F).

ENG ANTI ICE shall be ON in visible moisturewhen OAT is below 5°C (40 °F).

1-12. ELECTRICAL1-12-A. GENERATOR

1-12-B. STARTER

NOTE

28 VDC GPU for starting shall be limitedto 500 amps.

1-13. POWER PLANTRolls-Royce model 250-C47B.

NOTE

Intentional use of any power transientis prohibited.

Continuous operation,up to 10,000 feet Hp

0 to 180 Amps

Maximum continuous up to 10,000 feet Hp

180 Amps

Continuous operation,above 10,000 feet Hp

0 to 170 Amps

Maximum continuous above 10,000 feet Hp

170 Amps

Transient, 2 minutes 180 to 300 AmpsTransient, 5 seconds 300 to 400 Amps

External Power Start Battery Start40 seconds ON 60 seconds ON30 seconds OFF 60 seconds OFF40 seconds ON 60 seconds ON30 seconds OFF 60 seconds OFF40 seconds ON 60 seconds ON30 minutes OFF 30 minutes OFF

Page 24: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

1-6 Rev. 3 26 APR 2005

1-13-A. GAS PRODUCER RPM (NG)

1-13-B. POWER TURBINE RPM (NP)

NOTE

ENGINE OVSPD warning light willilluminate when NP versus TORQUE isbetween 102.4% NP at 100% TORQUEand 108.6% NP at 0% TORQUE.

When operating in MANUAL mode NPshould be maintained between 95% and100%.

1-13-C. MEASURED GAS TEMPERATURE (MGT)

GAUGE P/N 407-375-001-101/-103

NOTE

Either MGT gauge may be installed.

GAUGE P/N 407-375-001-105 AND SUB

1-13-D. ENGINE TORQUE

NOTE

Use of takeoff power is limited to 100KIAS, not to exceed placarded VNE.

1-13-E. FUEL PRESSURE

1-13-F. ENGINE OIL PRESSURE

NOTE

When 130 PSI is exceeded during start,operate engine at idle until oil pressuredrops below 130 PSI.

Continuous operation 63 to 105%Maximum continuous operation

105%

Transient, 10 seconds 105.1 to 106%

Avoid continuousoperations

68.4 to 87.1%

Minimum 99%Continuous operation 99 to 100%Maximum continuous 100%Maximum transient, 15 seconds

102.1 to107% NP

Continuous operation 100 to 727°CMaximum continuous 727°CTakeoff, 5 minutes 727 to 779°CMaximum for takeoff 779°CTransient, 12 seconds 780 to 826°CMaximum starting, do not exceed 10 seconds above 826°C or 1 second at 927°C.

927 °C

Continuous operation 100 to 727°CMaximum continuous 727°CTakeoff, 5 minutes 727 to 779°CMaximum for takeoff 779°CTransient, 12 seconds 780 to 905°CMaximum starting, do not exceed 10 seconds above 843°C or 1 second at 927°C.

927°C

Continuous operation 0 to 93.5%Maximum continuous 93.5%Takeoff, 5 minute 93.5 to 100%Transient, 5 seconds 105%

Minimum 8 PSIContinuous operation 8 to 25 PSIMaximum 25 PSI

Minimum below 79% NG 50 PSIMinimum from 79 to 94% NG 90 PSIMinimum above 94% NG 115 PSIMaximum 130 PSIMaximum cold starts only 200 PSI

Page 25: Bell 407 - Flight Manual, POH

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Page 26: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

1-13-G. ENGINE OIL TEMPERATURE

Continuous operation 0 to 107°C

Maximum 107°C

If hovering with a tailwind greater than 10knots at OAT above 37.8°C (100°F),closely monitor engine oil temperature.The oil temperature may be reduced byeither turning into wind, reducing poweror transition to forward flight.

NOTE

Positive temperature indication is whenthe second segment of the trend arc isilluminated.

1-14. TRANSMISSION

TEMPORARY REVISION (TR-10) — 15 FEB 2002 1-7

Page 27: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 1-7

1-13-G. ENGINE OIL TEMPERATURE

NOTE

Positive temperature indication is whenthe second segment of the trend arc isilluminated.

1-14. TRANSMISSION

1-14-A. TRANSMISSION OIL PRESSURE

1-14-B. TRANSMISSION OILTEMPERATURE

1-15. ROTOR

1-15-A. ROTOR RPM — POWER ON

NOTE

When operating in MANUAL mode NRshould be maintained between 95% and100%.

1-15-B. ROTOR RPM — POWER OFF

CAUTION

FO R A U TOR OT A TIV E TR A IN IN GMAINTAIN STEADY STATE NR ABOVE90%.

1-16. HYDRAULIC

Hydraulic fluid MIL-H-5606 may be used at allambient temperatures.

1-17. FUEL AND OIL

1-17-A. FUEL

Fuel conforming to following specificationsmay be used at all ambient temperatures:

ASTM-D-1655, Type B

MIL-T-5624, Grade JP-4 (NATO F-40).

Fuels conforming to following specificationsare limited to ambient temperatures of −32°C(-25°F) and above:

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

MIL-T-5624, Grade JP-5 (NATO F-44)

MIL-T-83133, Grade JP-8 (NATO F-34).

For operations below −32 °C (-25 °F), refer toRolls-Royce Operation and MaintenanceManual for cold weather fuel and blendinginstructions.

Continuous operation 0 to 107°C

Maximum 107°C

Minimum 30 PSI

Continuous operation 40 to 70 PSI

Maximum 70 PSI

Continuous operation 15 to 110°C

Maximum 110°C

Continuous operation 99 to 100%

Maximum continuous 100%

Minimum 85%

Continuous operation 85 to 107%

Maximum 107%

Page 28: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

1-8 17 DEC 2002

1-17-B. OIL

1-17-B-1. OIL − ENGINE

Oil conforming to MIL-L-7808 (NATO O-148),DOD-L-85734 (Turbine oil 555) or MIL-L-23699(N ATO O-156 ) is l i m i ted to am bi en ttemperatures above −40 °C (−40 °F).

NOTE

Refer to Rolls-Royce Operation andMaintenance Manual and BHT-407-MD-1 manual for approved oils and mixingof oils of different brands, types, andmanufacturers.

1-17-B-2. OIL − TRANSMISSION AND TAIL ROTOR GEARBOX

NOTE

It is recommended DOD-L-85734 oil beused in transmission and tail rotorgearbox to maximum extent allowed bytemperature limitations.

Oil conforming to DOD-L-85734 is limited toambient temperatures above −40°C (−40°F).

Oil conforming to MIL-L-7808 (NATO O-148) islimited to ambient temperatures below −18°C(−0°F).

1-18. ROTOR BRAKE

Rotor brake (if installed) application is limitedto ground operation after engine has beenshut down and NR has decreased to 40% orlower.

For emergency stops, apply rotor brake anytime after engine is shut down.

Engine starts with rotor brake engaged areprohibited.

1-19. NOT USED

1-20. INSTRUMENT MARKINGS AND PLACARDS

Refer to Figure 1-3 for Placards and decals.Refer to Figure 1-5 for Instrument markings.

NOTE

Illustrations shown in Figure 1-5 areartist representations and may or maynot depict actual approved instrumentsdue to printing limitations. Instrumentoperating ranges and limits shall agreewith those presented in this section.

Page 29: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 1-9

Figure 1-1. Gross weight longitudinal center of gravity limits (Sheet 1 of 2)

118 119 120 121 122 123 124 125 126 127 128 129 130

FUSELAGE STATION - INCHES

2400

2600

2800

3000

3200

3400

3600

3800

4000

4200

4400

4600

4800

5000

5200

5400

5600

5800

6000

6200

GR

OS

S W

EIG

HT

- P

OU

ND

S

6000

5000

4500

2800

2650

120.5 127.6

119.5

119.0

128.0 129.0

EXTERNAL LOAD ONLY

LONGITUDINAL C.G.

M407_FM-1__FIG_1-1_(1_OF_2).WMF

Page 30: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

1-10 17 DEC 2002

Figure 1-1. Gross weight longitudinal center of gravity limits (Sheet 2 of 2)

3000 3025 3050 3075 3100 3125 3150 3175 3200 3225 3250 3275 3300

FUSELAGE STATION - MILLIMETERS

1100

1200

1300

1400

1500

1600

1700

1800

1900

2000

2100

2200

2300

2400

2500

2600

2700

2800

GR

OS

S W

EIG

HT

- K

ILO

GR

AM

S

LONGITUDINAL C.G.

2268

EXTERNAL LOAD ONLY

3241 3061

2722

3035

2041

1270

1202 3023

3251 3277

M407_FM-1__FIG_1-1_(2_OF_2).WMF

Page 31: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 1-11

Figure 1-2. Gross weight lateral center of gravity limits (Sheet 1 of 2)

-5 -4 -3 -2 -1 0 1 2 3 4 5

BUTTOCK LINE - INCHES

2400

2600

2800

3000

3200

3400

3600

3800

4000

4200

4400

4600

4800

5000

5200

5400

5600

5800

6000

6200

GR

OS

S W

EIG

HT

- P

OU

ND

S

5000

-1.5

LATERAL C.G.

EXTERNAL LOAD ONLY

MAX AIRSPEED 100 KIAS

-0.9 1.4

2.0

-4.0 -2.5 3.0 4.0

3500

2650

3500

6000

EXTERNALLOAD ONLY

MAX AIRSPEED100 KIAS

EXTERNALLOAD ONLY

MAX AIRSPEED100 KIAS

M407_FM-1__FIG_1-2_(1_OF_2).WMF

Page 32: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

1-12 17 DEC 2002

Figure 1-2. Gross weight lateral center of gravity limits (Sheet 2 of 2)

-125 -100 -75 -50 -25 0 25 50 75 100 125

BUTTOCK LINE - MILLIMETERS

1100

1200

1300

1400

1500

1600

1700

1800

1900

2000

2100

2200

2300

2400

2500

2600

2700

2800

GR

OS

S W

EIG

HT

- K

ILO

GR

AM

S

LATERAL C.G.

EXTERNAL LOAD ONLY

MAX AIRSPEED 100 KIAS

EXTERNALLOAD ONLY

MAX AIRSPEED100 KIAS

EXTERNALLOAD ONLY

MAX AIRSPEED100 KIAS

-102 -64 76 102

1588 1588

1202

-39 52

2268

-23 36

2722

M407_FM-1__FIG_1-2_(2_OF_2).WMF

Page 33: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 1-13

Figure 1-3. Placards and decals (Sheet 1 of 3)

Airspeed limits shown are valid only for corresponding altitudes and temperatures. Hatched areas indicate conditions which exceed approved temperature or density altitude limitations.

Location: Between Pilot and Copilot seats

0 2 4 6 8 10 12 14 16 18 2052 13745 139 132 12540 140 133 126 11935 140 135 128 120 11330 140 137 129 122 115 10825 140 138 131 124 116 109 102 9520 140 140 133 125 118 111 103 96 890 140 140 140 132 125 117 110 103 95 88

-25 140 140 140 135 130 125 119 111 104 97 89-40 137 133 128 123 118 114 110 105 101 97 93

PRESSURE ALTITUDE FT x 1000407 AIRSPEED LIMITATIONS - KIAS

OAT °C

MAXIMUM AUTOROTATION VNE 100 KIAS

EMERGENCY PEDALSTOP RELEASE

PULL ONLY MAINT. RESET

REQUIRED

Location: Forward of Overhead Console

M407_FM-1__FIG_1-3_(VNE).WMF

Page 34: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

1-14 Rev. 3 26 APR 2005

Figure 1-3. Placards and decals (Sheet 2 of 3)

FUELFUEL SYSTEM USABLE CAPACITY

BASIC AIRCRAFT 127 U.S. GALLONS - 483 LITERSWITH 407-706-011 AUX KIT 147 U.S. GALLONS = 559 LITERS

SEE FLIGHT MANUAL FOR APPROVED FUELS

AVOID CONT OPS 68.4% TO 87.1% NP

Location: Above fuel filler cap.

THIS HELICOPTER MUST BE OPERATED INCOMPLIANCE WITH THE OPERATING LIMITATIONS

SPECIFIED IN THE APPROVED FLIGHT MANUAL

Location: Bottom and centered on instrument panel.

CARGO MUST BE SECUREDIN ACCORDANCE WITHFLIGHT MANUAL INSTR

Location: Inside of baggage door.

407-FM-1-3-2

DO NOT APPLY ROTOR BRAKEABOVE 40% RPM

Location: Near rotor brake (if installed).

Location: Instrument panel.

Page 35: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 1-15

Figure 1-3. Placards and decals (Sheet 3 of 3)

FADEC SOFTWARE VERSION 5.202WITH DIRECT REVERSION TOMANUAL INSTALLED. REFER TOFLIGHT MANUAL FOR OPERATION

Location: Instrument panel.

Page 36: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

1-16 17 DEC 2002

Figure 1-4. Ambient air temperature limitations

-40 -30 -20 -10 0 10 20 30 40 50 60

AMBIENT AIR TEMPERATURE - °C

0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

18,000

20,000

PR

ES

SU

RE

AL

TIT

UD

E

- F

T

-40 -20 0 20 40 60 80 100 120 140

AMBIENT AIR TEMPERATURE - °F

MIN

IMU

M O

AT

FL

IGH

T L

IMIT

MA

XIM

UM

OA

T

EXAMPLE: AT HP = 7000 FTMAX OAT = 37.8°C (100°F)MIN OAT = - 40°C (- 40°F)

FLIG

HT

LIMIT

MAXIMUM HD FLIGHT LIMIT

M407_FM-1__FIG_1-4.EMF

Page 37: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 1-17

Figure 1-5. Instrument markings (Sheet 1 of 4)

ENGINEENGINE OIOIL PL PRESSURERESSURE

5050 PSIPSI

5050 toto 9090 PSPSII

9090 toto 11115 P5 PSISI

11115 t5 too 130130 PSPSII

130130 PSPSII

200200 PSPSII

ENGINEENGINE OIOIL TL TEMPERAEMPERATURETURE

0 t0 too 107107 CC

107107 CC

MinimumMinimum

OperationOperation belowbelow 79%79% NGNG RPMRPM

ContinuousContinuous operationoperation belowbelow 94%94% NGNG RPRPMM

MaximumMaximum forfor continuouscontinuous operationoperation

MaximumMaximum forfor coldcold ststartart

ContinuousContinuous operationoperation

MaximumMaximum

ContinuousContinuous operationoperation

TRANSMISSIOTRANSMISSION ON OILIL PRESSUREPRESSURE

3030 PSPSII

4040 toto 7070 PSPSII

7070 PSPSII

TRANSMISSIOTRANSMISSION ON OILIL TEMPERATEMPERATURETURE

1515 toto 111010 CC

111010 CC

MinimumMinimum

ContinuousContinuous operationoperation

MaximumMaximum

ContinuousContinuous operationoperation

MaximumMaximum

NGNG (GAS(GAS PRODUCERPRODUCER RPM)RPM)

6363 toto 105%105%

105%105%

106%106%

ContinuousContinuous operationoperation

MaximumMaximum continuouscontinuous operationoperation

MaximumMaximum transient,transient, 1010 secondsseconds

M407_FM-1__FIG_1-5_(1_OF_4).EPS

Page 38: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

1-18 17 DEC 2002

Figure 1-5. Instrument markings (Sheet 2 of 4)

NPNP (POWER(POWER TURBINETURBINE RPM)RPM)

99%99% MinimuMinimum

9999 to 100%100% ContinuousContinuous operatiooperation

100%100% MaximuMaximum cm continuousontinuous

NRNR (ROT(ROTOROR RPM)RPM)

85%85%

85 to 107%107%

107%107%

MinimumMinimum (power(power off)off)

ContinuousContinuous operatiooperation (n (powerpower off)off)

MaximumMaximum (power(power off)off)

M407_FM-1__FIG_1-5_(2_OF_4).EPS

TRQTRQ (TORQUE)ORQUE)

0 t0 to 93.5%93.5%

93.93.5 t5 to 100%100%

100%100%

ContinuousContinuous operatiooperation

5 m5 minutinute te takeoffakeoff rangerange

MaximumMaximum

EitherEither gagegage maymay bebe instinstallealled

MGTMGT (MEASURED(MEASURED GASGAS TEMPERATEMPERATURE)TURE)

100100 to 727727 C

727727 to 779779 C

779779 C

826826 Coror

843843 C

927927 C

ContinuousContinuous operatiooperation

5 m5 minutinute te takeoffakeoff rangerange

MaximumMaximum for takeoffakeoff

BeginningBeginning of 10 secondssecondsrangerange for starting

MaximumMaximum for start andand shutshutdowndown(1 secondsecond maximum)maximum)

PN 407-375-001-105 AND SUB

PN 407-375-001-101/-103

*

*

Page 39: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 1-19

Figure 1-5. Instrument markings (Sheet 3 of 4)

Page 40: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

1-20 Rev. 3 26 APR 2005

Figure 1-5. Instrument markings (Sheet 4 of 4)

407FM_1_0001

DC LOAD

DC LOAD

FUEL PRESSURE

FUEL PRESSURE

* Either gauge may be installed.

* P/N 407-075-024-101

* P/N 407-075-024-103, 407-375-007-105 or 407-375-007-107

170 Amps

0 to 180 Amps

180 Amps

180 Amps

170 Amps

300 Amps

400 Amps

8 PSI

8 PSI

8 to 25 PSI

8 to 25 PSI

25 PSI

25 PSI

Maximum continuous above 10,000 FT Hp

Continuous operation

Maximum

Maximum

Maximum continuous above 10,000 FT Hp

Maximum transient, 2 minutes

Maximum transient, 5 seconds

Continuous operation

Continuous operation

Maximum

Maximum

Minimum

Minimum

VERTICAL SPEED INDICATOR

2,000 Feet per minute up Maximum

Page 41: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 2-1/2-2

Section 2NORMAL PROCEDURES

2

Paragraph NumberPage

Subject

TABLE OF CONTENTS

INTRODUCTION ......................................................................... 2-1.................... 2-3 COLD WEATHER OPERATIONS ...................................... 2-1-A................ 2-3 HOT WEATHER OPERATIONS......................................... 2-1-B................ 2-3

FLIGHT PLANNING .................................................................... 2-2.................... 2-3PREFLIGHT CHECK................................................................... 2-3.................... 2-3

BEFORE EXTERIOR CHECK ............................................ 2-3-A................ 2-4 EXTERIOR CHECK ............................................................ 2-3-B................ 2-4

INTERIOR AND PRESTART CHECK......................................... 2-4.................... 2-8ENGINE START .......................................................................... 2-5................... 2-10

DRY MOTORING RUN ....................................................... 2-5-A............... 2-11SYSTEMS CHECK ...................................................................... 2-6................... 2-11

PRELIMINARY HYDRAULIC SYSTEMS CHECK ............. 2-6-A............... 2-11 FADEC MANUAL CHECK ................................................. 2-6-B............... 2-11 ENGINE RUNUP................................................................. 2-6-C............... 2-11 HYDRAULIC SYSTEMS CHECK ....................................... 2-6-D............... 2-12

BEFORE TAKEOFF .................................................................... 2-7................... 2-12TAKEOFF .................................................................................... 2-8................... 2-13IN-FLIGHT OPERATIONS .......................................................... 2-9................... 2-13DESCENT AND LANDING.......................................................... 2-10................. 2-14ENGINE SHUTDOWN ................................................................. 2-11................. 2-14POSTFLIGHT CHECK ................................................................ 2-12................. 2-16

Figure Title Number Number

Page

LIST OF FIGURES

Preflight check sequence.......................................................... 2-1................... 2-17

Page 42: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

NORMAL PROCEDURES

Section 2

TEMPORARY REVISION (TR-10) — 15 FEB 2002 2-3

2-1-B. HOT WEATHER OPERATIONS

CAUTION

IF HOVERING WITH A TAILWINDGREATER THAN 10 KNOTS ATO AT A B O V E 3 7 . 8 ° C ( 1 0 0 ° F ) ,C L O S E L Y M O N I T O R E N G I N EOIL TEMPERATURE. THE OILT E M P E R A T U R E M A Y B EREDUCED BY EITHER TURNINGINTO WIND, REDUCING POWEROR TRANSITION TO FORWARDFLIGHT.

2-2. FLIGHT PLANNING

Page 43: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 2-3

Section 2NORMAL PROCEDURES

22-1. INTRODUCTION

This section contains instructions andprocedures for operating helicopter frompl an ni ng s tage , th ro u gh ac tua l f l ig h tconditions, to securing helicopter afterlanding.

Normal and standard conditions are assumedin these procedures. Pertinent data in othersections is referenced when applicable.

Instructions and procedures contained hereinare written for purpose of standardization andare not applicable to all situations.

2-1-A. COLD WEATHER OPERATIONS

Battery starts have been demonstrated to -29°C (-20°F) with standard 17 amp-hourbattery and -35°C (-31°F) with optional 28amp-hour battery.

During engine start in cold temperaturesinitial engine oil pressure of 200 PSI andpressure excursions down to 50 PSI duringwarm up are normal. Normal oil pressure andtemperature indications as per limitationssect i on sh o ul d b e o b ta in ed a f te rapproximately 5 minutes at idle.

2-1-B. HOT WEATHER OPERATIONS

CAUTION

DURING EXTEND ED HOVER ATTAKEOFF POWER WITH THE OATABOVE 49.7°C (121.4°F), MONITORTHE ENGINE OIL TEMPERATURE. IFT E M P E R A T U R E R I S E SABNORMALLY, REDUCE POWER ORTRANSITION TO FORWARD FLIGHTUNTIL TEMPERATURE DECREASES.

2-2. FLIGHT PLANNINGEach flight should be planned adequately toensure safe operations and to provide pilotwith data to be used during flight.Check type of mission to be performed anddestination.

Deter min e th a t a i rc r a ft ha s ad equ ateperformance to complete mission utilizingappropriate performance charts in Section 4.Determine aircraft weight and balance will bewithin limits during entire mission. Utilizeappropriate weight and balance charts inSection 5 and limitations in Section 1.

2-3. PREFLIGHT CHECKPilot is responsible for determining whetherhelicopter is in condition for a safe flight.Refer to Figure 2-1 for pref l ight checksequence.

NOTE

A preflight check is not intended to bea detailed mechanical inspection, butsimply a guide to help pilot checkcondition of helicopter. It may be ascomprehensive as conditions warrantat discretion of pilot.

All areas checked shall include a visualcheck for evidence of corrosion,particularly when helicopter is flownnear salt water or in areas of highindustrial emissions.

Page 44: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

2-4 17 DEC 2002

2-3-A. BEFORE EXTERIOR CHECK

1. Flight planning — Completed.

2. Publications — Checked.

3. GW and CG — Computed.

4. Helicopter servicing — Completed.

5. Battery — Connected.

2-3-B. EXTERIOR CHECK

2-3-B-1. FUSELAGE − CABIN RIGHT SIDE

WARNING

FA I LU R E T O R E MO VE R OT ORT I E D O W N S B E F O R E E N G I N ESTARTING MAY RESULT IN SEVEREDAMAGE AND POSSIBLE INJURY.

1. All main rotor blades — Tiedownsremoved, condition.

2. Right static port — Condition.

3. Cabin doors and hinge bolts —Condition and security.

4. Windows — Condition and security.

5. Landing gear — Condition. Groundhandling wheels removed.

6. Forward and aft crosstube fairings(if installed) — Secured, condition,and aligned.

2-3-B-2. FUSELAGE − CENTER RIGHT SIDE

1. Engine inlet — Condition; removeinlet covers.

2. Cabin roof, transmission cowling,and engine air inlet area — Cleanedof all debris, accumulated snow andice; cowling secured.

3. Forward fairing — Secured.

4. Transmission — Check oil level.Verify actual presence of oil in sightgauge.

5. Transmission oil cooler lines —Condition and security.

6. Transmission mounts — Conditionand security.

7. Main driveshaft — Condition.

8. Access door — Secured.

9. Fuel filler cap — Visually check fuellevel and cap secured.

NOTE

If helicopter is not parked on a levelsurface fuel sump may not properlydrain contaminants.

10. Fuel sump — Drain fuel sample asfollows:

a. RIGHT and LEFT FUEL BOOST/XFR circuit breaker switches —OFF.

b. BATT switch — BATT (on).

c. FUEL VALVE switch — OFF.

d. FWD and AFT FUEL SUMP drainbuttons — Press, drain sample,then release.

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f. Hydromechanical unit — Security and condition; evidence of leakage.

g. Hoses and tubing — Chafing, security, and condition.

h. Oil cooler blower inlet duct andscreen — Clear of obstructions,condition and security.

17. Engine cowl — Secured.

18. Generator cooling scoop — Clear of debris.

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11. Airframe fuel filter — Drain andcheck before first flight of day asfollows:

a. RIGHT and LEFT FUEL BOOST/XFR circuit breaker switches —LEFT and RIGHT (on).

b. FUEL VALVE switch — ON.

c. Fuel filter drain valve — Open,drain sample, then close.

12. Fuel filter test switch — Press andcheck FUEL FILTER caution lightil luminates. Release switch andcheck light extinguishes.

13. FUEL VALVE switch — OFF.

14. LEFT and RIGHT FUEL BOOST/XFRcircuit breaker switches — OFF.

15. BATT switch — OFF.

16. Powerplant area:

a. Main driveshaft aft flexure —Condition.

b. Engine — Condition, security ofattachments, evidence of oilleakage.

c. Engine mounts — Condition andsecurity.

d. Throttle linkage — Condition,s ecu r i ty, a nd f reed o m o foperation.

e. Engine fuel pump — Securityand condi t ion, ev idence ofleakage.

f. Hydromechanica l unit —S e c u r i t y a n d c o n d i t i o n ,evidence of leakage.

g. Hoses and tubing — Chafing,security, and condition.

17. Engine cowl — Secured.

18. Generator cooling scoop — Clear ofdebris.

19. Oil tank — Leaks, security, and capsecured.

20. Access door — Secured.

21. Aft fairing — Secured.

2-3-B-3. FUSELAGE − AFT RIGHT SIDE

1. Fuselage — Condition.

2. Tail rotor driveshaft cover —Condition and security.

3. Tailboom — Condition.

4. Horizontal stabilizer and positionlight — Condition and security.

2-3-B-4. FUSELAGE − FULL AFT

1. Vertical fin — Condition.

2. Tail rotor guard — Condition andsecurity.

3. Anticollision light — Condition andsecurity of lens.

4. Aft position light — Condition.

5. Tail rotor gearbox — Oil level, leaksand security.

6. Tail rotor — Tiedown removed,condition and free movement.

7. Tail rotor controls — Condition andsecurity.

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8. Tail rotor blades:

a. General condition.

b. Tip block — Security and sealintegrity.

c. Internal blade root — Clear ofsnow and ice.

9. Tail rotor yoke — Condition,evidence of static stop contactdamage (deformed static stop yieldindicator).

2-3-B-5. FUSELAGE − AFT LEFT SIDE

1. Tailboom — Condition.

2. Tail rotor driveshaft cover —Condition and security.

3. Horizontal stabilizer area:

a. Horizontal stabilizer — Generalcondi t ion and secur i ty o fattachment.

b. Position light — Condition andsecurity.

c. Forward and aft section of leftupper stabi l izer support totailboom area — Condition oftailboom.

4. Fuselage — Condition.

5. Forward tail rotor driveshaftcoupling — Condition of splinedadapter.

6. Oil cooler blower shaft hangerbearings — Evidence of greaseleakage and overheating.

7. Oil cooler blower — Clear ofobstructions and condition.

8. Oil cooler — Condition and leaks.

9. Oil cooler blower access door —Secured.

10. Oil tank sight glass — Check oillevel.

11. Aft fairing — Secured.

12. Baggage compartment — Cargo tieddown, door secured.

13. Exhaust cover — Removed.

14. Powerplant area:

a. Engine — Condition, security ofattachments.

b. Engine mounts — Condition andsecurity.

c. Exhaust stack — Condition andsecurity.

d. Evidence of fuel and oil leaks.

e. Fuel and oil filter bypassindicators — Check retracted.

f. Hoses and tubing for chafingand condition.

g. Pneumatic lines — Conditionand security.

h. Tail rotor driveshaft — Conditionof splines and couplings.

i. Air induction diffuser duct —Condition and security.

j. Rotor brake disc and caliper (ifinstalled) — Condition, securityof attachment and leakage.Ensure brake pads are retractedfrom brake disc.

k. Engine cowling — Secured.

l. Air induction cowling —Secured.

m. Cabin roof, transmissioncowling, engine air inlet area,and p lenum — Clear o f a l ldebris, accumulated snow andice; cowling secured.

15. Transmission area:

a. Transmission mounts —Condi t ion and secur i ty o felastomeric mounts.

b. Transmission oil filter — Bypass

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c. Main driveshaft — Condition.

d. Transducers and pressure lines— Condition and security.

e. Access door — Secured.

2-3-B-6. CABIN ROOF

1. Main rotor dampers and fairing —Condition and security.

2. Main rotor hub, yoke and frahm —Condition and security.

3. Main rotor blade and skin —Condition.

4. Pitch horn bearing — Wear andsecurity.

5. Main rotor pitch links — Conditionand security of attachment bolts andlocking hardware.

6. Swashplate assembly — Condition,security of attached controls, andboot condition.

7. Control linkages to swashplate —Condition, security of attachmentbolts and locking hardware.

8. Control tube hydraulics-off balancesprings — Condition and security.

9. Hydraulic reservoir filler cap —Closed and locked.

10. Hydraulic system filters — Bypassindicator retracted.

11. Hydraulic actuators and lines —Condition, security, interference,leakage.

2-3-B-7. FUSELAGE − CABIN LEFT SIDE

1. Forward fairing and access door —Secured.

2. Cabin doors and hinge bolts —Condition and security.

3. Windows — Condition and security.

4. Hydraulic reservoir — Check fluidlevel.

5. Landing gear — Condition andground handling wheels removed.

6. Forward and aft crosstube fairings(if installed) — Secured, condition,and aligned.

7. Left static port — Condition.

2-3-B-8. FUSELAGE − FRONT

1. Exterior surfaces — Condition.

2. Windshield — Condition andcleanliness.

3. Battery and vent lines — Conditionand security.

4. HOUR METER circuit breaker — In.

5. Battery access door — Secured.

6. Pitot tube — Cover removed, clear ofobstructions.

7. External power door — Conditionand security.

8. Landing light lamps — Condition.

9. Antennas — Condition and security.

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2-4. INTERIOR AND PRESTART CHECK

1. Cabin interior — Clean, equipmentsecured.

2. Fire extinguisher — Installed andsecured.

3. Cabin loading — Maintain CG withinlimits.

4. Passenger seat belts — Secured.

5. Copilot seat belt — Secured (if solo).

6. Doors — Secured.

7. Throttle — Closed.

8. LDG LTS switch — OFF.

9. Communications switches — Set.

10. Altimeter — Set.

11. Instruments — Correct indications.

12. Overhead switches — Set:

a. BATT switch — OFF.

b. GEN switch — OFF.

c. PART SEP switch (if installed) —OFF.

d. ANTI COLL LT switch — ANTICOLL LT. (on)

e. HYD SYS switch — HYD SYS.(on)

f. CABIN LT/PASS switch — OFF.

g. POS LT switch — As desired.

h. DEFOG switch — OFF.

i. PITOT HEATER switch — OFF.

j. ENG ANTI ICE switch — OFF.

k. AVIONICS MASTER switch —OFF.

l. HEATER switch (if installed) —OFF.

m. INSTR LT rheostat — OFF.

13. Overhead circuit breaker switches —OFF.

14. Overhead circuit breakers — In.

15. Rotor brake handle (if installed) —Up and latched.

CAUTION

28 VD C GP U SH A LL B E 50 0AMPERES OR LESS TO REDUCERISK OF STARTER DAMAGE FROMOVERHEATING.

16. GPU — Connected (if used).

17. BATT switch — ON for battery start,ON for GPU start, OFF for batterycart start. Observe the following:

a. Low rotor audio horn activated.

b. For 8 seconds,

(1) Trend arcs on LCDinstruments indicate fullscale.

(2) TORQUE and NG digitsdisplay 8188.8.

(3) MGT and FUEL digitsdisplay 81888.

(4) NR and NP needles move to1 07% an d 10 0%,respectively.

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c. After 3 seconds; ENG OUT,FAD EC D EGR A DE , FA DE CFAULT, RESTART FAULT, andENGINE OVSPD lights illuminatewith activation of engine outaudio for 3 seconds.

d. ENG OUT light re-illuminateswith reactivation of engine outaudio, after 3 seconds.

18. HORN MUTE button — Press tomute.

19. Caution lights — ENG OUT, XMSNOIL PRESS, R PM, HYD RA UL ICSYSTEM, GEN FAIL, L/FUEL BOOST,R/FUEL BOOST, L/FUEL XFR, and R/FUEL XFR will be illuminated.

NOTE

L/FUEL XFR and R/FUEL XFR will notbe illuminated when forward fuel tankis empty.

20. PEDAL STOP PTT switchannunciator:

Pedals — Centered.

Pr ess — Ver i fy PED A L STO Pcaution and ENGAGED annunciatorilluminated and left pedal travelrestricted.

Release — Veri fy PEDAL STOPcaution and ENGAGED annunciatorextinguished and both pedals travelunrestricted.

21. Flight controls — Loosen frictions;check travel and verify CYCLICC EN TE RI N G l i g ht o p er a t io n ;position for start. Tighten friction asdesired.

22. Throttle — Check freedom of traveland appropriate operation at OFF, I( id le) , FLY and MAX posi t ions.Return throttle to OFF position.

NOTE

With INSTR LT rheostat on and CAUTLT switch positioned to DIM, cautionlights are dimmed to a fixed intensityand cannot be adjusted by INSTR LTrheostat.

23. INSTR LT rheostat — As desired.

24. CAUT LT switch — As desired.

25. FUEL BOOST/XFR circuit breakerswitches — LEFT (on) and RIGHT(on) and verify all boost and transfercaution lights extinguish.

26. FUEL pressure — Check.

27. CAUTION LT TEST button — Pressto test.

28. INSTR CHK button — Press andcheck for exceedances.

29. LCD TEST button — Press to test, ifdesired.

30. FADEC HORN TEST button — Pressto test.

31. FADEC MODE switch — AUTO.

32. FUEL VALVE switch — ON, guardc lo se d, F UE L VA LVE l ig h tilluminates then extinguishes.

33. FUEL QTY — Check TOTAL and FWDtank quantity.

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34. OAT/VOLTS display — Check OATand select VOLTS.

CAUTION

ANY ATTEMPT TO START ENGINEW HE N V OL TA G E IS B EL OW 24VOL T S M AY R ES UL T I N A HO TST A RT . M ON IT OR F OR F A DE CFAILURE. IF FADEC FAILS (FADECFA I L W A RN I NG L IG H T) , A B OR TSTART BY ROLLING THROTTLE TOCUTOFF AND ENGAGE STARTER TOREDUCE MGT.

2-5. ENGINE START

1. Collective — Full down.

2. Cyclic and pedals — Centered andC YC LI C C EN TE RI N G l ig h textinguished.

NOTE

If throttle is positioned in idle formo re than 60 seco n ds , s ta r te rlatching is disabled and throttle mustbe repositioned to cut off and thenback to idle to enable it for another 60seconds.

It is recommended that MGT be below150°C when below 10,000 feet HP orbelow 65 °C when above 10,000 feet HPprior to attempting an engine start.Compliance with this recommendationwill allow for cooler starts and reducepotential of reaching hot start abortlimits. Refer to DRY MOTORING RUN,paragraph 2-5-A.

3. Throttle — Idle position.

4. START switch — Momentarily press(hold for approximately 1 second)and observe STAR T and AUTORELIGHT lights are illuminated.

5. MGT — Monitor.

CAUTION

IF MAIN ROTOR IS NOT ROTATING BY25% NG, ABORT START BY ROLLINGTHROTTLE TO CUT OFF. ENSURESTARTER HAS DISENGAGED WHENMGT DECREASES BELOW 150°C.

6. START light — Extinguished at 50%NG (starter has disengaged).

7. AUTO RELIGHT light —Extinguished at 60% NG.

8. ENG and XMSN OIL pressures —Check.

CAUTION

IF ENGINE HAS BEEN SHUT DOWNF OR M OR E T H A N 1 5 M IN U T ES,STABILIZE AT IDLE FOR 1 MINUTEBEFORE INCREASING THROTTLE.

NOTE

During cold temperature operations,normal transmission and engine oilpressure limits may be exceededduring start. Stabilize engine at idleuntil minimum temperature andpressure limits are attained.

9. Idle — 63 ± 1% NG.

10. BATT switch — ON (if applicable).

11. GPU — Disconnect and close door(if applicable).

12. GEN switch — GEN (on); observeGEN FAIL light extinguishes.

NOTE

Tu rn gen era to r OF F i f ammeterindication drops to zero amps after aninitial full scale indication. One reset isallowed. RESET generator and thenturn generator back ON (applicablewith AMPS/FUEL PSI gauge PN 407-075-024-101 and sub.). Refer to BHT-407-MD-1.

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13. Voltmeter — 28.5 ± 0.5 volts.

14. FLIGHT INSTR circuit breakerswitches (3) (if installed) — DG, ATTand TURN (on).

NOTE

If dual controls are installed, guardthrottle to prevent inadvertentmanipulation from co-pilot position.

2-5-A. DRY MOTORING RUN

The following procedure is used to reduceresidual MGT to recommended levels forengine start.

1. Throttle — Closed position.

2. START switch — Hold engaged for15 seconds, then release.

Follow ENGINE START procedure, paragraph2-5, once 0% NG is indicated.

2-6. SYSTEMS CHECK2-6-A. PRELIMINARY HYDRAULIC

SYSTEMS CHECK

NOTE

Uncommanded control movement ormotoring with hydraulic system off mayindicate hydraulic system malfunction.

1. HYD SYS switch — OFF.

2. HYDRAULIC SYSTEM caution light— Illuminated.

3. HYD SYS switch — HYD SYS (on).

4. HYDRAULIC SYSTEM caution light— Extinguished.

2-6-B. FADEC MANUAL CHECK

WARNING

A U T O T O M A N U A L M O D ETRANSITIONS WITH NR/NP AT 100%FLAT PITCH CAN RESULT IN RAPIDN R / N P A C C E L E R A T I O N I NAPPROXIMATELY 7 SECONDS. TOAVOID POSSIBLE OVERSPEEDC O N D I T I O N , P E R F O R M T H EFOLLOWING CHECK AT IDLE (63%NG).

1. Throttle — Idle (63% NG).

2. FADEC MODE switch — MAN.

3. FADEC MANUAL and AUTORELIGHT lights — Illuminated.

4. Check NG stabilized at 75% or less.

5. Throttle — Increase slowly to ensureengine responds, then return to idle.

6. FADEC MODE switch - AUTO.

7. FADEC MANUAL and AUTORELIGHT lights — Extinguished.

2-6-C. ENGINE RUNUP

1. Throttle — Increase smoothly to FLYdetent position. Check RPM warninglight extinguished at 95% NR.

2. NR and NP needles — Checkmatching and indicating 100%.

NOTE

Overhead circuit breakers highlightedwith arrow graphic ; are poweredthrough AVIONICS MASTER switch.

3. AVIONICS MASTER switch —AVIONICS MASTER (on).

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4. ELT (if installed) — Check forinadvertent transmission.

5. Flight controls — Check freedomwith minimum friction.

6. ENG ANTI ICE switch — ENG ANTIICE (on); check for MGT increaseand illumination of ENGINE ANTI-ICE light (if installed).

7. ENG ANTI ICE switch — OFF; checkMGT returns to normal and ENGINEANTI - ICE l ight ( i f insta l led)extinguishes; then ENG ANTI ICE(on) if required.

NOTE

If temperature is below 5°C (40°F) andvisible moisture is present, ENG ANTIICE shall be on.

8. PART SEP switch (if installed) — Asrequired.

2-6-D. HYDRAULIC SYSTEMS CHECK

NOTE

Hydraulic systems check is todetermine proper operation ofhydraulic actuators for each flightcontrol system. If abnormal forces,unequal forces, control binding, ormotoring are encountered, it may be anindication of a malfunctioning flightcontrol actuator.

1. Collective — Full down.

2. NR — 100% RPM.

3. HYD SYS switch — OFF.

4. HYDRAULIC SYSTEM caution light— Illuminated.

5. Cyclic — Centered.

6. Cyclic control — Check normaloperation by moving cyclic forwardand aft , then le ft and r ight(approximately 1 inch). Centercyclic.

7. Collective — Check normaloperation by increasing collectiveslightly (1 to 2 inches). Repeat two tothree times as required. Return tofull down position.

8. Pedals — Check normal operation bydisplacing pedals slightly (1 inch).

9. HYD SYS switch — HYD SYS (on).

10. HYDRAULIC SYSTEM caution light— Extinguished.

11. Cyclic and collective friction — Setas desired.

2-7. BEFORE TAKEOFF1. ENG ANTI ICE switch — As required.

2. Light switches — As required.

3. INSTR LT rheostat — As desired.

NOTE

For night flight, it is recommended topoint the map light at the flightinstruments and set to a low intensity.Sufficient night lighting will beprovided in the event of an instrumentlighting failure.

4. Radio(s) — Check as required.

5. Flight controls — Position andadjust frictions for takeoff.

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CAUTION

F A I L U R E T O P O S I T I O N A N DMAINTAIN THROTTLE IN FLY DETENTPOSITION PRIOR TO TAKEOFF ANDD U R I N G N O R M A L F L I G H TOPERATIONS CAN LIMIT AVAILABLEENGINE POWER.

6. Throttle — Open to FLY detentposition. Check 99 to 100% NR/NP.

7. Engine, transmission, and electricalinstruments — Within limits.

8. Flight and navigation instruments —Check.

9. FUEL QTY — Note indication.

10. FUEL QTY FWD TANK button —Pr ess , n o te fu e l r emai n in g i nforward cell.

2-8. TAKEOFF

1. Rear facing seat headrests —Adjusted to proper position.

NOTE

During takeoffs disregard CYCLICCENTERING light and position cyclicas required.

2. Collective — Increase to hover.

3. Directional control — As required tomaintain desired heading.

4. Cyclic — Apply as required toaccelerate smoothly.

5. Increase collective, up to 5% torqueab ov e h o ver p ow er, to o bta i ndesired rate of climb and airspeed.On ce c l ear o f the H V d i agr amshaded areas, adjust power andairspeed as desired.

6. PEDAL STOP PTT switch — CheckENGAGED annunciator illuminatedabove 55 ± 5 KIAS.

2-9. IN-FLIGHT OPERATIONS

1. AIRSPEED — As desired (not toexceed VNE at flight altitude).

CAUTION

A T H I G H P O W E R A N D H I G HA I R S P E E D , C Y C L I C O N L YA C C E L E R A T I O N S A N DMANEUVERING MAY SIGNIFICANTLYINCREASE MGT AND TORQUE WITHN O C OL LE CT I VE IN P UT . T H ISIN C R EA SE IS M O RE R A PI D A TLOWER OAT.

NOTE

Pilot shall keep feet on tail rotor pedalsat all times. Do not press PEDAL STOPPTT switch in flight.

2. PEDAL STOP PTT switch — CheckENGAGED annunciator illuminatedabove 55 ± 5 KIAS.

3. ENG ANTI ICE and PITOT HEATERswitches — ENG ANTI ICE andPITOT HEATER swi tches o n invisible moisture when ambienttemperature is at or below 5°C(40°F).

4. PITOT HEATER — confirm operation(increase ammeter load).

NOTE

When ENG ANTI ICE switch is in ENGANTI ICE (on), MGT will increase.Monitor MGT when selecting ENG ANTIICE at high power settings.

5. Altimeter — Within limits.

6. FUEL QTY FWD TANK button —Pr ess , n ote for war d fu e l tankindication.

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NOTE

Fu l l fo rw ard fu e l tan k q ua nt i ty(approximately 256 pounds) will beindicated at approximately 770 poundsor greater total fuel. Fuel transfer willbe complete at approximately 185pounds total fuel.

2-10. DESCENT AND LANDING

NOTE

Large reductions in collective pitch atheavy GW may permit NR to increaseindependent of NP (needles split). Mainrotor may be reengaged with a smoothincrease in collective pitch.

1. Rear facing seat headrests —Adjusted to proper position.

2. Flight controls — Adjust friction asdesired.

3. Throttle — Fly detent position.Check 99 to 100% NP.

4. Flight path — As required for type ofapproach.

5. ENG ANTI ICE — As required.

6. LDG LTS switch — As desired.

NOTE

During run-on or slope landingsdisregard CYCLIC CENTERING lightand position cyclic as required. Afterlanding is completed and collective isfull down, reposition cyclic so thatC YC LI C C EN T ER IN G l i g ht isextinguished.

7. PEDAL STOP PTT switch — CheckENGAGED annunciator extinguishedbelow 50 ± 5 KIAS.

2-11. ENGINE SHUTDOWN

1. Collective — Full down.

2. Cyclic and pedals — Centered andC YC LI C C EN TE RI N G l ig h textinguished.

3. Cyclic friction — Increase so thatcyclic maintains centered position.

4. LDG LTS switch — OFF.

5. Throttle — Reduce to idle stop.Check RPM warning light illuminatedand audio on at 95% NR.

NOTE

If dual controls are installed, guardthrottle to prevent inadvertentmanipulation from co-pilot position.

6. HORN MUTE button — Press tomute.

7. MGT — Stabilize at idle for 2minutes.

8. ENG ANTI ICE switch — OFF.

9. FLIGHT INSTR circuit breakersswitches (if installed) — OFF

10. FUEL BOOST/XFR LEFT circuitbreaker switch — OFF.

NOTE

Left fuel boost and transfer pumps willcontinue to operate until either LEFTFUEL BOOST/XFR circuit breakerswitch (highlighted with yellow border)or FUEL VALVE switch is positioned toOFF. These pumps operate directlyfrom battery and will not be deactivatedwhen BATT switch is OFF. Batterypower will be depleted if both switchesremain on.

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11. ELT (if installed) — Check forinadvertent transmission.

12. AVIONICS MASTER switch — OFF.

13. GEN switch — OFF.

14. OVSPD TEST button — If required;press, hold 1 second, and release.

NOTE

Overspeed shut down test should beaccomplished on first engine shutdown of the day. ENGINE OVSPD lightwill momentarily illuminate in additionto those lights that illuminate during anormal shut down.

15. IDLE REL switch — Press and hold.

CAUTION

POSITIONING THROTTLE OUT OFCUT-OFF DURING NG SPOOL DOWNM AY C A U SE POST EN GIN ESHUTDOWN FIRE.

16. Throttle — Closed; check MGT andN G d ecr eas i ng , EN GI NE OU Twarning light illuminated and audioon at 55 ± 1%.

17. HORN MUTE button — Press tomute.

CAUTION

AVOID RAPID ENGAGEMENT OFROTOR BRAKE IF HELICOPTER IS ONICE OR OTHER SLIPPERY OR LOOSESURFACE TO PREVENT ROTATION OFHELICOPTER.

18. Rotor brake (if installed) — Apply fullrotor brake at or below 40% NR.Return rotor brake handle to stowedposition just prior to main rotorstopping.

19. FUEL VALVE switch — OFF.

CAUTION

DO NOT INCREASE COLLECTIVE ORAPPLY LEFT TAIL ROTOR PEDAL TOSL OW RO TO R D U R IN G CO A STDOWN.

20. Pilot — Remain on flight controlsuntil rotor has come to a completestop.

21. All overhead switches, except HYDSYS switch — OFF.

NOTE

Ensure engine rotation has completelystopped prior to positioning BATTswitch to OFF.

22. BATT switch — OFF, with NG at 0%.

CAUTION

APPLICABLE MAINTENANCE ACTIONMUST BE PERFORMED PRIOR TOFURTHER FLIGHT IF A FADEC LIGHTHAS ILLUMINATED DURING THEPREVIOUS FLIGHT OR ON ENGINESHUTDOWN.

NOTE

If shutting down at, or refueling to,between approximately 185 to 210pounds total fuel quantity, up to 18pounds of fuel may remain in forwardfuel cell as unusable.

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2-12. POSTFLIGHT CHECK

If any of following conditions exist:

• Thunderstorms are in local area or forecasted.

• Winds in excess of 35 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 basic GW of helicopter.

• Helicopter to be left unattended.

Perform following:

1. Install main rotor blade tiedowns.

2. Secure tail rotor loosely to tailboomwi th t ied o wn s t r ap to p r even texcessive flapping.

3. Install exhaust cover, engine inletprotective plugs and pitot cover.

NOTE

Refer to BHT-407-MD-1 for additionaltiedown data.

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Figure 2-1. Preflight check sequence

17 DEC 2002 2-17/2-18

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Section 3EMERGEMCY/MALFUNCTION PROCEDURES

3

Paragraph NumberPage

Subject

TABLE OF CONTENTS

INTRODUCTION ......................................................................... 3-1.................... 3-3DEFINITIONS .............................................................................. 3-2.................... 3-3ENGINE ....................................................................................... 3-3.................... 3-3

ENGINE FAILURE............................................................... 3-3-A................ 3-3ENGINE RESTART IN FLIGHT........................................... 3-3-B................ 3-4ENGINE UNDERSPEED ..................................................... 3-3-C................ 3-6ENGINE OVERSPEED........................................................ 3-3-D................ 3-6ENGINE COMPRESSOR STALL........................................ 3-3-E ................ 3-6ENGINE HOT START/SHUTDOWN ................................... 3-3-F ................ 3-7ENGINE OIL PRESSURE LOW OR FLUCTUATING ......... 3-3-G................ 3-7ENGINE OIL TEMPERATURE HIGH.................................. 3-3-H................ 3-7DRIVESHAFT FAILURE ..................................................... 3-3-J ................ 3-8FADEC FAILURE ................................................................ 3-3-K................ 3-8

FIRE............................................................................................. 3-4.................... 3-9ENGINE FIRE ON GROUND............................................... 3-4-A................ 3-9ENGINE FIRE DURING FLIGHT......................................... 3-4-B................ 3-9CABIN SMOKE OR FUMES ............................................... 3-4-C................ 3-9

TAIL ROTOR ............................................................................... 3-5................... 3-10COMPLETE LOSS OF TAIL ROTOR THRUST.................. 3-5-A............... 3-10FIXED PITCH FAILURES.................................................... 3-5-B............... 3-10

HYDRAULIC SYSTEM ................................................................ 3-6................... 3-11LOSS OF HYDRAULIC PRESSURE .................................. 3-6-A............... 3-11FLIGHT CONTROL ACTUATOR MALFUNCTION............. 3-6-B............... 3-12

ELECTRICAL SYSTEM .............................................................. 3-7................... 3-12GENERATOR FAILURE ..................................................... 3-7-A............... 3-12EXCESSIVE ELECTRICAL LOAD...................................... 3-7-B............... 3-12

FUEL SYSTEM............................................................................ 3-8................... 3-13CYCLIC JAM ............................................................................... 3-9................... 3-13WARNING, CAUTION, AND ADVISORY LIGHTS/MESSAGES 3-10................. 3-14

Title Number

TableNumberPage

LIST OF TABLES

Warning (red) lights ................................................................... 3-1................... 3-15Caution (amber) and advisory (white/green) lights ................ 3-2................... 3-16

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Section 3EMERGEMCY/MALFUNCTION PROCEDURES

33-1. INTRODUCTION

Following procedures contain indications offailures or malfunctions which affect safety ofcrew, hel icopter, ground personne l orproperty; use of emergency features ofprimary and backup systems; and appropriatewarnings, cautions, and explanatory notes.Tables 3-1 and 3-2 list fault conditions andcorrective actions for warning lights andcaution/advisory lights respectively.

NOTE

All corrective action procedures listedherein assume pilot gives first priorityto helicopter control and a safe flightpath.

A tripped circuit breaker should not beres e t in f l ig h t un le ss d eem ednecessary for safe completion of theflight.

If a tripped circuit breaker is deemednecessary for safe completion of theflight, it should only be reset one time.

Helicopter should not be operated followingany precautionary landing until cause ofma l funct ion has been de termined andcorrective maintenance action taken.

3-2. DEFINITIONS

Following terms indicate degree of urgency inlanding helicopter.

Fol lowin g te rms are u sed to descr ibeoperating condition of a system, subsystem,assembly, or component.

3-3. ENGINE

3-3-A. ENGINE FAILURE

3-3-A-1. ENGINE FAILURE — HOVERING

INDICATIONS:

1. Left yaw.

2. ENGINE OUT and RPM warninglights illuminated.

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

Landing site and duration of flight are at discretion of pilot. Extended flight beyond nearest approved landing area is not recommended.

Affected Fails to operate in intended or usual manner.

Normal Operates in intended or usual manner.

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3. Engine instruments indicate powerloss.

4. Engine out audio activated when NGdrops below 55%.

5. NR decreasing with RPM warninglight and audio on when NR dropsbelow 95%.

PROCEDURE:

1. Maintain heading and attitudecontrol.

2. Collective — Adjust to control NRand rate of descent. Increase prior toground contact to cushion landing.

NOTE

Amplitude of collective movement is afunction of height above ground. Anyforward airspeed will aid in ability tocushion landing.

3. Land.

4. Shut down helicopter.

3-3-A-2. ENGINE FAILURE — INFLIGHT

INDICATIONS:

1. Left yaw.

2. ENGINE OUT and RPM warninglights illuminated.

3. Engine instruments indicate powerloss.

4. Engine out audio activated when NGdrops below 55%.

5. NR decreasing with RPM warninglight and audio on when NR dropsbelow 95%.

PROCEDURE:

1. Maintain heading and attitudecontrol.

2. Collective — Adjust as required tomaintain 85 to 107% NR.

NOTE

M ain ta i n i ng N R a t h ig h end o foperating range will provide maximumrotor energy to accomplish landing, butwill cause an increased rate of descent.

3. Cyclic — Adjust to obtain desiredautorotative AIRSPEED.

NOTE

Maximum AIRSPEED for steady stateautorotation is 100 KIAS. Minimum rateof d escent ai rspeed is 55 KIAS.Maximum glide distance airspeed is 80KIAS.

4. Attempt engine restart if amplealtitude remains. (Refer to ENGINERESTART, paragraph 3-3-B).

5. FUEL VALVE switch — OFF.

6. At low altitude:

a. Throttle — Closed.

b. Flare to lose airspeed.

7. Apply collective as flare effectdecreases to further reduce forwardspeed and cushion landing. Uponground contact, collective shall bereduced smoothly while maintainingcyc l ic in n eu t ra l o r cen ter edposition.

8. Complete helicopter shutdown.

3-3-B. ENGINE RESTART IN FLIGHT

An engine restart may be attempted in flight iftime and altitude permit.

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CAUTION

IF CAUSE OF FAILURE IS OBVIOUSLYMECHANICAL, AS EVIDENCED BYABNORMAL METALLIC OR GRINDINGSOUNDS, DO NOT ATTEMPT ARESTART.

3-3-B-1. RESTART −−−− AUTOMATIC MODE

l PROCEDURE (NO RESTART FAULT ORFADEC MANUAL LIGHTS ILLUMINATED):

1. Collective — Adjust to maintain 85 to107% NR.

2. AIRSPEED — Adjust as desired.

NOTE

Minimum rate of descent airspeed of 55KIAS and minimum NR will allow pilotmore time for air restart.

3. FUEL VALVE switch — ON.

4. Throttle — Cutoff.

5. START switch — Hold to startposition (start will latch after throttleis placed to idle).

6. NG — Between 12% and 50%.

7. Throttle — Idle.

8. MGT — Monitor.

9. Throttle — Advance smoothly to FLYdetent position.

If restart is unsuccessful, abort start andsecure engine as follows:

10. Throttle — Closed.

11. FUEL VALVE switch — OFF.

12. Accomplish autorotative descentand landing.

3-3-B-2. RESTART — MANUAL MODE

R ESTA R T FA U LT O R FA D EC M A N UA LLIGHTS ILLUMINATED.

l PROCEDURE:

1. Collective — Adjust to maintain 85 to107% NR.

2. AIRSPEED — Adjust as desired.

NOTE

Minimum rate of descent airspeed of 55KIAS and minimum NR will allow pilotmore time for air restart.

3. Throttle — Closed.

4. FADEC MODE switch — MAN.

5. FUEL VALVE switch — ON.

6. START switch — Hold to startposition (starter will not latch).

7. NG — 12%.

8. Throttle — Slowly advance out ofcutoff and stop advancing throttle atlight off.

9. MGT — Allow to peak.

10. Throttle — Increase fuel flow bymodulating throttle to maintain MGTwithin limits.

11. START switch — Release at 50% NG.

12. Throttle — Advance smoothly andmodulate to 100% NP.

If restart is unsuccessful, abort start andsecure engine as follows:

13. Throttle — Closed.

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14. FUEL VALVE switch — OFF.

15. Accomplish autorotative descentand landing.

3-3-C. ENGINE UNDERSPEED

NO CAUTION/WARNING/ADVISORY LIGHTSILLUMINATED.

INDICATIONS:

1. Decrease in NG.

2. Subsequent decrease in NP.

3. Possible decrease in NR.

4. Decrease in TRQ.

PROCEDURE:

1. Collective — Adjust as required tomaintain 85 to 107% NR.

2. Throttle — Confirm in FLY detentposition.

3. Throttle — Position throttle to theapproximate bezel position thatcoincides with the guage indicatedNG.

4. FADEC MODE switch — MAN.

5. NR — Maintain 95 to 100% withthrottle and collective.

6. Land as soon as practical.

3-3-D. ENGINE OVERSPEED

(NO CAUTION/WARNING/ADVISORY LIGHTSILLUMINATED)

INDICATIONS:

1. Increase in NR.

2. Increase in NP.

3. Increase in NG.

4. Increase in TRQ.

PROCEDURE:

1. Throttle — Retard.

2. NG or NP — Attempt to stabilize withthrottle and collective.

3. FADEC MODE switch — MAN.

4. NR — Maintain 95 to 100% withthrottle and collective.

CAUTION

IF UNABLE TO MAINTAIN NR, NP, NG,OR MGT, PREPARE FOR A POWEROF F L A N D IN G B Y L OW ER IN GCOLLECTIVE AND SHUTTING DOWNENGINE.

3-3-E. ENGINE COMPRESSOR STALL

INDICATIONS:

1. Engine pops.

2. High or erratic MGT.

3. Decreasing or erratic NG or NP.

4. TRQ oscillations.

PROCEDURE:

1. Collective — Reduce power,maintain slow cruise flight.

2. MGT and NG — Check for normalindications.

3. ENG ANTI ICE switch — ON.

4. PART SEP switch (if installed) — ON.

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5. HEATER switch (if installed) — ON.

NOTE

Severity of compressor stalls willdictate if engine should be shut downand treated as an engine failure. Violentstalls can cause damage to engine anddrive system components, and must behandled as an emergency condition.Stalls of a less severe nature (one ortwo low intensity pops) may permitcontinued operation of engine at ared u ced p o wer l eve l , a vo id in gcondition that resulted in compressorstall.

If pilot elects to continue flight:

6. Collective — Increase slowly toachieve desired power level.

7. MGT and NG — Monitor for normalresponse.

8. Land as soon as practical.

If pilot elects to shut down engine:

9. Enter autorotation.

10. Throttle — Closed.

11. FUEL VALVE switch — OFF.

12. Collective — Adjust as required tomaintain 85 to 107% NR.

13. Cyclic — Adjust as required tomaintain desired AIRSPEED.

14. Prepare for power-off landing.

3-3-F. ENGINE HOT START/SHUTDOWN

INDICATIONS:

1. Excessive MGT.

2. Visible smoke or fire.

PROCEDURE:

1. Throttle — Closed.

2. FUEL VALVE switch — OFF.

NOTE

Starter will remain engaged until MGTd ecre ases to 150 ° C an d th enautomatically disengage. Starter maybe manually engaged by holdingSTARTER switch forward.

3. STARTER switch — Ensure starter ismotoring engine until MGT stabilizesat normal temperature.

4. Shut down helicopter.

3-3-G. ENGINE OIL PRESSURE LOW OR FLUCTUATING

INDICATIONS:

1. Engine oil pressure below minimum.

2. Engine oil pressure fluctuatingabnormally.

PROCEDURE:

1. Engine oil pressure and temperature— Monitor.

2. Land as soon as practical.

3-3-H. ENGINE OIL TEMPERATURE HIGH

INDICATIONS:

1. Engine oil temperature increasingabove normal.

2. Engine oil temperature abovemaximum.

PROCEDURE:

Land as soon as practical.

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3-3-J. DRIVESHAFT FAILURE

WARNING

FAILURE OF MAIN DRIVESHAFT TOTRANSMISSION WILL RESULT INCOMPLETE LOSS OF POWER TO MAINR OT OR . A L TH OU G H C O CK PI TINDICATIONS FOR A DRIVESHAFTFAILURE ARE SIMILAR TO AN ENGINEOVERSPEED, IT IS IMPERATIVE THATA U T O R O T A T I V E F L I G H TPROCEDURES BE ESTABLISHEDIMMEDIATELY. FAILURE TO REACTIMMEDIATELY TO LOW RPM AUDIO,RPM LIGHT AND NP/NR TACHOMETERCAN RESULT IN LOSS OF CONTROL.

INDICATIONS:

1. Left yaw

2. Rapid decrease in NR

3. Rapid increase in NP

4. LOW RPM audio horn

5. Illumination of RPM light

6. Possible increase in noise level dueto o ver sp eed in g en g in e an ddriveshaft breakage.

NOTE

Engine overspeed trip system willactivate at 118.5% NP causing fuel flowto go to minimum. After initialoverspeed, FADEC will adjust fuel flowto maintain engine at 100% NP.

PROCEDURE:

1. Maintain heading and attitudecontrol.

2. Collective — Adjust as required tomaintain 85 to 107% NR.

NOTE

Minimum rate of descent airspeed is 55KIAS. Maximum glide distanceairspeed is 80 KIAS.

3. Cyclic — Adjust to obtain desiredautorotative airspeed.

NOTE

To maintain tail rotor effectiveness donot shutdown engine.

4. Landing — Complete autorotativelanding.

5. Complete helicopter shutdown.

3-3-K. FADEC FAILURE

NOTE

Takeoff power may not be available inthe MAN mode. Maximum continuouspower will be available for all ambientconditions.

INDICATIONS

1. FADEC fail audio activated.

2. FA D E C FA I L w a r n i n g l i g h tilluminated.

3. FADEC MANUAL caut ion l ightilluminated.

4. AUTO RELIGHT advisory l ightilluminated.

5. FADEC MODE switch MAN lightilluminated.

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PROCEDURE:

WARNING

WITHIN 2 TO 7 SECONDS AFTER THEFADEC FAUL WARNING NR/NP MAYINCREASE RAPIDLY, REQUIRINGPOS IT IV E M O VEM EN T S O FCOLLECTIVE AND THROTTLE TOCONTROL NR.

1. Throttle — If time permits, matchthr o t t le b ez e l po s i t io n to N Gindication.

2. NR/NP — Maintain 95 to 100% withcollective and throttle.

3. FADEC MODE switch — Depress onetime, muting FADEC fail audio.

NOTE

Depressing FADEC MODE switch onetime, will only mute FADEC fail audio.This step should not be accomplisheduntil pilot is firmly established in MANcontrol.

4. Land as soon as practical.

5. Normal shutdown if possible.

3-4. FIRE

3-4-A. ENGINE FIRE ON GROUND

INDICATIONS:

1. Smoke

2. Fumes

3. Fire

PROCEDURE:

1. Throttle — Closed

2. FUEL VALVE switch — OFF

3. GEN switch — OFF

4. BATT switch — OFF

5. Rotor brake (if installed) — Engage

6. Exit helicopter

3-4-B. ENGINE FIRE DURING FLIGHT

INDICATIONS:

1. Smoke.

2. Fumes.

3. Fire.

PROCEDURE:

1. Inflight — Immediately enterautorotation.

2. Throttle — Closed.

3. FUEL VALVE switch — OFF.

4. If time permits, FUEL BOOST/XFRcircuit breaker switches — OFF.

5. Execute autorotative descent andlanding.

6. BATT switch — OFF.

NOTE

Do not restart engine until correctivemaintenance has been performed.

3-4-C. CABIN SMOKE OR FUMES

INDICATIONS:

1. Smoke

2. Fumes

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PROCEDURE:

1. Inflight — Start descent

2. AIR COND BLO switch (if installed)— OFF

3. HEATER switch (if installed) — OFF

4. All vents — Open

5. Side windows — Open

If time and altitude permits:

6. Source — Attempt to identify andsecure.

7. If source is identified and smokeand/or fumes still persist — Land assoon as possible.

8. If source is identified and smokeand/or fumes are cleared — Land assoon as practical.

3-5. TAIL ROTOR

There is no single emergency procedure forall types of antitorque malfunctions . One keyto a pilot successfully handling a tail rotoremergency l ies in the abil ity to quicklyrecognize the type of malfunction that hasoccurred.

3-5-A. COMPLETE LOSS OF TAIL ROTOR THRUST

This is a situation involving a break in drivesystem (e.g., severed driveshaft), wherein tailrotor stops turning and delivers no thrust.

INDICATIONS:

1. Uncontrollable yawing to right (leftside slip).

2. Nose down tucking.

3. Possible roll of fuselage.

NOTE

Severity of initial reaction of helicopterwill be affected by AIRSPEED, CG,power being used, and HD.

PROCEDURE:

3-5-A-1. HOVERING

Close thrott le and per form a hover ingautorotation landing. A slight rotation can beexpected on touchdown.

3-5-A-2. IN-FLIGHT

Reduce throttle to idle, immediately enterautorotat ion, and maintain a min imumAIRSPEED of 55 KIAS during descent.

NOTE

When a suitable landing site is notavailable, vertical f in may permitcontrolled flight at low power levelsand sufficient AIRSPEED. During finalstages of approach, a mild flare shouldbe executed, making sure all power torotor is off. Maintain helicopter in aslight flare and smoothly use collectiveto execute a soft, slightly nose-highlanding. Landing on aft portion of skidswill tend to correct side drift. Thistechnique will, in most cases, result ina run-on type landing.

CAUTION

IN A RUN-ON TYPE LANDING AFTERTOUCH ING DOWN , DO NOT U SECY CL IC T O RED U CE FO RW A RDSPEED.

3-5-B. FIXED PITCH FAILURES

This is a situation involving inabil ity tochange tail rotor thrust (blade angle) withanti-torque pedals.

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INDICATIONS:

1. Lack of directional response.

2. Locked pedals.

NOTE

If pedals cannot be moved with amoderate amount of force, do notattempt to apply a maximum effort,since a more serious malfunction couldresult. If helicopter is in a trimmedcondition when malfunction occurs,TRQ and AIRSPEED should be notedand helicopter flown to a suitablelanding area. Certain combinations ofTRQ, NR, and AIRSPEED will correct ayaw attitude, and these combinationsshould be used to land helicopter.

PROCEDURE:

NOTE

Pull pedal stop emergency release toensure pedal stop is retracted.

3-5-B-1. HOVERING

Do not close throttle unless a severe rightyaw occurs. If pedals lock in any position at aho ve r, l an di ng f r o m a ho ve r c an beaccomplished with greater safety underpower-controlled flight rather than by closingthrottle and entering autorotation.

3-5-B-2. IN-FLIGHT — LEFT PEDAL APPLIED

In a high power condition, helicopter will yawto left when power is reduced. Power andAIRSPEED should be adjusted to a valuewhere a comfortable yaw angle can bemaintained. If AIRSPEED is increased, verticalf in wi l l become more ef fec t ive and anincreased left yaw attitude will develop. Toaccomplish landing, establish a power-on

approach with sufficiently low AIRSPEED(zero if necessary) to attain a rate of descentwith a comfortable sideslip angle. (A decreasein NP d ecreases tai l ro tor thrus t . ) Ascollective is increased just before touchdown,left yaw will be reduced.

3-5-B-3. IN-FLIGHT — RIGHT PEDAL APPLIED

In cruise flight or reduced power situation,helicopter will yaw to right when power isincreased. A low power, run-on type landingwill be necessary by gradually reducingthrottle to maintain heading while addingcollective to cushion landing. If right yawbecomes excessive, close throttle completely.

3-6. HYDRAULIC SYSTEM

3-6-A. LOSS OF HYDRAULIC PRESSURE

INDICATIONS:

1. HYDRAULIC SYSTEM caution lightilluminated.

2. Grinding or howling noise frompump.

3. Increase in force required to moveflight controls.

4. Feedback forces may be evidentduring flight control movement.

PROCEDURE:

1. Reduce AIRSPEED to 70 to 100KIAS.

2. HYD SYSTEM circuit breaker — Out.If hydraulic power is not restored,push breaker in.

3. HYD SYS switch — HYD SYS; OFF ifhydraulic power is not restored.

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4. For extended flight set comfortableAIRSPEED, u p to 120 KIAS, tominimize control forces.

5. Land as soon as practical.

6. A run-on landing at effectivet ran s l a t io n a l l i f t spe ed(ap pr o x im ate ly 1 5 k no ts ) isrecommended.

3-6-B. FLIGHT CONTROL ACTUATOR MALFUNCTION

An actuator hardover can occur in any flightcontrol axis, but a cyclic cam jam will onlyoccur in the fore and aft axis. An actuatorhardover is manifested by uncommandedmovements of one or two flight controls. Iftwo controls move, the pilot will find one ofthese controls will require a higher thanno r mal co nt r o l fo rce to o p p ose themovement. This force cannot be “trimmed” tozero without turning the HYD SYS switch OFF.Once the hydraulic boost is OFF, the forceson the affected flight control will be similar tothe “normal” hydraulic off forces.

INDICATIONS:

1. Uncommanded flight controlmovements

2. High flight control forces to opposemovement in one axis

3. Feedback forces only in affectedflight control axis

4. Flight control forces normal inunaffected axis

PROCEDURE:

1. Attitude — Maintain

2. HYD SYS switch — OFF

3. AIRSPEED — Set to 70 to 100 KIAS

4. Land as soon as possible usingprocedure from paragraph 3-6-A

3-7. ELECTRICAL SYSTEM

3-7-A. GENERATOR FAILURE

INDICATIONS:

1. GEN FAIL caution light illuminated.

2. AMPS indicates 0.

3. Voltmeter — Approximately 24 volts

PROCEDURE:

1. GENERATOR FIELD andGEN ER ATOR R ES ET c i rcu i tbreakers — Check in.

2. GEN switch — RESET; then GEN.

3. If power is not restored, place GENswitch to OFF; land as soon aspractical.

NOTE

With generator OFF, a fully chargedbattery will provide approximately 21minutes of power for basic helicopterand one VHF COMM radio (35 minuteswith optional 28 ampere/hour battery).

3-7-B. EXCESSIVE ELECTRICAL LOAD

INDICATIONS:

1. AMPS indicates excessive load.

2. Smoke or fumes.

PROCEDURE:

1. GEN switch — OFF.

2. BATT switch — OFF.

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3. FUEL BOOST/XFR LEFT circuitbreaker switch — LEFT (on).

WARNING

PRIOR TO BATTERY DEPLETION,A LT IT U D E M US T B E R ED U CE DBELOW 8000 FEET HP (JET A) OR 4000HP (JET B). UNUSABLE FUEL MAY BEAS HIGH AS 135 POUNDS AFTER THEBATTERY IS DEPLETED DUE TOINABILITY TO TRANSFER FUEL FROMFORWARD CELLS.

NOTE

With battery and generator OFF, an80% charged battery will operate leftfuel boost pump and left fuel transferpump for approximately 1.7 hours (2.8hours with optional 28 ampere/hourbattery).

4. Airspeed — 60 KIAS or less.

NOTE

Pedal stop disengages with loss ofelectrical power.

5. Land as soon as practical.

NOTE

When throttle is repositioned to the idlestop (during engine shutdown) thePMA will go offline and the engine mayflameout.

3-8. FUEL SYSTEM

DUAL FUEL TRANSFER FAILURE

INDICATIONS:

1. L/FUEL XFR and R/FUEL XFRcaution lights illuminate.

2. Last 135 pounds of fuel in forwardcell may not be usable.

3. Fuel will stop transferring fromfor wa rd to a f t fu e l ce l l a tapproximately 340 pounds totalindicated fuel.

PROCEDURE:

1. LEFT and RIGHT FUEL BOOST/XFRcircuit breaker switches — CheckON.

2. Determine FUEL QTY in forward cell.

3. Subtract quantity of fuel trapped inforward cell from total to determineusable fuel remaining.

4. Plan landing accordingly.

3-9. CYCLIC CAM JAM

A cyclic cam jam can only occur in the foreand aft axis, whereas, an actuator hardovercan occur in any flight control axis. A cycliccam jam is manifested when a commandedcontrol movement requires a higher thannormal fore and aft spring force. The force feltwhen moving the cyclic fore and aft with acam jam is the result of overriding a springcapsule.

INDICATIONS:

1. High (approximately 15 pounds) foreand aft cyclic control forces.

2. Normal pedal, collective and lateralcyclic control forces.

PROCEDURE:

1. Helicopter pitch attitude — Maintainnormal pitch attitudes with forwardor aft cyclic force.

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CAUTION

DO NOT TURN HYDRAULIC BOOSTOFF

2. Land as soon as practical.

3-10. WARNING, CAUTION, AND ADVISORY LIGHTS/MESSAGES

R ed wa rn in g l ig h ts /m essag es , fau l tcondit ions, and correct ive act ions arepresented in Table 3-1.

Amber caution and White advisory lights/mess age s a nd cor rec t ive ac t i on s a represented in Table 3-2.

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Table 3-1. Warning (red) lights

PANELWORDING FAULT CONDITION CORRECTIVE ACTION

BATTERY HOT Battery overheating. Turn BATT switch OFF and land as soon as practical. If BATTERY RLY light illuminates, turn GEN switch OFF if conditions permit. Land as soon as possible.

ENGINE OUT NG less than 55 ± 1% and/or FADEC senses ENGINE OUT.

Verify engine condition. Accomplish engine failure procedure.

ENGINE OVSPD NG greater than 110% or NP versus TORQUE is above maximum continuous limit (102.4% NP at 100% TORQUE to 108.6% NP at 0% TORQUE).

Adjust throttle and collective as necessary. Determine if engine is controllable, if not shut down. Maintenance action required before next flight.

FADEC FAIL(During start)

FADEC has detected a serious malfunction.

Close throttle immediately. Engage starter to reduce MGT. Applicable maintenance action required prior to next flight.

FADEC FAIL(Inflight) FADEC has detected a malfunction and an overspeed may occur 2 to 7 seconds following activation of FADEC fail horn and illumination of FADEC FAIL warning light. Engine may underspeed significantly prior to overspeed. Any other FADEC related lights may be illuminated.

Accomplish FADEC FAILURE procedure, paragraph 3-3-K. Applicable maintenance action required prior to next flight.

RPM(with low RPM audio)

NR below 95%. Reduce collective and ensure throttle is in FLY detent position. Light will extinguish and audio will cease when NR increases above 95%.

RPM(without audio) NR above 107%. Increase collective and/or reduce severity of maneuver. Light will extinguish when NR decreases below 107%.

XMSN OIL PRESS Transmission oil pressure is below minimum.

Reduce power; verify fault with gage. Land as soon as possible.

XMSN OIL TEMP Transmission oil temperature is at or above red line.

Reduce power; verify fault with gage. Land as soon as practical.

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Table 3-2. Caution (amber) and advisory (white/green) lights

PANELWORDING FAULT CONDITION CORRECTIVE ACTION

AUTO RELIGHT(white) Engine igniter is operating. None.

NOTE

AUTO RELIGHT light will beilluminated when ignition system isactivated.Ignition system isactivated:

1 - during start sequence

2 - in MANUAL mode with NGabove 55%

3 - with FADEC detection of engineout condition with NG above 50%.

BAGGAGE DOOR Baggage compartment door not securely latched.

Close door securely before flight. If light illuminates during flight, land as soon as practical.

BATTERY RLY Battery relay has malfunctioned to closed (ON) position with BATT switch OFF. Battery is still connected to DC BUSS.

If BATTERY HOT light is illuminated, turn GEN switch OFF if conditions permit. Land as soon as possible.

CHECK INSTR TRQ, MGT, or NG is about to or has detected an exceedance. Flashing LCD trend arc and digital display indicates impending exceedance. Letter E in digital display indicates an exceedance has occurred.

Reduce engine power if possible. Press INSTR CHK button to display magnitude of exceedance. Refer to BHT-407-MD-1.

CYCLIC CENTERING Cyclic stick is not centered. Reposition cyclic stick to center position to extinguish CYCLIC CENTERING light.

ENGAGED Information system status. None.

ENGINE ANTI-ICE (white)

ANTI-ICE switch ON. Engine receiving anti-icing air.

If light (if installed) remains illuminated with ENGINE ANTI-ICE switch OFF, avoid operations requiring maximum power.

ENGINE CHIP Ferrous particles in engine oil. Land as soon as possible.

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FADEC DEGRADED (Inflight)

FADEC ECU operation is degraded which may result in NR droop, NR lag, or reduced maximum power capability.

Remain in AUTO mode. Fly helicopter smoothly and nonaggressively. Land as soon as practical.

NOTE

It may be necessary to use FUELVALVE switch to shut down engineafter landing.

Applicable maintenance action required prior to next flight.

FADEC DEGRADED (With engine shutdown)

FADEC ECU has recorded a fault during previous flight or a current fault has been detected.

Position throttle to idle; if light extinguishes, fault is from previous flight. Applicable maintenance action required prior to next flight.

FADEC FAULT PMA and or MGT, NP or NG automatic limiting circuit(s) not functional.

Remain in AUTO mode. Land as soon as practical. Applicable maintenance action required prior to next flight.

FADEC MANUAL FADEC is operating in MANUAL mode. No automatic governing is available. AUTO RELIGHT light will be illuminated.

Fly helicopter smoothly and nonaggressively. Maintain NR with coordinated throttle and collective movements. Land as soon as practical.

FLOAT ARM FLOAT ARM switch is ON. Float inflation solenoid is armed.

Normal operation for takeoff and landing over water. FLOAT ARM switch — OFF. If light remains illuminated, FLOATS circuit breaker — Out. Land as soon as practical.

NOTE

With float inflation solenoid armed,flight should not exceed 60 KIAS and500 feet AGL.

FLOAT TEST (green) Float system in test mode. None.

Table 3-2. Caution (amber) and advisory (white/green) lights (Cont)

PANELWORDING FAULT CONDITION CORRECTIVE ACTION

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FUEL FILTER Airframe fuel filter in impending bypass.

Land as soon as practical. Clean before next flight.

FUEL LOW 100 ±10 pounds of fuel remain in aft tank.

Verify FUEL QTY. Land as soon as practical.

R/FUEL BOOST Right fuel boost pump has failed. If practical, descend below 8000 feet HP if fuel is Jet A or 4000 feet HP if

fuel is Jet B to prevent fuel starvation if other fuel boost pump fails or has low output pressure. Land as soon as practical.

NOTE

If either or both fuel boost pumpsfail, unusable fuel is unaffected.Corrective action is as per R/FUELBOOST or L/FUEL BOOST light.

L/FUEL BOOST Left fuel boost pump has failed. If practical, descend below 8000 feet HP if fuel is Jet A or 4000 feet HP if

fuel is Jet B to prevent fuel starvation if other fuel boost pump fails or has low output pressure. Land as soon as practical.

FUEL VALVE Fuel valve position differs from FUEL VALVE switch indication or FUEL VALVE circuit breaker out.

Check FUEL VALVE circuit breaker in. Land a soon as practical. If on ground, cycle FUEL VALVE switch.

L/FUEL XFR Left fuel transfer pump has failed.

Land as soon as practical.

Table 3-2. Caution (amber) and advisory (white/green) lights (Cont)

PANELWORDING FAULT CONDITION CORRECTIVE ACTION

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CAUTION

IF BOTH FUEL TRANSFER PUMPSFAIL, UNUSABLE FUEL MAY BE ASHIGH AS 135 POUNDS DUE TO IN-ABILITY TO TRANSFER FUEL FROMFORWARD CELL. LAND AS SOONAS PRACTICAL.

NOTE

Under normal fuel transferconditions, helicopters S/N 53000- 53174 L/FUEL XFR and R/FUELXFR lights will illuminate for 2 1/2minutes and then extinguish.This indicates transfer iscomplete and transfer pumpshave been automatically turnedoff. Helicopters S/N 53175 andsubsequent inhibit illuminationof the lights.

R/FUEL XFR Right fuel transfer pump has failed.

Land as soon as practical.

GEN FAIL Generator not connected to DC BUSS.

Verify fault with AMPS gage. GEN switch — RESET, then ON. If GEN FAIL light remains illuminated, GEN switch — OFF. Land as soon as practical.

HEATER OVERTEMP An overtemp condition has been detected by a temperature probe either under pilot seat, copilot seat, or in vertical tunnel.

Turn HEATER switch OFF immediately.

Table 3-2. Caution (amber) and advisory (white/green) lights (Cont)

PANELWORDING FAULT CONDITION CORRECTIVE ACTION

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HYDRAULIC SYSTEM Hydraulic pressure below limit. Verify HYD SYS switch position. Accomplish hydraulic system failure procedure (refer to paragraph 3-6).

LITTER DOOR Litter door not securely latched. Close door securely before flight. If light illuminates during flight, land as soon as practical.

PEDAL STOP Pedal Restrictor Control Unit has detected a failure of part of system.

VNE — 60 KIAS.

PEDAL STOP emergency release — Pull.

Land as soon as practical.

RESTART FAULT(white)

FADEC ECU has detected a fault which will not allow engine to be restarted in AUTO mode.

Remain in AUTO mode. Plan landing site accordingly.

Applicable maintenance action required prior to next flight

NOTE

When throttle is repositioned to idlestop (during engine shutdown) thePMA will go offline and engine mayflameout.

START(white)

Start relay is in START mode. If START switch has not been engaged and there is zero indication on AMPS gage; START relay has malfunctioned and helicopter is on battery power. START circuit breaker — Out. Land as soon as practical.

T/R CHIP Ferrous particles in tail rotor gearbox oil.

Land as soon as possible.

XMSN CHIP Ferrous particles in transmission oil.

Land as soon as possible.

Table 3-2. Caution (amber) and advisory (white/green) lights (Cont)

PANELWORDING FAULT CONDITION CORRECTIVE ACTION

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Section 4PERFORMANCE

4

Paragraph NumberPage

Subject

TABLE OF CONTENTS

INTRODUCTION ......................................................................... 4-1.................... 4-3POWER ASSURANCE CHECK.................................................. 4-2.................... 4-3DENSITY ALTITUDE................................................................... 4-3.................... 4-4HEIGHT – VELOCITY ENVELOPE............................................. 4-4.................... 4-4HOVER CEILING......................................................................... 4-5.................... 4-4NOT USED .................................................................................. 4-6.................... 4-5CLIMB AND DESCENT............................................................... 4-7.................... 4-5

CLIMB................................................................................... 4-7-A................ 4-5 AUTOROTATION ................................................................. 4-7-B................ 4-6

AIRSPEED CALIBRATION......................................................... 4-8.................... 4-6NOT USED .................................................................................. 4-9.................... 4-6NOISE LEVELS........................................................................... 4-10.................. 4-6

FAR PART 36 STAGE 2 NOISE LEVEL................................. 4-10-A.............. 4-6CANADIAN AIRWORTHINESS MANUAL CHAPTER 516 AND ICAO ANNEX 16 NOISE LEVEL............................. 4-10-B.............. 4-6

Figure Title Number Number

Page

LIST OF FIGURES

Power assurance check ............................................................ 4-1.................... 4-7Density altitude .......................................................................... 4-2.................... 4-8Altitude vs gross weight for height – velocity diagram ......... 4-3.................... 4-9Height – velocity diagram ......................................................... 4-4................... 4-10Hover ceiling wind accountability chart – below 14,000 feet HD................................................................ 4-5................... 4-11Hover ceiling wind accountability chart – between 14,000 and 17,000 feet HD ........................................ 4-5A ................ 4-12Hover ceiling wind accountability chart – above 17,000 feet HD ............................................................... 4-5B ................ 4-13Hover ceiling IGE ....................................................................... 4-6................... 4-14Hover ceiling OGE ..................................................................... 4-7................... 4-22Rate of climb – takeoff power ................................................... 4-8................... 4-30Rate of climb – maximum continuous power.......................... 4-9................... 4-40Autorotation glide distance ...................................................... 4-10................. 4-50Airspeed installation correction ............................................... 4-11................. 4-51

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Section 4PERFORMANCE

44-1. INTRODUCTION

Performance data presented herein arede r i ved f ro m en g in e ma nu fac tu r e 'ssp ec i f i ca t i on p ow er fo r en gi ne lessinstallation losses. These data are applicableto basic helicopter without any optionalequipment that would appreciably affect lift,drag, or power available.

4-2. POWER ASSURANCE CHECK

A Power assurance check chart (Figure 4-1) isprovided for Rolls-Royce model 250-C47Bengine. This chart ind ica tes max imumal lowab le M GT fo r an eng ine meet in gminimum Rolls-Royce specification. Enginemust develop required torque w i thoutexceeding char t MGT in order to meetperformance data contained in this manual.

Figure 4-1 may be used to periodicallymonitor engine performance.

To perform power assurance check, turn offall sources of bleed air, including ENGINEANTI-ICING. Establish level fl ight at anA IR SPE ED of 85 to 1 05 K IA S o r V N E ,whichever is lower. Check may also beconducted in a hover pr ior to takeoff ,depending on ambient conditions and grossweight.

Record following information from cockpitinstruments:

EXAMPLE:

SOLUTION:

Enter Power assurance check chart atobserved TORQUE (70%), proceed verticallydown to intersect HP (6000 feet), followhorizontally to intersect indicated OAT (10°C),then drop ver t ica l ly to read maximumallowable MGT.

If actual MGT is less than or equal to chartMGT, engine performance equals or exceedsminimum specification and performance datacontained in this manual can be achieved.

If actual MGT is greater than chart MGT,engine performance is less than minimumspeci fication and al l per formance datacontained in this manual cannot be achieved.Refer to appropriate maintenance manual todetermine cause of low power (high MGT).

NOTE

Chart may also be used to determineminimum specification power foractual MGT. Using above example,enter chart at actual MGT (675°C,proceed up to OAT (10°C), across to HP

(6000 feet), and up to read minimumtorque available (70%). If actual poweris equal to or greater than chart torque,engine performance equals or exceedsmi ni mu m sp ec i f ica t io n an dperformance data contained in thismanual can be achieved. I f actualtorque indication is less than charttorque, engine performance is lessthan minimum specification and allperformance in this manual cannot beach ie ved . R e fer to ap pr o pr ia temaintenance manual to determinecause of low power.

HP 6000 feet

OAT 10°C

MGT Actual reading

TORQUE 70%

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4-3. DENSITY ALTITUDE

A D ens i ty a l t i tud e a nd tem p era tu r econversion chart (Figure 4-2) is provided toaid in calcula t ion of per formance andlimitations. HD is an expression of density ofair in terms of height above sea level; hence,the less dense the air, the higher the HD. Forstandard conditions of temperature andpressure, HD is same as HP. As temperatureincreases above standard for an altitude, HDwill also increase to values higher than HP.Figure 4-2 expresses HD as a function of HPand temperature.

Density altitude chart also includes theinverse of the square root of the density ratio

(1 / ) , which is used to calculate trueairspeed by the following relation:

KTAS = KCAS×1/

EXAMPLE:

If ambient temperature is -15°C and HP is 7000

feet, find HD, 1/ , and true airspeed for 100KCAS.

SOLUTION:

Enter bottom of chart at -15°C.

Move vertically upward to 7000 feet HP

line.

From this point, move horizontally toleft and read HD of 5000 feet, move

horizontally to right and read 1/ =1.08.

True airspeed = KCAS × 1/ = 100 ×1.08 = 108 KTAS.

4-4. HEIGHT – VELOCITYENVELOPE

The He ight – Veloci ty envelope char ts(Figures 4-3 and 4-4) define conditions fromwhich a safe landing can be made on asmooth, level, firm surface; following anengine failure. The Height – Velocity diagram

(Figure 4-4) is valid only when helicoptergross weight does not exceed limits of theAltitude vs Gross Weight for Height – Velocitydiagram (Figure 4-3). Four envelopes (GrossWeight Regions) are specified. Each GrossWeight Region applies for all gross weightswithin its boundaries. No interpolation isallowed.

For a given ambient outside air temperature,pressure altitude, and gross weight, theappropriate limiting envelope (Region A, B, C,or D) can be determined. Using Figure 4-3(Altitude VS Gross Weight), move upwardvertically from entry OAT to pressure altitude.From that point, move right horizontally tod e term in e the co r rec t we i g ht re g i on .(Examples: 15°C at Sea Level at 5000 poundsGW = Region B, and 30°C a t 2000 fee tpressure alti tude at 5000 pounds GW =Region D) Once the correct weight region hasb een d e te r mi ned (A, B , C , o r D ) , thecorresponding Avoid area is selected fromFigure 4-4 (Height – Velocity diagram).

4-5. HOVER CEILING

NOTE

Hover performance charts are basedon 100% ROTOR RPM.

Satisfactory stability and control have beendemonstrated in each area of the Hoverceiling charts with winds as depicted on theHover ceiling wind accountabil ity chart(Figures 4-5, 4-5A and 4-5B).

Hover ceiling – in ground effect charts (Figure4-6) and Hover ceiling – out of ground effectcharts (Figure 4-7) present hover performanceas allowable gross weight for conditions of HPand OAT. These ho ver ing we igh ts a reobtainable in zero wind conditions. Eachchart is divided into two areas: Area A (nonshaded area) and Area B (shaded area).

For the data presented below 14,000 ft HD,Area A of the hover ceiling charts presentshover performance (relat ive to GW) forconditions where adequate control marginsexist for all relative wind conditions up to 35knots for lateral CG not exceeding ±2.5 inches(±63 mm); and up to 17 knots, for lateral CGnot exceeding ±4.0 inches (±102 mm); for

σ

σ

σ

σ

σ

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hover, takeoff and landing. Area B of theho ve r c e i l in g ch ar ts p re sen ts h o verperformance (relative to GW) for conditionswhere adequate control margins exist forrelative winds within ±45° of the nose ofhelicopter up to 35 knots for lateral CG notexceeding ±2.5 inches (±63 mm), and up to 17knots for lateral CG not exceeding ±4.0 inches(±102 mm); for hover, takeoff and landing.

For data presented between 14,000 and 17,000ft HD, Area A of the hover ceiling charts

presents hover performance (relative to GW)for condi tions where adequate controlmargins exist for all relative wind conditionsup to 20 knots for lateral CG not exceeding±2.5 inches (±63 mm); for hover, takeoff andlanding. Area B of the hover ceiling chartspresents recommended azimuth for takeoffand landing for all relative winds within ±30°of nose of helicopter for lateral CG notexceeding ±2.5 inches (±63 mm).

For data presented above 17,000 ft HD, there

is no A r ea A . A r ea B pre sents ho verperformance (relative to GW) for conditionswhere adequate control margins exist for allrelative winds within ±30° of the nose of thehelicopter for lateral CG not exceeding ±2.5inches (±63 mm); for hover, takeoff andlanding

The following example uses a Hover ceilingchart at takeoff power. The example is typicalfor use with all other Hover ceiling charts.

EXAMPLE:

What IGE GW hover capability could beexpected for the following conditions:

A. HEATER and ANTI ICE – OFFB. HP – 6000 feet

C. OAT – +20°CD. TAKE OFF POWER

SOLUTION:

Use Hover ceiling IGE – takeoff power chart(sheet 1 of Figure 4-6).

A. Enter OAT scale at +20 °C.B. Move upward to 6000 feet HP curve.C. Move horizontally to +20 °C curve.D. Drop down to read maximum

external gross weight of 5400 pounds (IGE hover capability exceeds maximum internal GW of 5000 pounds).

4-6. NOT USED

4-7. CLIMB AND DESCENT

4-7-A. CLIMB

Rate of climb charts are presented for variouscombinations of power settings and ENGINEANTI-ICING switch positions. Refer to Figures4-8 and 4-9.

Recommended best rate of climb airspeed is60 KIAS.

Reduce rate of climb data 100 feet per minutewhen operating with any combination ofdoor(s) removed.

The following example uses a Rate of climbchart at takeoff power. The example is typicalfor use with all other Rate of climb charts.

EXAMPLE:

Find the maximum rate of climb that can beattained using takeoff power under thefollowing conditions:

HEATER OFF

ENGINE ANTI-ICING OFF

OAT 10°C

HP 14,000 feet

GW 3500 pounds

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SOLUTION:

Enter appropriate gross weight chart (sheet 3of Figure 4-8). At HP scale of 14000 feetproceed horizontally to temperature of 10°C.Drop down vertically and read a rate of climbof 1700 feet per minute.

4-7-B. AUTOROTATION

Refer to Figure 4-10 for autorotational glidedistance as a function of altitude.

4-8. AIRSPEED CALIBRATION

Refer to Figure 4-11 for airspeed installationcorrection during level flight and climb.

4-9. NOT USED

4-10. NOISE LEVELS

4-10-A. FAR PART 36 STAGE 2NOISE LEVEL

Thi s a i rc ra ft i s cer t i f ied as a S tag e 2helicopter as prescribed in FAR Part 36,Subpart H, for gross weights up to andincluding the certificated maximum takeoffand landing weight of 5000 pounds (2268kilograms). There are no operating limitationsto meet any of the noise requirements.

The following noise level complies with FARPart 36, Appendix J, Stage 2 noise levelrequirements. It was obtained by analysis ofapproved data from noise tests conductedun d er th e p ro v i s io n s of FA R Par t 36 ,Amendment 36-20.

The certified flyover noise level for the Model407 is 85.1 dBA SEL.

NOTE

No determination has been made bythe certifying authorities that the noise

levels of this aircraft are or should beacce ptab l e o r u n accep tab le fo roperat ions at, into, or out of anyairport.

VH is defined as the airspeed in level flight

obtained using the minimum specificationengine torque corresponding to maximumcontinuous power available for sea level, 25°C(77°F) ambient conditions at the relevantmaximum certificated weight. The value of VH

thus defined for this aircraft is 127 KTAS.

4-10-B. CANADIAN AIRWORTHINESS MANUAL CHAPTER 516 AND ICAO ANNEX 16 NOISE LEVEL

This aircraft complies with the noise emissionstandards applicable to the aircraft as set outb y the I n te rn a t i on a l C i v i l Av i a t io nOrganization (ICAO) in Annex 16, Volume 1,Chapter 11, for gross weights up to andincluding the certificated maximum takeoffand landing weight of 5000 pounds (2268kilograms). There are no operating limitationsto meet any of the noise requirements.

The following noise level complies with ICAOAnnex 16, Volume 1, Chapter 11 noise levelrequirements. It was obtained by analysis ofapproved data from noise tests conductedunder the provisions of ICAO Annex 16,Volume 1, Third Edition-1993.

The flyover noise level for the Model 407 is84.6 dBA SEL.

NOTE

ICAO Annex 16, Volume 1, Chapter 11approval is applicable only af terendorsement by the Civil AviationAuthority of the country of aircraftregistration.

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4

Figure 4-1. Power assurance check

BASIC INLET

MODEL 407 POWER ASSURANCE CHECK - ROLLS ROYCE 250-C47B ENGINEHOVER OR LEVEL FLIGHT (85 TO 105 KIAS - NOT TO EXCEED VNE)

48

58

68

78

88

98

108

118

128

138

148

175 200 225 250 275 300 325 350 375 400 425 450 475 500 525 550 575 600 625 650 675 700 725 750 775

MEASURED GAS TEMPERATURE - DEG.C

35 9085807570656055504540 10095

ENGINE TORQUE - PERCENTGENERATOR LOAD 35 AMPS OR LESS

POWER TURBINE - 100% RPMHEATER / ECS OFF

ANTI-ICE OFF

EXAMPLE: ENTER CHART AT OBSERVED TORQUE (70%)PROCEED VERTICALLY DOWN TO PRESSURE ALTITUDE (6,000 FT.)FOLLOW HORIZONTALLY TO THE RIGHT TO OBSERVED OAT (10 DEG.C)DROP DOWN TO READ MAXIMUM ALLOWABLE MGT (675 DEG.C)

M407FM1 FIG 4-1.WMF

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Figure 4-2. Density altitude

-50 -40 -30 -20 -10 0 10 20 30 40 50 60

OUTSIDE AIR TEMPERATURE - °C

-8

-6

-4

-2

0

2

4

6

8

10

12

14

16

18

20

22

24

DE

NS

ITY

AL

TIT

UD

E -

FT

x 1

00

0

0.90

0.92

0.94

0.96

0.98

1.00

1.02

1.04

1.06

1.08

1.10

1.12

1.14

1.16

1.18

1.20

1.22

1.24

1.26

1.28

1.30

1.32

1.34

1.36

1.38

1.40

1.421.441.46

25,000

SEA LEVEL

STA

ND

AR

D D

AY

5,000

-5,000

10,000

15,000

20,000

PRESSURE ALTITUDE - FT

-10,000

1 /

σ

EXAMPLE: If OAT is -15°C andHP is 7000 ft, HD is 5000 ft

and is 1.081 / σ

M407_FM-1__FIG_4-2.WMF

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Figure 4-3. Altitude vs gross weight for height – velocity diagram

ALTITUDE VS GROSS WEIGHTFOR HEIGHT-VELOCITY DIAGRAM

13 14 15 16 17 18 19 20 21 22

GROSS WEIGHT - KG x 100

-40 -20 0 20 40 60

OAT - °C

30 34 38 42 46 50

GROSS WEIGHT - LBS x 100

8000

6000

4000

2000

SEA LEVEL

Hp

- FT

10,0

00

14,000 FT HD

MA

XIM

UM

OA

T

-200

0

MIN

IMU

M O

AT

LIM

IT

12,0

00

14,0

00

MA

XIM

UM

INT

ER

NA

L G

RO

SS

WE

IGH

T

DEMONSTRATEDTO 9000 FEET

DENSITY ALTITUDE

9000 FT HD

GR

OSS

WEIG

HT R

EGIO

NS

A

B

C

D

M407_FM-1__FIG_4-3.EMF

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Figure 4-4. Height – velocity diagram

0 10 20 30 40 50 60 70 80 90 100 110 120

INDICATED AIRSPEED - KNOTS

0

50

100

150

200

250

300

350

400

450

500

550

600

650

700

750

800

SK

ID H

EIG

HT

- F

EE

T

HEIGHT-VELOCITY DIAGRAMFOR GROSS WEIGHT REGIONS A TO D

0

20

40

60

80

100

120

140

160

180

200

220

240

SK

ID H

EIG

HT

- M

ET

ER

S

NOTE: LOW HOVER POINT IS AT 6 FT SKID HEIGHT

AVOID

AV

OID

AR

EA

S

REG

ION "A" BELO

W TH

IS LINE

RE

GIO

N "B

" BE

LOW

THIS

LINE

RE

GIO

N "C

" BE

LOW

THIS

LINE

RE

GIO

N "D

" BE

LOW

THIS

LINE

M407_FM-1__FIG_4-4.EMF

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17 DEC 2002 4-11

Figure 4-5. Hover ceiling wind accountability chart – below 14,000 feet HD

± 45°

ALLAZIMUTHS

SHADED AREA (AREA B)

(± 102 mm); FOR HOVER, TAKEOFF AND LANDING.

PRESENTS HOVER PERFORMANCE (RELATIVE TO GW) FOR CONDITIONS WHERE ADEQUATE CONTROL MARGINS EXIST FOR RELATIVE WINDS WITHIN ± 45° OF NOSE OF HELICOPTER UP TO 35 KNOTS FOR LATERAL CG NOT EXCEEDING ± 2.5 INCHES (± 63 mm), AND UP TO 17 KNOTS FOR LATERAL CG NOT EXCEEDING ± 4.0 INCHES

NON-SHADED AREA (AREA A)

(± 102 mm); FOR HOVER, TAKEOFF AND LANDING.

PRESENTS HOVER PERFORMANCE (RELATIVE TO GW) FOR CONDITIONS WHERE ADEQUATE CONTROL MARGINS EXIST FOR ALL RELATIVE WIND CONDITIONS UP TO 35 KNOTS FOR LATERAL CG NOT EXCEEDING ± 2.5 INCHES (± 63 mm), AND UP TO 17 KNOTS FOR LATERAL CG NOT EXCEEDING ± 4.0 INCHES

ALTITUDE BELOW14000 FT HD

M407_FM-1_FIG_4-5.WMF

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Figure 4-5A. Hover ceiling wind accountability chart – between 14,000 and 17,000 feet HD

ALLAZIMUTHS

SHADED AREA (AREA B)PRESENTS RECOMMENDED AZIMUTH FOR TAKEOFF AND LANDING FOR ALL RELATIVE WINDS WITHIN ± 30° OF NOSE OF HELICOPTER FOR LATERAL CG NOT EXCEEDING ± 2.5 INCHES (± 63 mm).

NON-SHADED AREA (AREA A)PRESENTS HOVER PERFORMANCE (RELATIVE TO GW) FOR CONDITIONS WH ERE AD EQUAT E C ONT ROL MARGINS EXIST FOR ALL RELATIVE WIND CONDITIONS UP TO 20 KNOTS FOR LATERAL CG NOT EXCEEDING ± 2.5 INCHES (± 63 mm); FOR HOVER, TAKEOFF AND LANDING.

ALTITUDE BETWEEN14000 AND 17000 FT HD

± 30°

M407_FM-1__FIG_4-5A.WMF

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Figure 4-5B. Hover ceiling wind accountability chart – above 17,000 feet HD

ALTITUDE ABOVE17000 FT HD

SHADED AREA (AREA B)PRESENTS HOVER PERFORMANCE ( R E L A T I V E T O G W ) F O R CONDITIONS WHERE ADEQUATE CONTROL MARGINS EXIST FOR ALL WINDS DIRECTLY OFF THE NOSE OF THE HELICOPTER; FOR HOVER, TAKEOFF AND LANDING.

M407_FM-1_FIG_4-5B.WMF

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Figure 4-6. Hover ceiling IGE (sheet 1 of 8)

HOVER CEILINGIN GROUND EFFECT

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE OFF

BASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100M

AX

IMU

M O

AT

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

51.7

5040

30

20

10

0

-10

-30-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FM-1__FIG_4-6_(1_OF_8).WMF

MAX DEMONSTRATED HD

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Figure 4-6. Hover ceiling IGE (sheet 2 of 8)

HOVER CEILINGIN GROUND EFFECT

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)ANTI-ICE ONBASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

5

0-10

-30

-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FM-1__FIG_4-6_(2_OF_8).WMF

MAX DEMONSTRATED HD

Page 92: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-16 17 DEC 2002

Figure 4-6. Hover ceiling IGE (sheet 3 of 8)

HOVER CEILINGIN GROUND EFFECT

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER ON

BASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

2010

0-10

-30-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FM-1__FIG_4-6_(3_OF_8).WMF

MAX DEMONSTRATED HD

Page 93: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-17

Figure 4-6. Hover ceiling IGE (sheet 4 of 8)

HOVER CEILINGIN GROUND EFFECT

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE ON

BASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

50

-10

-30-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FM-1__FIG_4-6_(4_OF_8).WMF

MAX DEMONSTRATED HD

Page 94: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-18 17 DEC 2002

Figure 4-6. Hover ceiling IGE (sheet 5 of 8)

HOVER CEILINGIN GROUND EFFECT

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE OFF

BASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

MA

XIM

UM

OA

T20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

OAT - °C

51.750

4030

20

100

-10-30

-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

EX

TE

RN

AL

= 6

000 L

B

MA

X G

W IN

TE

RN

AL

= 5

000 L

B

M407_FM-1__FIG_4-6_(5_OF_8).EMF

MAX DEMONSTRATED HD

Page 95: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-19

Figure 4-6. Hover ceiling IGE (sheet 6 of 8)

HOVER CEILINGIN GROUND EFFECT

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)ANTI-ICE ONBASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

50

-10

-30-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FM-1__FIG_4-6_(6_OF_8).WMF

MAX DEMONSTRATED HD

Page 96: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-20 17 DEC 2002

Figure 4-6. Hover ceiling IGE (sheet 7 of 8)

HOVER CEILINGIN GROUND EFFECT

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER ON

BASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

2010

0-10

-30-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FM-1__FIG_4-6_(7_OF_8).EMF

MAX DEMONSTRATED HD

Page 97: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-21

Figure 4-6. Hover ceiling IGE (sheet 8 of 8)

HOVER CEILINGIN GROUND EFFECT

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE ON

BASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

50

-10

-30-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FM-1__FIG_4-6_(8_OF_8).WMF

MAX DEMONSTRATED HD

Page 98: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-22 17 DEC 2002

Figure 4-7. Hover ceiling OGE (sheet 1 of 8)

HOVER CEILINGOUT OF GROUND EFFECT

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)HEATER AND ANTI-ICE OFF

BASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

MA

XIM

UM

OA

T

OAT - °C

51.750

40

30

20

10

0

-10

-30

-40

-20

M407_FM-1__FIG_4-7_(1_OF_8).WMF

MAX DEMONSTRATED HD

Page 99: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-23

Figure 4-7. Hover ceiling OGE (sheet 2 of 8)

HOVER CEILINGOUT OF GROUND EFFECT

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)ANTI-ICE ONBASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

OAT - °C

-20

50

-10

-30

-40

M407_FM-1__FIG_4-7_(2_OF_8).WMF

MAX DEMONSTRATED HD

Page 100: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-24 17 DEC 2002

Figure 4-7. Hover ceiling OGE (sheet 3 of 8)

HOVER CEILINGOUT OF GROUND EFFECT

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)HEATER ON

BASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

OAT - °C

-2020

100

-10

-30-40

M407_FM-1__FIG_4-7_(3_OF_8).WMF

MAX DEMONSTRATED HD

Page 101: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-25

Figure 4-7. Hover ceiling OGE (sheet 4 of 8)

HOVER CEILINGOUT OF GROUND EFFECT

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)HEATER AND ANTI-ICE ON

BASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

OAT - °C

-20

50

-10

-30

-40

M407_FM-1__FIG_4-7_(4_OF_8).WMF

MAX DEMONSTRATED HD

Page 102: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-26 17 DEC 2002

Figure 4-7. Hover ceiling OGE (sheet 5 of 8)

HOVER CEILINGOUT OF GROUND EFFECT

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)HEATER AND ANTI-ICE OFF

BASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

MA

XIM

UM

OA

T

OAT - °C

51.750

4030

200

-10

-30-40

10-20

M407_FM-1__FIG_4-7_(5_OF_8).EMF

MAX DEMONSTRATED HD

Page 103: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-27

Figure 4-7. Hover ceiling OGE (sheet 6 of 8)

HOVER CEILINGOUT OF GROUND EFFECT

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)ANTI-ICE ONBASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

OAT - °C

-205

0-10

-30-40

M407_FM-1__FIG_4-7_(6_OF_8).WMF

MAX DEMONSTRATED HD

Page 104: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-28 17 DEC 2002

Figure 4-7. Hover ceiling OGE (sheet 7 of 8)

HOVER CEILINGOUT OF GROUND EFFECT

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)HEATER ON

BASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

OAT - °C

-2020

100

-10

-30-40

M407_FM-1__FIG_4-7_(7_OF_8).EMF

MAX DEMONSTRATED HD

Page 105: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-29

Figure 4-7. Hover ceiling OGE (sheet 8 of 8)

HOVER CEILINGOUT OF GROUND EFFECT

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)HEATER AND ANTI-ICE ON

BASIC INLET

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

OAT - °C

-205

0-10

-30-40

M407_FM-1__FIG_4-7_(8_OF_8).EMF

MAX DEMONSTRATED HD

Page 106: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-30 17 DEC 2002

Figure 4-8. Rate of climb – takeoff power (sheet 1 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 225 FT/MIN ABOVE15,000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 3000 lb (1361 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X OA

T LIMIT

OAT-°C

30

20

10

0

-10

M407_FM-1__FIG_4-8_(1_OF_10).WMF

Page 107: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-31

Figure 4-8. Rate of climb – takeoff power (sheet 2 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 225 FT/MIN ABOVE11,000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 3000 lb (1361 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

BASIC INLET

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X O

AT LIM

IT

OAT-°C

-20

20

10

0

-10

-30

M407_FM-1__FIG_4-8_(2_OF_10).WMF

Page 108: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-32 17 DEC 2002

Figure 4-8. Rate of climb – takeoff power (sheet 3 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 190 FT/MIN ABOVE11,500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 3500 lb (1587 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X O

AT LIM

IT

OAT-°C

30

20

10

0

-10

-20-30-40

40

M407_FM-1__FIG_4-8_(3_OF_10).WMF

Page 109: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-33

Figure 4-8. Rate of climb – takeoff power (sheet 4 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 190 FT/MIN ABOVE7500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 3500 lb (1587 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

BASIC INLET

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

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M407_FM-1__FIG_4-8_(4_OF_10).WMF

Page 110: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-34 17 DEC 2002

Figure 4-8. Rate of climb – takeoff power (sheet 5 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 170 FT/MIN ABOVE9000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 4000 lb (1814 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

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M407_FM-1__FIG_4-8_(5_OF_10).WMF

Page 111: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-35

Figure 4-8. Rate of climb – takeoff power (sheet 6 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 170 FT/MIN ABOVE4500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 4000 lb (1814 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

BASIC INLET

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M407_FM-1__FIG_4-8_(6_OF_10).WMF

Page 112: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-36 17 DEC 2002

Figure 4-8. Rate of climb – takeoff power (sheet 7 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 150 FT/MIN ABOVE6500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 4500 lb (2041 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

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M407_FM-1__FIG_4-8_(7_OF_10).WMF

Page 113: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-37

Figure 4-8. Rate of climb – takeoff power (sheet 8 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 150 FT/MIN ABOVE2000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 4500 lb (2041 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

BASIC INLET

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M407_FM-1__FIG_4-8_(8_OF_10).WMF

Page 114: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-38 17 DEC 2002

Figure 4-8. Rate of climb – takeoff power (sheet 9 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 135 FT/MIN ABOVE5000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 5000 lb (2268 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

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M407_FM-1__FIG_4-8_(9_OF_10).WMF

Page 115: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-39

Figure 4-8. Rate of climb – takeoff power (sheet 10 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 135 FT/MIN ABOVE1000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 5000 lb (2268 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

BASIC INLET

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M407_FM-1__FIG_4-8_(10_OF_10).WMF

Page 116: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-40 17 DEC 2002

Figure 4-9. Rate of climb – maximum continuous power (sheet 1 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 225 FT/MIN ABOVE10,000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 3000 lb (1361 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

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M407_FM-1__FIG_4-9_(1_OF_10).WMF

Page 117: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-41

Figure 4-9. Rate of climb – maximum continuous power (sheet 2 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 225 FT/MIN ABOVE6000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 3000 lb (1361 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

BASIC INLET

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M407_FM-1__FIG_4-9_(2_OF_10).WMF

Page 118: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-42 17 DEC 2002

Figure 4-9. Rate of climb – maximum continuous power (sheet 3 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 190 FT/MIN ABOVE7500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 3500 lb (1587 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

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M407_FM-1__FIG_4-9_(3_OF_10).WMF

Page 119: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-43

Figure 4-9. Rate of climb – maximum continuous power (sheet 4 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 190 FT/MIN ABOVE2500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 3500 lb (1587 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

BASIC INLET

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M407_FM-1__FIG_4-9_(4_OF_10).WMF

Page 120: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-44 17 DEC 2002

Figure 4-9. Rate of climb – maximum continuous power (sheet 5 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 170 FT/MIN ABOVE5000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 4000 lb (1814 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

0 200 400 600 800 1000 1200 1400 1600 1800 2000

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M407_FM-1__FIG_4-9_(5_OF_10).WMF

Page 121: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-45

Figure 4-9. Rate of climb – maximum continuous power (sheet 6 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 170 FT/MINFOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 4000 lb (1814 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

BASIC INLET

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M407_FM-1__FIG_4-9_(6_OF_10).WMF

Page 122: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-46 17 DEC 2002

Figure 4-9. Rate of climb – maximum continuous power (sheet 7 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 150 FT/MIN ABOVE3000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 4500 lb (2041 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

0 200 400 600 800 1000 1200 1400 1600 1800 2000

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M407_FM-1__FIG_4-9_(7_OF_10).WMF

Page 123: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-47

Figure 4-9. Rate of climb – maximum continuous power (sheet 8 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 150 FT/MINFOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 4500 lb (2041 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

BASIC INLET

0 200 400 600 800 1000 1200 1400 1600 1800 2000

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M407_FM-1__FIG_4-9_(8_OF_10).WMF

Page 124: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-48 17 DEC 2002

Figure 4-9. Rate of climb – maximum continuous power (sheet 9 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 135 FT/MIN ABOVE3000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 5000 lb (2268 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

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M407_FM-1__FIG_4-9_(9_OF_10).WMF

Page 125: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-49

Figure 4-9. Rate of climb – maximum continuous power (sheet 10 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 135 FT/MINFOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 5000 lb (2268 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

BASIC INLET

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M407_FM-1__FIG_4-9_(10_OF_10).WMF

Page 126: Bell 407 - Flight Manual, POH

BHT-407-FM-1 TC APPROVED

4-50 17 DEC 2002

Figure 4-10. Autorotation glide distance

AUTOROTATION GLIDE DISTANCE

0 1 2 3 4 5 6 7 8 9 10 11 12 13 14

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NOTE: AUTOROTATIONAL DESCENTPERFORMANCE IS A FUNCTION OFAIRSPEED AND IS ESSENTIALLYUNAFFECTED BY DENSITY ALTITUDEAND GROSS WEIGHT.

Minimum Rate ofDescent Airspeed 55 KIAS

Maximum Glide DistanceAirspeed 80 KIAS

M407_FM-1__FIG_4-10.EMF

Page 127: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FM-1

17 DEC 2002 4-51/4-52

Figure 4-11. Airspeed installation correction

AIRSPEED INSTALLATION CORRECTION TABLEKCAS = (KIAS – INSTRUMENT ERROR – POSITION ERROR)

NOTE: This chart assumes zero instrument error.

KIASCLIMBKCAS

LEVEL FLIGHTKCAS

20 – – 22

30 30 33

40 37 43

50 47 52

60 58 63

70 69 73

80 78 82

90 87 92

100 95 100

110 – – 110

120 – – 121

130 – – 131

140 – – 144

M407_FM-1_FIG_4-11.WMF

Page 128: Bell 407 - Flight Manual, POH

BHT-407-FM-1

17 DEC 2002 5-1

Section 5WEIGHT AND BALANCE

5x

Paragraph NumberPage

Subject

TABLE OF CONTENTS

INTRODUCTION ......................................................................... 5-1.................... 5-3EMPTY WEIGHT CENTER OF GRAVITY .................................. 5-2.................... 5-3

EMPTY WEIGHT ................................................................. 5-2-A................ 5-3CENTER OF GRAVITY ....................................................... 5-2-B................ 5-3

GROSS WEIGHT CENTER OF GRAVITY.................................. 5-3.................... 5-3USEFUL LOADS ................................................................. 5-3-A................ 5-3CENTER OF GRAVITY ....................................................... 5-3-B................ 5-3

DOORS OPEN OR REMOVED ................................................... 5-4.................... 5-4DOOR WEIGHTS AND MOMENTS .................................... 5-4-A................ 5-4BALLAST ADJUSTMENT................................................... 5-4-B................ 5-4

COCKPIT AND CABIN LOADING.............................................. 5-5.................... 5-4LONGITUDINAL LOADING ................................................ 5-5-A................ 5-5MOST FORWARD AND MOST AFT CG ............................ 5-5-B................ 5-5ALTERNATE LOADING...................................................... 5-5-C................ 5-5CABIN FLOOR LOADING................................................... 5-5-D................ 5-5

BAGGAGE COMPARTMENT LOADING ................................... 5-6.................... 5-5FUEL LOADING .......................................................................... 5-7.................... 5-6SAMPLE LOADING PROBLEM ................................................. 5-8.................... 5-6

Figure Title Number Number

Page

LIST OF FIGURES

Fuselage stations....................................................................... 5-1.................... 5-7Buttock lines .............................................................................. 5-2.................... 5-8Fuel center of gravity................................................................. 5-3.................... 5-9

Title Number

TableNumberPage

LIST OF TABLES

Door Weights and Moments (U.S.) ........................................... 5-1................... 5-10Cabin and baggage loading (U.S.)............................................ 5-2................... 5-11Cabin and baggage loading (Metric) ........................................ 5-3................... 5-12Fuel Loading (U.S.) .................................................................... 5-4................... 5-13Fuel Loading (Metric)................................................................. 5-5................... 5-14

Page 129: Bell 407 - Flight Manual, POH

BHT-407-FM-1

5-2 17 DEC 2002

Title Number

TableNumberPage

LIST OF TABLES (CONT)

Fuel Density vs Temperature.................................................... 5-6 .................. 5-15Sample Loading Problem (U.S.) ............................................... 5-7 .................. 5-16Sample Loading Problem (Metric)............................................ 5-8 .................. 5-17Weight and Balance Worksheet (U.S.)..................................... 5-9 .................. 5-18Weight and Balance Worksheet (Metric) ................................. 5-10 ................ 5-19

Page 130: Bell 407 - Flight Manual, POH

BHT-407-FM-1

17 DEC 2002 5-3

Section 5WEIGHT AND BALANCE

55-1. INTRODUCTION

This section presents loading information andinstructions necessary to ensure that flightcan be performed within approved grossweight and center of gravity limitations as

defined in Section 1.

5-2. EMPTY WEIGHT CENTER OF GRAVITY

5-2-A. EMPTY WEIGHT

The empty weight condition consists of thebasic helicopter with required equipment,optional equipment kits, transmission andgearbox oils, hydraulic fluid, unusable fuel,undrainable engine oil, and fixed ballast. Theempty weight and center of gravity arerecorded on the Actual Weight Record, a copyof which should be carried in the helicopter toenable weight and balance computations.

5-2-B. CENTER OF GRAVITY

An empty weight center of gravity chart isprovided in maintenance manual as a guide tosimplify computing ballast requirements. Thisch ar t was der iv ed f ro m gr o ss w e ig h tlongitudinal center of gravity limits shown inSection 1, using most forward and most aftuseful loads for standard seating and fuel.

NOTE

Empty weight center of gravity chartis n ot va l id i f h e l i co pter has anonstandard fuel system or seatingarrangement.

5-3. GROSS WEIGHT CENTER OF GRAVITY

Gross weight condition is empty weightcondition plus useful load.

5-3-A. USEFUL LOADS

Useful load consists of usable fuel, engine oil,crew, passengers, baggage and cargo.Combinations of these items which have mostadverse effect on helicopter center of gravityare known as most forward and most aftuseful loads. Whenever cargo and/or baggageare carried , these useful loads may bedifferent for each flight, and weight andbalance must be computed to ensure grossweight and center of gravity will remain withinlimits throughout flight.

Standard most forward and most aft usefulloads are combinations of fuel, crew andpassenger loading only. These loads, inconjunction with empty weight center ofgravity chart, allow passengers only (nobaggage or other cargo) to be carried withinappropr iate weight l im itat ions withoutcomputing center of gravity for each flight.

If helicopter has a nonstandard fuel system orseating arrangement, or is not ballasted inaccordance with empty weight center ofgravity chart in maintenance manual, pilotmust determine weight and balance to ensuregross weight and center of gravity will remainwithin limits throughout each flight.

5-3-B. CENTER OF GRAVITY

It is the responsibility of the pilot to ensurethat helicopter is properly loaded to maintain

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5-4 17 DEC 2002

center of gravity throughout each flight withingross weight center of gravity limits shown inSection 1 or appropriate supplement. Grossweight longitudinal and lateral center ofgravity can be calculated using Actual WeightRecord, diagrams and loading tables in thissection and loading tables in applicable flightmanual supplements.

W he n c arr y i ng b ag ga ge , car g o orno n stan d ard l oad s , e f fec ts o f fu e lconsumpt ion and addi t ion/delet ion ofpa ssen g ers , b ag ga ge or car g o a tintermediate points should be checked priorto flight.

Significant fuselage stations and buttocklines are shown in Figures 5-1 and 5-2 to aidin weight and balance computations.

5-4. DOORS OPEN OR REMOVED

When one or more cabin doors are removed,helicopter may exceed gross weight center ofgravity limits during flight. If using Weightempty center of gravity chart, refer to BHT-407-MM-1, a ballast adjustment to offsetmoment change is necessary (Table 5-1).Otherwise, gross weight center of gravityshould be computed for each flight.

5-4-A. DOOR WEIGHTS AND MOMENTS

Following table presents weight and momentadjustments for cabin doors. Sign conventionfor buttock lines used to compute lateralmoments are:

1. Left is negative.

2. Right is positive.

Example:

When removing a left door only, subtractpositive weight value and negative momentvalue shown in table. Net effect on helicopteris a reduction in weight and a shift in lateralCG to right (positive direction).

5-4-B. BALLAST ADJUSTMENT

Following check can be made to determine ifa ballast adjustment is necessary after doorsare removed or installed.

1. For helicopters without ballast orwith nose ballast, apply weight andmoment changes to most aft usefulload condition to determine if anincrease in nose ballast is required,or a reduction is allowed.

2. For helicopters with tail ballast,apply weight and moment changesto mo st fo rw ard u se fu l lo adcondition to determine if a reductionin tai l ballast is a l lowed, or anincrease is required.

NOTE

Ballast changes are performed bymaintenance personnel. After anyballast change, Actual Weight Recordmust be revised to show new weight

empty condition.

5-5. COCKPIT AND CABIN LOADING

Loading tables (Tables 5-2 and 5-3) provideweights and moments for each passengerlo ca t i on , l i t t e r p a t ien t an d b ag g agecompartment in both U.S. and metric units.

To find moments for weights in excess ofthose shown on tables, multiply weight byfuselage station at which center of gravity of

ACTION MOMENT CHANGE

LEFT DOOR RIGHT DOOR

Remove Positive (+) Negative (-)Install Negative (-) Positive (+)

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17 DEC 2002 5-5

the object is located. An alternate method isto calculate amount of weight in excess ofmaximum weight listed on table, then readmoment for this excess weight from table andadd it to moment for maximum weight shownon table. This will give desired moment for theobject.

5-5-A. LONGITUDINAL LOADING

1. A minimum weight of 170 pounds(77 .1 k i lograms) is required incockpit at fuselage station 65.0when the empty weight center ofgravity chart is used.

2. Passenger seating is unrestricted.

3. Cargo loading is restricted only byfloor load limit. Refer to Section 1.

5-5-B. MOST FORWARD AND MOST AFT CG

When using empty weight center of gravitychart, following combinations of crew, fueland passenger loading w il l have mostextreme effects on longitudinal center ofgravity, assuming standard weights for allcrew and passengers.

1. Most forward CG will occur withforward and mid seats occupied andfuel quantity of 74.8 gallons (283.0liters).

2. Most aft CG will occur with oneforward seat occupied (pilot) andfuel quantity of 28.4 gallons (107.5liters).

Since center of gravity of aft passengers is onaft limit, weight of passengers is not includedin most aft useful load. However when mostaft center of gravity of a configuration isforward of aft limit, addition of aft passengerswill shift center of gravity further aft, andshould be included in computation.

5-5-C. ALTERNATE LOADING

Gross weight center of gravity chart must beused to determine cabin loading requirementsunder following conditions:

1. Whenever cargo and/or baggage arecarried.

2. When actual passenger weights areused.

3. When seating arrangement and/orfuel system are non-standard.

4. When performing specialty missions,such as hoisting or rappelling.

5-5-D. CABIN FLOOR LOADING

Cabin floor is structurally designed for 75pounds per square foot (3.7 kilograms per 100square centimeters).

5-6. BAGGAGE COMPARTMENT LOADING

W he n we i gh t i s l oa ded i n to bag g ag ecompartment, the pilot is required to computeweight and balance, regardless of passengerloading.

Bagg ag e compartment is s t ruc tura l lydesigned for 86 pounds per square foot (4.2kilograms per 100 square centimeters) for atotal weight of 250 pounds (113.4 kilograms).

Loading of baggage compartment should befrom front to rear. Load shall be secured totiedown fittings if shifting of load in flightcould result in structural damage to baggagecompartment or in gross weight center ofgravity being exceeded.

If load is not secured, center of gravity mustbe computed with load in most adverseposition.

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5-7. FUEL LOADING

Longitudinal center of gravity of fuel shifts asit is consumed (Figure 5-3). Extreme effects offuel consumption on helicopter center ofgravity for standard fuel system are asfollows:

1. Critical fuel for computing mostforward useful load is 74.8 gallons(283.0 liters).

2. Critical fuel for computing most aftuseful load is 28.4 gallons (107.5liters).

Fuel loading tables (Tables 5-4 and 5-5) listusable fuel quantities, weight and moments inboth U.S. and metric units.

Fuel density vs temperature (Table 5-6), isprovided to calculate fuel weight variation forequivalent volumes of fuel caused by achange in temperature. For example weight of

127.8 gallons (full fuel) of JP-5 at -40°F is913.8 pounds (414.5 kilograms) versus 869.0pounds (394.1 kilograms) shown on Fuelloading chart (Tables 5-4 and 5-5).

5-8. SAMPLE LOADING PROBLEM

A sample loading problem showing derivationof critical gross weights and center of gravitylocations for a typical mission is presented inU.S. and metric units (Tables 5-7 and 5-8).Method shown derives a gross weight withzero fuel for each load condit ion to bechecked, then adds appropriate fuel weightand moment read directly from Fuel loadingtable. Center of gravity for each condition iscalculated by dividing total moment by totalweight.

Forms have been provided (Tables 5-9 and 5-10) in both U.S. and Metric Units, to aid incomputing critical load conditions for a flight.

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17 DEC 2002 5-7

Figure 5-1. Fuselage stations

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5-8 17 DEC 2002

Figure 5-2. Buttock lines

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17 DEC 2002 5-9

Figure 5-3. Fuel center of gravity

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5-10 17 DEC 2002

Table 5-1. Door Weights and Moments (U.S.)

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17 DEC 2002 5-11

Table 5-2. Cabin and baggage loading (U.S.)

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5-12 17 DEC 2002

Table 5-3. Cabin and baggage loading (Metric)

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17 DEC 2002 5-13

Table 5-4. Fuel Loading (U.S.)

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5-14 17 DEC 2002

Table 5-5. Fuel Loading (Metric)

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17 DEC 2002 5-15

Table 5-6. Fuel Density vs Temperature

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5-16 17 DEC 2002

Table 5-7. Sample Loading Problem (U.S.)

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17 DEC 2002 5-17

Table 5-8. Sample Loading Problem (Metric)

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5-18 17 DEC 2002

Table 5-9. Weight and Balance Worksheet (U.S.)

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Table 5-10. Weight and Balance Worksheet (Metric)

17 DEC 2002 5-19/5-20

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Appendix AOPTIONAL EQUIPMENT SUPPLEMENTS

A

Paragraph NumberPage

Subject

TABLE OF CONTENTS

OPTIONAL EQUIPMENT ............................................................ A-1 ................... A-3

Title Number

TableNumberPage

LIST OF TABLES

Flight Manual Supplements for Optional Equipment ............. A-1 ................... A-3

17 DEC 2002 A-1/A-2

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29 NOV 2004 Rev. 2 A-3

BHT-407-FM-1

Appendix AOPTIONAL EQUIPMENT SUPPLEMENTS

AA-1. OPTIONAL EQUIPMENTBell Helicopter Textron's policy is one ofcontinuous product improvement and Bellreserves the right to incorporate changes,make additions to and improve its productswithout imposing any obligation upon thecompany to furnish for or instal l such

changes, additions, improvement, etc., on itsproducts previously manufactured.

The following items may be installed on thebasic helicopter by authorized personnel.Only the optional equipment listed in thissection require a Flight Manual Supplement.

Table A-1. Flight Manual Supplements for Optional Equipment

NAME OF EQUIPMENT KIT NUMBERDATECERTIFIED

CURRENTREVISION

BHT-407-FMS-1 Lightweight Emergency Flotation Landing Gear

407-706-008 11 APR 96 Original

BHT-407-FMS-2 High Skid Gear

407-706-007 14 FEB 96 Original

BHT-407-FMS-3 Particle Separator

206-706-212 1 MAR 96 Reissue 16 DEC 02

BHT-407-FMS-4 Snow Deflector

206-706-208 1 MAR 96 Reissue 16 DEC 02

BHT-407-FMS-5 Cargo Hook

206-706-341 14 FEB 96 Rev. 104 SEP 98

BHT-407-FMS-6 Auxiliary Fuel Kit

407-706-011 20 MAR 96 Original

BHT-407-FMS-7 Litter(s) Kit

407-706-631 or407-799-100 or407-799-001

14 FEB 96 Rev. 116 SEP 99

BHT-407-FMS-10 Helicopters Registered In U.S.A.

CANCELLED

BHT-407-FMS-17 Cargo Tie-down Provisions Kit

407-705-201 1 APR 96 Original

BHT-407-FMS-20 KLN 89B GPS Navigator

407-705-001 14 FEB 96 Rev. 1 26 NOV 96

BHT-407-FMS-21 Fire Detection System

407-799-004 or 407-706-015

2 MAY 96 Reissue 08 SEP 98

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A-4 Rev. 2 29 NOV 2004

BHT-407-FMS-22 Auxiliary Vertical Fin Strobe Lights

407-899-023 10 MAY 96 Original

BHT-407-FMS-23 Ryan Traffic Collision Avoidance Device

407-899-022 15 MAY 96 Original

BHT-407-FMS-25 Quiet Cruise Mode

407-706-016 8 MAY 98 Reissue 17 DEC 02

BHT-407-FMS-26 Modified Hydromechanical Unit

CANCELED

BHT-407-FMS-27 FADEC Software 5.201

CANCELED

BHT-407-FMS-28 Increased Internal Gross Weight

407-706-020 16 MAR 99 Reissue 16 DEC 02

BHT-407-FMS-29Airspeed Actuated Pedal Stop

CANCELED

BHT-407-FMS-CAA United KingdomRegistered Helicopters

08 JAN 02 Original

BHT-407-FMS-IAC ARInterstate Aviation Committee — Aviation Register Commonwealth of Independent States

407-706-021 20 MAY 99 Original

BHT-407-FMS-32Hanger Bearing Vibration Monitor Kit(not distributed to all customers)

407-706-023 15 July 03 Original

Table A-1. Flight Manual Supplements for Optional Equipment (Cont)

NAME OF EQUIPMENT KIT NUMBERDATECERTIFIED

CURRENTREVISION

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BHT-407-FMS-3

ROTORCRAFTFLIGHT MANUAL

SUPPLEMENT

PARTICLE SEPARATOR206-706-212

CERTIFIED1 MARCH 1996

This supplement shall be attached to Model 407 FlightManual when Particle Separator is installed.

Information contained herein supplements informationof basic Flight Manual. For limitations, Procedures, andPerformance Data not contained in this supplement,consult basic Flight Manual.

REISSUED — 16 DECEMBER 2002

2002

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BHT-407-FMS-3

NP 16 DEC 2002

Additional copies of this publication may be obtained by contacting:Commercial Publication Distribution Center

Bell Helicopter Textron Inc.P. O. Box 482

Fort Worth, Texas 76101-0482

NOTICE PAGE

Manufacturer’s Data portion of this supplement is proprietary to BellHelicopter Textron Inc. Disclosure, reproduction, or use of these data forany purpose other than helicopter operation is forbidden without priorwritten authorization from Bell Helicopter Textron Inc.

PROPRIETARY RIGHTS NOTICE

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NOTE

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

LOG OF REVISIONS

Original ....................... 0................... 01 MAR 96Revision...................... 1................... 01 MAY 97Revision...................... 2................... 04 SEP 98

Revision ......................3 ................... 17 APR 00Reissue........................0 ................... 16 DEC 02

LOG OF PAGES

REVISION REVISIONNO. NO.PAGE PAGE

FLIGHT MANUAL

Title............................................................ 0NP.............................................................. 0A — B ........................................................ 0C/D............................................................. 0i/ii ............................................................... 01 — 38 ....................................................... 039/40 .......................................................... 0

MANUFACTURER’S DATA

41/42 ..........................................................0

16 DEC 2002 A

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LOG OF TC APPROVED REVISIONS

Original ........................0 ................... 01 MAR 96Revision.......................1 ................... 01 MAY 97Revision.......................2 ................... 04 SEP 98Revision.......................3 ................... 17 APR 00Reissue ........................0 ................... 16 DEC 02

B 16 DEC 2002

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LOG OF FAA APPROVED REVISIONS

Original ....................... 0................... 01 MAR 96Revision...................... 1....................01 MAY 97Revision...................... 2....................18 MAY 99

Revision ......................3 ................... 05 MAY 00Reissue........................0 .................... 24 SEP 03

16 DEC 2002 C/D

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BHT-407-FMS-3

GENERAL INFORMATION

Bell particle separator kit (206-706-212)consists of particle separator, bleed air tubingand hose, electrical cable and requiredhardware for installation.

This supplement incorporates performanceinformation for various combinations of Bell

kits. It also includes limitations and operatingprocedures made necessary because of kitcombina t ions . This supplement is notintended to replace approved supplementsfor other optional equipment, but should beused in conjunction with such supplements.

16 DEC 2002 i/ii

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TC APPROVED BHT-407-FMS-3

16 DEC 2002 1

Section 1LIMITATIONS

11-3. TYPES OF OPERATION

Particle separator can be removed and theengine air intake screen installed to attainbasic helicopter performance.

1-5. CONFIGURATION

1-5-A. OPTIONAL EQUIPMENT

For operat ions with part ic le separatorinstalled in conjunction with 206-706-208

snow deflector, refer to LIMITATIONS sectionan d PE RF OR M A N CE se c t io n o f sn owdeflector supplement (BHT-407-FMS-4).

1-6. WEIGHT AND CENTER OF GRAVITY

Actual weight change shall be determinedafter kit is installed and ballast readjusted, ifnecessary, to return empty weight CG towithin allowable limits.

1

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Section 2NORMAL PROCEDURES

22-7. BEFORE TAKEOFF

1. PART SEP purge switch – Asrequired.

2-7-A. BEFORE FLIGHT WHEN OPERATING IN SNOW CONDITIONS

1. Thoroughly check cabin roof ,transmission cowling, deflectorbaffles and engine air intake areas.All areas checked shall be clean andfree of accumulated snow, slush, andice before each flight.

2. Check engine air plenum chamberthrough plexiglass windows on eachside of inlet cowling for snow, slush,or ice, paying particular attention tofirewalls and rear face of particleseparator. Clean thoroughly beforeeach flight.

2-9. IN-FLIGHT OPERATIONS

1. PART SEP purge switch – Asrequired.

2-10. DESCENT AND LANDING

1. PART SEP purge switch – Asrequired.

Section 3EMERGENCY/MALFUNCTION PROCEDURES

3No change from basic manual.

Section 4PERFORMANCE

44-2. POWER ASSURANCE

CHECK

Per fo rmance is r ed uced w i th par t ic leseparator installed. This reduction increases

with use of particle separator purge and isprimarily result of bleed air being taken fromengine. A Power assurance check chart(Figure 4-1) is provided to determine if enginecan produce installed power.

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16 DEC 2002 3

4

Figure 4-1. Power assurance check

PARTICLE SEPARATOR KIT

MODEL 407 POWER ASSURANCE CHECK - ROLLS ROYCE 250-C47B ENGINEHOVER OR LEVEL FLIGHT (85 TO 105 KIAS - NOT TO EXCEED VNE)

48

58

68

78

88

98

108

118

128

138

175 200 225 250 275 300 325 350 375 400 425 450 475 500 525 550 575 600 625 650 675 700 725 750 775

MEASURED GAS TEMPERATURE - DEG.C

35 9085807570656055504540 10095

ENGINE TORQUE - PERCENT

PARTICLE SEPARATOR PURGE OFF

GENERATOR LOAD 35 AMPS OR LESS

POWER TURBINE - 100% RPM

HEATER / ECS OFF

ANTI-ICE OFF

EXAMPLE: ENTER CHART AT OBSERVED TORQUE (70%)

PROCEED VERTICALLY DOWN TO PRESSURE ALTITUDE (6,000 FT.)

FOLLOW HORIZONTALLY TO THE RIGHT TO OBSERVED OAT (10 DEG.C)

DROP DOWN TO READ MAXIMUM ALLOWABLE MGT (681 DEG.C)

407FMS3 FIG 4-1 REV A.WMF

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Figure 4-2. Hover ceiling IGE – takeoff power (sheet 1 of 4)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE OFF

PARTICLE SEPARATOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100M

AX

IMU

M O

AT

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

51.750

4030

20

10

0

-10

-30-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-3_FIG 4-2 (1_OF_4).WMF

MAX DEMONSTRATED HD

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16 DEC 2002 5

Figure 4-2. Hover ceiling IGE – takeoff power (sheet 2 of 4)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)ANTI-ICE ON

PARTICLE SEPARATOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

5

0

-10

-30

-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-3__FIG_4-2_(2_OF_4).WMF

MAX DEMONSTRATED HD

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Figure 4-2. Hover ceiling IGE – takeoff power (sheet 3 of 4)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER ON

PARTICLE SEPARATOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

2010

0-10

-30-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-3__FIG_4-2_(3_OF_4).WMF

MAX DEMONSTRATED HD

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Figure 4-2. Hover ceiling IGE – takeoff power (sheet 4 of 4)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE ON

PARTICLE SEPARATOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

50

-10-30

-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-3__FIG_4-2_(4_OF_4).WMF

MAX DEMONSTRATED HD

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Figure 4-3. Hover ceiling IGE – maximum continuous power (sheet 1 of 4)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE OFF

PARTICLE SEPARATOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

MA

XIM

UM

OA

T

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

51.7

50

4030

20

100

-10-30

-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-3__FIG_4-3_(1_OF_4).EMF

MAX DEMONSTRATED HD

Page 183: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

16 DEC 2002 9

Figure 4-3. Hover ceiling IGE – maximum continuous power (sheet 2 of 4)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)ANTI-ICE ON

PARTICLE SEPARATOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

50

-10-30

-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-3__FIG_4-3_(2_OF_4).WMF

MAX DEMONSTRATED HD

Page 184: Bell 407 - Flight Manual, POH

BHT-407-FMS-3 TC APPROVED

10 16 DEC 2002

Figure 4-3. Hover ceiling IGE – maximum continuous power (sheet 3 of 4)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER ON

PARTICLE SEPARATOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

2010

0-10

-30-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-3__FIG_4-3_(3_OF_4).EMF

MAX DEMONSTRATED HD

Page 185: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

16 DEC 2002 11

Figure 4-3. Hover ceiling IGE – maximum continuous power (sheet 4 of 4)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE ON

PARTICLE SEPARATOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

50

-10-30

-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-3__FIG_4-3_(4_OF_4).EMF

MAX DEMONSTRATED HD

Page 186: Bell 407 - Flight Manual, POH

BHT-407-FMS-3 TC APPROVED

12 16 DEC 2002

Figure 4-4. Hover ceiling OGE – takeoff power (sheet 1 of 4)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE OFF

PARTICLE SEPARATOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

HOVER CEILING

OUT OF GROUND EFFECT

REFER TO

FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-3__FIG_4-4_(1_OF_4).EPS

Page 187: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

16 DEC 2002 13

Figure 4-4. Hover ceiling OGE – takeoff power (sheet 2 of 4)

HOVER CEILINGOUT OF GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)ANTI-ICE ON

PARTICLE SEPARATOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

14,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

17,000 FT HD

8000

14,0

00

6000

4000

2000

12,0

00

SEA LEVEL

-200

0

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

-20

50

-10

-30

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5

AREA B

M407_FM S- 3__F IG_4-2_(2_OF_4).WMF

Page 188: Bell 407 - Flight Manual, POH

BHT-407-FMS-3 TC APPROVED

14 16 DEC 2002

Figure 4-4. Hover ceiling OGE – takeoff power (sheet 3 of 4)

HOVER CEILING

OUT OF GROUND EFFECT

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER ON

PARTICLE SEPARATOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

REFER TO FIG. 4-5

REFER TO

FIG. 4-5A

M407_FMS-3__FIG_4-4_(3_OF_4).EPS

Page 189: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

16 DEC 2002 15

Figure 4-4. Hover ceiling OGE – takeoff power (sheet 4 of 4)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE ON

PARTICLE SEPARATOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

HOVER CEILING

OUT OF GROUND EFFECT

REFER TO FIG. 4-5

REFER TO

FIG. 4-5A

M407_FMS-3__FIG_4-4_(4_OF_4).EPS

Page 190: Bell 407 - Flight Manual, POH

BHT-407-FMS-3 TC APPROVED

16 16 DEC 2002

Figure 4-5. Hover ceiling OGE – maximum continuous power (sheet 1 of 4)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE OFF

PARTICLE SEPARATOR

HOVER CEILING

OUT OF GROUND EFFECT

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

REFER TO

FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-3__FIG_4-5_(1_OF_4).EPS

Page 191: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

16 DEC 2002 17

Figure 4-5. Hover ceiling OGE – maximum continuous power (sheet 2 of 4)

HOVER CEILINGOUT OF GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)ANTI-ICE ON

PARTICLE SEPARATOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

14,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

17,000 FT HD

8000

14,0

00

6000

4000

2000

12,0

00

SEA LEVEL

-200

0

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

-205

0-10

-30-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-3__FIG_4-5_(2_OF_4).WMF

Page 192: Bell 407 - Flight Manual, POH

BHT-407-FMS-3 TC APPROVED

18 16 DEC 2002

Figure 4-5. Hover ceiling OGE – maximum continuous power (sheet 3 of 4)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER ON

PARTICLE SEPARATOR

HOVER CEILING

OUT OF GROUND EFFECT

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

REFER TO

FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-3__FIG_4-5_(3_OF_4).EPS

Page 193: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

16 DEC 2002 19

Figure 4-5. Hover ceiling OGE – maximum continuous power (sheet 4 of 4)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE ON

PARTICLE SEPARATOR

HOVER CEILING

OUT OF GROUND EFFECT

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

REFER TO

FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-3__FIG_4-5_(4_OF_4).EPS

Page 194: Bell 407 - Flight Manual, POH

BHT-407-FMS-3 TC APPROVED

20 16 DEC 2002

Figure 4-6. Rate of climb takeoff power (sheet 1 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 225 FT/MIN ABOVE14,500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 70 FT/MIN FOR PURGE ON

Gross Weight 3000 lb (1361 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFF

PARTICLE SEPARATORPURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X OA

T LIMIT

OAT-°C

30

20

10

0

-10-20

M407_FMS-3__FIG_4-6_(1_OF_10).WMF

Page 195: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

16 DEC 2002 21

Figure 4-6. Rate of climb takeoff power (sheet 2 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 225 FT/MIN ABOVE10,500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 70 FT/MIN FOR PURGE ON

Gross Weight 3000 lb (1361 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

PARTICLE SEPARATORPURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X O

AT LIM

IT

OAT-°C

20

10

0

-10

-20

-30

M407_FMS-3__FIG_4-6_(2_OF_10).WMF

Page 196: Bell 407 - Flight Manual, POH

BHT-407-FMS-3 TC APPROVED

22 16 DEC 2002

Figure 4-6. Rate of climb takeoff power (sheet 3 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 190 FT/MIN ABOVE11,000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 60 FT/MIN FOR PURGE ON

Gross Weight 3500 lb (1587 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFF

PARTICLE SEPARATORPURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X O

AT LIM

IT

OAT-°C

30

20

10

0

-10 -20

-30-40

40

50

M407_FMS-3__FIG_4-6_(3_OF_10).WMF

Page 197: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

16 DEC 2002 23

Figure 4-6. Rate of climb takeoff power (sheet 4 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 190 FT/MIN ABOVE7500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 60 FT/MIN FOR PURGE ON

Gross Weight 3500 lb (1587 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

PARTICLE SEPARATORPURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X O

AT LIM

IT

OAT-°C

20

10

0

-10

-20

-30

-40

M407_FMS-3__FIG_4-6_(4_OF_10).WMF

Page 198: Bell 407 - Flight Manual, POH

BHT-407-FMS-3 TC APPROVED

24 16 DEC 2002

Figure 4-6. Rate of climb takeoff power (sheet 5 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 170 FT/MIN ABOVE8500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 55 FT/MIN FOR PURGE ON

Gross Weight 4000 lb (1814 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFF

PARTICLE SEPARATORPURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X OA

T LIMIT

OAT-°C

30

20

10

0

-10

-20 -30

-40

40

50

M407_FMS-3__FIG_4-6_(5_OF_10).WMF

Page 199: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

16 DEC 2002 25

Figure 4-6. Rate of climb takeoff power (sheet 6 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 170 FT/MIN ABOVE4500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 55 FT/MIN FOR PURGE ON

Gross Weight 4000 lb (1814 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

PARTICLE SEPARATORPURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MAX O

AT LIMIT

OAT-°C

20

10

0

-10

-20

-30

-40

M407_FMS-3__FIG_4-6_(6_OF_10).WMF

Page 200: Bell 407 - Flight Manual, POH

BHT-407-FMS-3 TC APPROVED

26 16 DEC 2002

Figure 4-6. Rate of climb takeoff power (sheet 7 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 150 FT/MIN ABOVE6000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 50 FT/MIN FOR PURGE ON

Gross Weight 4500 lb (2041 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFF

PARTICLE SEPARATORPURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X OA

T LIMIT

OAT-°C

30

20

10

0

-10

-20

-30

-40

40

50

M407_FMS-3__FIG_4-6_(7_OF_10).WMF

Page 201: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

16 DEC 2002 27

Figure 4-6. Rate of climb takeoff power (sheet 8 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 150 FT/MIN ABOVE1500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 50 FT/MIN FOR PURGE ON

Gross Weight 4500 lb (2041 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

PARTICLE SEPARATORPURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

OAT-°C

20

10

0

-10

-20

-30

-40

M407_FMS-3__FIG_4-6_(8_OF_10).WMF

Page 202: Bell 407 - Flight Manual, POH

BHT-407-FMS-3 TC APPROVED

28 16 DEC 2002

Figure 4-6. Rate of climb takeoff power (sheet 9 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 135 FT/MIN ABOVE4500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 45 FT/MIN FOR PURGE ON

Gross Weight 5000 lb (2268 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFF

PARTICLE SEPARATORPURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X OA

T LIMIT

OAT-°C

30

20

10

0

-10

-20

-30

-40

40

50

M407_FMS-3__FIG_4-6_(9_OF_10).WMF

Page 203: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

16 DEC 2002 29

Figure 4-6. Rate of climb takeoff power (sheet 10 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 135 FT/MIN ABOVE500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 45 FT/MIN FOR PURGE ON

Gross Weight 5000 lb (2268 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

PARTICLE SEPARATORPURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

OAT-°C

20

10

0

-10

-20

-30

-40

M407_FMS-3__FIG_4-6_(10_OF_10).WMF

Page 204: Bell 407 - Flight Manual, POH

BHT-407-FMS-3 TC APPROVED

30 16 DEC 2002

Figure 4-7. Rate of climb maximum continuous power (sheet 1 of 10)

407FMS-3-4-7-1.TIF

Page 205: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

16 DEC 2002 31

Figure 4-7. Rate of climb maximum continuous power (sheet 2 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 225 FT/MIN ABOVE5500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 70 FT/MIN FOR PURGE ON

Gross Weight 3000 lb (1361 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

PARTICLE SEPARATORPURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X O

AT L

IMIT

OAT-°C

20

10

0

-10

-20

-30

-40

M407_FMS-3__FIG_4-7_(2_OF_10).WMF

Page 206: Bell 407 - Flight Manual, POH

BHT-407-FMS-3 TC APPROVED

32 16 DEC 2002

Figure 4-7. Rate of climb maximum continuous power (sheet 3 of 10)

407FMS-3-4-7-3.TIF

Page 207: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

16 DEC 2002 33

Figure 4-7. Rate of climb maximum continuous power (sheet 4 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 190 FT/MIN ABOVE2500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 60 FT/MIN FOR PURGE ON

Gross Weight 3500 lb (1587 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

PARTICLE SEPARATORPURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X O

AT LIM

IT

OAT-°C20

10

0

-10

-20

-30

-40

M407_FMS-3__FIG_4-7_(4_OF_10).WMF

Page 208: Bell 407 - Flight Manual, POH

BHT-407-FMS-3 TC APPROVED

34 16 DEC 2002

Figure 4-7. Rate of climb maximum continuous power (sheet 5 of 10)

407FMS-3-4-7-5.TIF

Page 209: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

16 DEC 2002 35

Figure 4-7. Rate of climb maximum continuous power (sheet 6 of 10)

407FMS-3-4-7-6.TIF

Page 210: Bell 407 - Flight Manual, POH

BHT-407-FMS-3 TC APPROVED

36 16 DEC 2002

Figure 4-7. Rate of climb maximum continuous power (sheet 7 of 10)

407FMS-3-4-7-7.TIF

Page 211: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

16 DEC 2002 37

Figure 4-7. Rate of climb maximum continuous power (sheet 8 of 10)

407FMS-3-4-7-8.TIF

Page 212: Bell 407 - Flight Manual, POH

BHT-407-FMS-3 TC APPROVED

38 16 DEC 2002

Figure 4-7. Rate of climb maximum continuous power (sheet 9 of 10)

407FMS-3-4-7-9.TIF

Page 213: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-3

Figure 4-7. Rate of climb maximum continuous power (sheet 10 of 10)

407FMS-3-4-7-10.TIF

16 DEC 2002 39/40

Page 214: Bell 407 - Flight Manual, POH

MANUFACTURER’S DATA BHT-407-FMS-3

Section 1SYSTEMS DESCRIPTION

This kit is equipped with a PART SEP switchlocated on overhead console. When switch isOFF, engine bleed air is not used to purge

debris from particle separator. When switch isON, engine bleed is used to purge debris.

16 DEC 2002 41/42

Page 215: Bell 407 - Flight Manual, POH

BHT-407-FMS-4

ROTORCRAFTFLIGHT MANUAL

SUPPLEMENT

SNOW DEFLECTOR206-706-208

CERTIFIED1 MARCH 1996

This supplement shall be attached to Model 407 FlightManual when Snow Deflector kit is installed.

Information contained herein supplements Informationof basic Flight Manual. For limitations, Procedures, andPerformance Data not contained in this supplement,consult basic Flight Manual

REISSUED — 16 DECEMBER 2002

2002

Page 216: Bell 407 - Flight Manual, POH

BHT-407-FMS-4

NP 16 DEC 2002

Additional copies of this publication may be obtained by contacting:Commercial Publication Distribution Center

Bell Helicopter Textron Inc.P. O. Box 482

Fort Worth, Texas 76101-0482

NOTICE PAGE

Manufacturer’s Data portion of this supplement is proprietary to BellHelicopter Textron Inc. Disclosure, reproduction, or use of these data forany purpose other than helicopter operation is forbidden without priorwritten authorization from Bell Helicopter Textron Inc.

PROPRIETARY RIGHTS NOTICE

Page 217: Bell 407 - Flight Manual, POH

BHT-407-FMS-4

NOTE

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

LOG OF REVISIONS

Original ....................... 0....................01 MAR 96Revision...................... 1....................27 MAY 97Revision...................... 2....................04 SEP 98

Revision ......................3 ................... 17 APR 00Reissue........................0 ................... 16 DEC 02

LOG OF PAGES

REVISION REVISIONNO. NO.PAGE PAGE

FLIGHT MANUAL

Title............................................................ 0NP.............................................................. 0A — B ........................................................ 0

C/D .............................................................0i/ii ...............................................................01 — 76........................................................0

16 DEC 2002 A

Page 218: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

LOG OF TC APPROVED REVISIONS

Original ........................0 ...................01 MAR 96Revision.......................1 ...................27 MAY 97Revision.......................2 ...................04 SEP 98

Revision ...................... 3 ................... 17 APR 00Reissue ....................... 0.................... 16 DEC 02

B 16 DEC 2002

Page 219: Bell 407 - Flight Manual, POH

BHT-407-FMS-4

LOG OF FAA APPROVED REVISIONS

Original ....................... 0................... 01 MAR 96Revision...................... 1................... 27 MAY 97Revision...................... 2................... 18 MAY 99

Revision ......................3 ................... 05 MAY 00Reissue........................0 ....................24 SEP 03

16 DEC 2002 C/D

Page 220: Bell 407 - Flight Manual, POH

BHT-407-FMS-4

GENERAL INFORMATION

Snow deflector kit (206-706-208) consists oftwo deflectors that mount on either side of

transmission fairing, just forward of engineair inlets.

16 DEC 2002 i/ii

Page 221: Bell 407 - Flight Manual, POH

16 DEC 2002 1

TC APPROVED BHT-407-FMS-4

Section 1LIMITATIONS

11-3. TYPES OF OPERATION

Snow deflector kit shall be installed foroperation in falling or blowing snow. Theymay be installed with basic inlet screen orparticle separator kit (206-706-212).

1-6. WEIGHT AND CENTER OF GRAVITY

Actual weight changes shall be determinedafter kit is installed and ballast readjusted, ifnecessary, to return empty weight CG to withinallowable limits. Refer to Center of gravity vsweight empty chart in BHT-407-MM-1.

1-11. AMBIENT TEMPERATURES

Snow def lectors shal l be removed foroperations above 30°C (86°F).

1-22. SNOW OPERATION

For operation in falling or blowing snow,thefollowing limits apply:

Hover flight in falling and/or blowing snow is limited to 15 minute duration after which helicopter shall be landed and checked for snow and/or ice accumulation.

Flight operations are prohibited when visibility in falling or blowing snow is less than one-half (1/2) statute mile.

Page 222: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

2 16 DEC 2002

Section 2NORMAL PROCEDURES

22-3. PREFLIGHT CHECK

2-3-A. EXTERIOR CHECK

2-3-A-1. OPERATION IN FALLING OR BLOWING SNOW

1. Thoroughly check cabin roof, transmission fairing, deflector baffles, and engine air intake areas. All areas checked shall be clean and free of accumulated snow, slush, and ice before each flight.

NOTE

Due to reduced performance at highertemperatures, it is recommended thatsnow deflectors be removed above20°C (68°F).

2. Particle separator kit (if installed), check engine air plenum chamber through plexiglass windows on each side of inlet cowling for snow, slush, or ice, paying particular attention to firewalls and rear face of particle separator. Clean thoroughly before each flight.

2-3-A-2. AFTER EXITING HELICOPTER

WARNING

F AI LU R E T O I N ST AL L EN GI N EINTAKE COVERS COULD ALLOWFALLING/BLOWING SNOW TO ENTERTHE PARTICLE SEPARATOR PLENUM(IF INSTALLED).

Instal l protective covers (engine intake,exhaust, and pitot tube).

Section 3EMERGENCY/MALFUNCTION PROCEDURES

3No change from basic manual.

Page 223: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-4

16 DEC 2002 3

Section 4PERFORMANCE

4

4-1. INTRODUCTION

Refer to appropriate performance charts inaccordance with optional equipment installed.

NOTE

Due to reduced performance at highertemperatures, it is recommended thatsnow deflectors be removed above20°C (68°F).

4-2. POWER ASSURANCE CHECK

Power assurance check chart Figure 4-1.

Performance is reduced with snow bafflesinstalled. Power assurance check chart(Figure 4-1) is provided to determine if enginecan p r od u ce in s ta l led po wer. Pow erassurance check shall be conducted in levelflight only. This chart is valid for both basicinlet with snow deflectors installed and snowdeflectors with particle separator installed.PARTICLE SEP PRG switch (if installed) shallbe OFF when performing a power assurancecheck.

4-5. HOVER CEILING

4-5-A. HOVER CEILING IN-GROUND-EFFECT

Hover ceiling IGE (takeoff power) charts arepresented in Figure 4-2, and Hover ceiling IGE(maximum continuous power) charts arepresented in Figure 4-3.

4-5-B. HOVER CEILING OUT-OF-GROUND-EFFECT

Hover ceiling OGE (takeoff power) charts arepresented in Figure 4-4, and Hover ceilingOGE (maximum continuous power) charts arepresented in Figure 4-5.

4-7. CLIMB AND DESCENT

4-7-A. RATE OF CLIMB

Rate of climb (takeoff power) charts arepresented in Figure 4-6, Rate of c l imb(maximum continuous power) charts arepresented in Figure 4-7, Rate of climb (takeoffpower) (par t ic le separator ) char ts a represented in Figure 4-8, and Rate of climb(maximum cont inuous power) (par tic leseparator) charts are presented in Figure 4-9.

Page 224: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

4 16 DEC 2002

Figure 4-1. Power assurance check chart

SNOW DEFLECTOR KIT

MODEL 407 POWER ASSURANCE CHECK - ROLLS ROYCE 250-C47B ENGINELEVEL FLIGHT (85 TO 105 KIAS - NOT TO EXCEED VNE)

48

58

68

78

88

98

108

118

128

175 200 225 250 275 300 325 350 375 400 425 450 475 500 525 550 575 600 625 650 675 700 725 750 775

MEASURED GAS TEMPERATURE - DEG.C

35 9085807570656055504540 10095

ENGINE TORQUE - PERCENT

PARTICLE SEPARATOR PURGE OFFGENERATOR LOAD 35 AMPS OR LESS

POWER TURBINE - 100% RPMHEATER / ECS OFF

ANTI-ICE OFF

EXAMPLE: ENTER CHART AT OBSERVED TORQUE (70%)PROCEED VERTICALLY DOWN TO PRESSURE ALTITUDE (6,000 FT.)

FOLLOW HORIZONTALLY TO THE RIGHT TO OBSERVED OAT (10 DEG.C)DROP DOWN TO READ MAXIMUM ALLOWABLE MGT (721 DEG.C)

407FMS4 FIG 4-1.WMF

Page 225: Bell 407 - Flight Manual, POH

16 DEC 2002 5

TC APPROVED BHT-407-FMS-4

Figure 4-2. Hover ceiling IGE – takeoff power (sheet 1 of 8)

HOVER CEILINGIN GROUND EFFECT

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE OFF

BASIC INLETSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

MA

XIM

UM

OA

T20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

3020

10

0

-10

-30-20

-40 REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-2_(1_OF_8).WMF

MAX DEMONSTRATED HD

Page 226: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

6 16 DEC 2002

Figure 4-2. Hover ceiling IGE – takeoff power (sheet 2 of 8)

HOVER CEILINGIN GROUND EFFECT

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)ANTI-ICE ONBASIC INLET

SNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

50

-10

-30

-20-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-2_(2_OF_8).WMF

MAX DEMONSTRATED HD

Page 227: Bell 407 - Flight Manual, POH

16 DEC 2002 7

TC APPROVED BHT-407-FMS-4

Figure 4-2. Hover ceiling IGE – takeoff power (sheet 3 of 8)

HOVER CEILINGIN GROUND EFFECT

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER ON

BASIC INLETSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

2010

0-10

-30-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-2_(3_OF_8).WMF

MAX DEMONSTRATED HD

Page 228: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

8 16 DEC 2002

Figure 4-2. Hover ceiling IGE – takeoff power (sheet 4 of 8)

HOVER CEILINGIN GROUND EFFECT

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE ON

BASIC INLETSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

50

-10-30

-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-2_(4_OF_8).WMF

MAX DEMONSTRATED HD

Page 229: Bell 407 - Flight Manual, POH

16 DEC 2002 9

TC APPROVED BHT-407-FMS-4

Figure 4-2. Hover ceiling IGE – takeoff power (sheet 5 of 8)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE OFF

PARTICLE SEPARATORSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

MA

XIM

UM

OA

T20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

3020

100

-10

-30-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-2_(5_OF_8).WMF

MAX DEMONSTRATED HD

Page 230: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

10 16 DEC 2002

Figure 4-2. Hover ceiling IGE – takeoff power (sheet 6 of 8)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)ANTI-ICE ON

PARTICLE SEPARATORSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

50

-10

-30

-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-2_(6_OF_8).WMF

MAX DEMONSTRATED HD

Page 231: Bell 407 - Flight Manual, POH

16 DEC 2002 11

TC APPROVED BHT-407-FMS-4

Figure 4-2. Hover ceiling IGE – takeoff power (sheet 7 of 8)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER ON

PARTICLE SEPARATORSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

2010

0-10

-30-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-2_(7_OF_8).WMF

MAX DEMONSTRATED HD

Page 232: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

12 16 DEC 2002

Figure 4-2. Hover ceiling IGE – takeoff power (sheet 8 of 8)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE ON

PARTICLE SEPARATORSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

50

-10-30

-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-2_(8_OF_8).WMF

MAX DEMONSTRATED HD

Page 233: Bell 407 - Flight Manual, POH

16 DEC 2002 13

TC APPROVED BHT-407-FMS-4

Figure 4-3. Hover ceiling IGE – maximum continuous power (sheet 1 of 8)

HOVER CEILINGIN GROUND EFFECT

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE OFF

BASIC INLETSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

30 20

10

0-10

-30-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-3_(1_OF_8).EMF

MAX DEMONSTRATED HD

Page 234: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

14 16 DEC 2002

Figure 4-3. Hover ceiling IGE – maximum continuous power (sheet 2 of 8)

HOVER CEILINGIN GROUND EFFECT

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)ANTI-ICE ONBASIC INLET

SNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

50

-10-30

-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-3_(2_OF_8).WMF

MAX DEMONSTRATED HD

Page 235: Bell 407 - Flight Manual, POH

16 DEC 2002 15

TC APPROVED BHT-407-FMS-4

Figure 4-3. Hover ceiling IGE – maximum continuous power (sheet 3 of 8)

HOVER CEILINGIN GROUND EFFECT

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER ON

BASIC INLETSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

2010

0-10

-30-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-3_(3_OF_8).EMF

MAX DEMONSTRATED HD

Page 236: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

16 16 DEC 2002

Figure 4-3. Hover ceiling IGE – maximum continuous power (sheet 4 of 8)

HOVER CEILINGIN GROUND EFFECT

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE ON

BASIC INLETSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

50

-10-30

-20-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-3_(4_OF_8).EMF

MAX DEMONSTRATED HD

Page 237: Bell 407 - Flight Manual, POH

16 DEC 2002 17

TC APPROVED BHT-407-FMS-4

Figure 4-3. Hover ceiling IGE – maximum continuous power (sheet 5 of 8)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE OFF

PARTICLE SEPARATORSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

30 20

100

-10-30

-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-3_(5_OF_8).EMF

MAX DEMONSTRATED HD

Page 238: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

18 16 DEC 2002

Figure 4-3. Hover ceiling IGE – maximum continuous power (sheet 6 of 8)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)ANTI-ICE ON

PARTICLE SEPARATORSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

50

-10-30

-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-3_(6_OF_8).WMF

MAX DEMONSTRATED HD

Page 239: Bell 407 - Flight Manual, POH

16 DEC 2002 19

TC APPROVED BHT-407-FMS-4

Figure 4-3. Hover ceiling IGE – maximum continuous power (sheet 7 of 8)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER ON

PARTICLE SEPARATORSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

2010

0-10

-30-20

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-3_(7_OF_8).EMF

MAX DEMONSTRATED HD

Page 240: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

20 16 DEC 2002

Figure 4-3. Hover ceiling IGE – maximum continuous power (sheet 8 of 8)

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)HEATER AND ANTI-ICE ON

PARTICLE SEPARATORSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5, 4-5A OR 4-5B IN BHT-407-FM-1)

14,000 FT HD

17,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

20,000 FT HD

8000

14,0

0060

0040

0020

00

12,0

00SEA L

EVEL-2

000

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

0018,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

50

-10-30

-20-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5B

REFER TO FIG. 4-5

20,0

00

AREA B

M407_FMS-4__FIG_4-3_(8_OF_8).EMF

MAX DEMONSTRATED HD

Page 241: Bell 407 - Flight Manual, POH

16 DEC 2002 21

TC APPROVED BHT-407-FMS-4

Figure 4-4. Hover ceiling OGE – takeoff power (sheet 1 of 8)

HOVER CEILINGOUT OF GROUND EFFECT

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)HEATER AND ANTI-ICE OFF

BASIC INLETSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

14,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

17,000 FT HD

8000

14,0

00

6000

4000

2000

12,0

00

SEA LEVEL

-200

0

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

-2010

0

-10

-30

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5

AREA B

MA

X O

AT

3020

M407_FMS-4__FIG_4-4_(1_OF_8).WMF

Page 242: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

22 16 DEC 2002

Figure 4-4. Hover ceiling OGE – takeoff power (sheet 2 of 8)

HOVER CEILINGOUT OF GROUND EFFECT

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)ANTI-ICE ONBASIC INLET

SNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

14,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

17,000 FT HD

8000

14,0

00

6000

4000

2000

12,0

00

SEA LEVEL

-200

0

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

-20

50

-10 -30

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5

AREA B

M407_FMS-4__FIG_4-4_(2_OF_8).WMF

Page 243: Bell 407 - Flight Manual, POH

16 DEC 2002 23

TC APPROVED BHT-407-FMS-4

Figure 4-4. Hover ceiling OGE – takeoff power (sheet 3 of 8)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER ON

BASIC INLET

SNOW DEFLECTOR

HOVER CEILING

OUT OF GROUND EFFECT

REFER TO

FIG. 4-5A

REFER TO FIG. 4-5

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

M407_FMS-4__FIG_4-4_(3_OF_8).EPS

Page 244: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

24 16 DEC 2002

Figure 4-4. Hover ceiling OGE – takeoff power (sheet 4 of 8)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE ON

BASIC INLET

SNOW DEFLECTOR

HOVER CEILING

OUT OF GROUND EFFECT

REFER TO

FIG. 4-5A

REFER TO FIG. 4-5

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

M407_FMS-4__FIG_4-4_(4_OF_8).EPS

Page 245: Bell 407 - Flight Manual, POH

16 DEC 2002 25

TC APPROVED BHT-407-FMS-4

Figure 4-4. Hover ceiling OGE – takeoff power (sheet 5 of 8)

HOVER CEILINGOUT OF GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)HEATER AND ANTI-ICE OFF

PARTICLE SEPARATORSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

14,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

17,000 FT HD

8000

14,0

00

6000

4000

2000

12,0

00

SEA LEVEL

-200

0

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

-20

10

0

-10

-30

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5

AREA B

MA

X O

AT

3020

M407_FMS-4__FIG_4-4_(5_OF_8).WMF

Page 246: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

26 16 DEC 2002

Figure 4-4. Hover ceiling OGE – takeoff power (sheet 6 of 8)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

ANTI-ICE ON

PARTICLE SEPARATOR

SNOW DEFLECTOR

HOVER CEILING

OUT OF GROUND EFFECT

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

REFER TO

FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-4__FIG_4-4_(SHEET_6).EPS

Page 247: Bell 407 - Flight Manual, POH

16 DEC 2002 27

TC APPROVED BHT-407-FMS-4

Figure 4-4. Hover ceiling OGE – takeoff power (sheet 7 of 8)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER ON

PARTICLE SEPARATOR

SNOW DEFLECTOR

HOVER CEILING

OUT OF GROUND EFFECT

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

REFER TO

FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-4__FIG_4-4_(SHEET_7).EPS

Page 248: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

28 16 DEC 2002

Figure 4-4. Hover ceiling OGE – takeoff power (sheet 8 of 8)

HOVER CEILINGOUT OF GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)HEATER AND ANTI-ICE ON

PARTICLE SEPARATORSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

14,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

17,000 FT HD

8000

14,0

00

6000

4000

2000

12,0

00

SEA LEVEL

-200

0

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

-205

0-10

-30

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-4__FIG_4-4_(8_OF_8).WMF

Page 249: Bell 407 - Flight Manual, POH

16 DEC 2002 29

TC APPROVED BHT-407-FMS-4

Figure 4-5. Hover ceiling OGE – maximum continuous power (sheet 1 of 8)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE OFF

BASIC INLET

SNOW DEFLECTOR

HOVER CEILING

OUT OF GROUND EFFECT

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

REFER TO

FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-4__FIG_4-5_(SHEET_1).EPS

Page 250: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

30 16 DEC 2002

Figure 4-5. Hover ceiling OGE – maximum continuous power (sheet 2 of 8)

HOVER CEILINGOUT OF GROUND EFFECT

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)ANTI-ICE ONBASIC INLET

SNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

14,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

17,000 FT HD

8000

14,0

00

6000

4000

2000

12,0

00

SEA LEVEL

-200

0

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

-205

0-10

-30

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-4__FIG_4-5_(2_OF_8).WMF

Page 251: Bell 407 - Flight Manual, POH

16 DEC 2002 31

TC APPROVED BHT-407-FMS-4

Figure 4-5. Hover ceiling OGE – maximum continuous power (sheet 3 of 8)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER ON

BASIC INLET

SNOW DEFLECTOR

HOVER CEILING

OUT OF GROUND EFFECT

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

REFER TO

FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-4__FIG_4-5_(SHEET_3).EPS

Page 252: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

32 16 DEC 2002

Figure 4-5. Hover ceiling OGE – maximum continuous power (sheet 4 of 8)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE ON

BASIC INLET

SNOW DEFLECTOR

HOVER CEILING

OUT OF GROUND EFFECT

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

REFER TO

FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-4__FIG_4-5_(SHEET_4).EPS

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16 DEC 2002 33

TC APPROVED BHT-407-FMS-4

Figure 4-5. Hover ceiling OGE – maximum continuous power (sheet 5 of 8)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE OFF

PARTICLE SEPARATOR

SNOW DEFLECTOR

HOVER CEILING

OUT OF GROUND EFFECT

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

REFER TO

FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-4__FIG_4-5_(SHEET_5).EPS

Page 254: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

34 16 DEC 2002

Figure 4-5. Hover ceiling OGE – maximum continuous power (sheet 6 of 8)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

ANTI-ICE ON

PARTICLE SEPARATOR

SNOW DEFLECTOR

HOVER CEILING

OUT OF GROUND EFFECT

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

REFER TO

FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-4__FIG_4-5_(SHEET_6).EPS

Page 255: Bell 407 - Flight Manual, POH

16 DEC 2002 35

TC APPROVED BHT-407-FMS-4

Figure 4-5. Hover ceiling OGE – maximum continuous power (sheet 7 of 8)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER ON

PARTICLE SEPARATOR

SNOW DEFLECTOR

HOVER CEILING

OUT OF GROUND EFFECT

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHARTIN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

REFER TO

FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-4__FIG_4-5_(SHEET_7).EPS

Page 256: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

36 16 DEC 2002

Figure 4-5. Hover ceiling OGE – maximum continuous power (sheet 8 of 8)

HOVER CEILINGOUT OF GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)HEATER AND ANTI-ICE ON

PARTICLE SEPARATORSNOW DEFLECTOR

NOTE: REFER TO APPROPRIATE HOVER CEILING WIND ACCOUNTABILITY CHART IN BASIC FLIGHT MANUAL (FIGURE 4-5 OR 4-5A IN BHT-407-FM-1)

14,000 FT HD

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - LBS x 100

16 18 20 22 24 26

GROSS WEIGHT - KG x 100

17,000 FT HD

8000

14,0

00

6000

4000

2000

12,0

00

SEA LEVEL

-200

0

H P -

FT

MA

XIM

UM

OA

T

10,0

00

16,0

00

MIN

IMU

M O

AT

EX

TE

RN

AL

= 6

000

LB

MA

X G

WIN

TE

RN

AL

= 5

000

LB

OAT - °C

-205

0-10

-30

-40

REFER TO FIG. 4-5A

REFER TO FIG. 4-5

M407_FMS-4__FIG_4-5_(8_OF_8).WMF

Page 257: Bell 407 - Flight Manual, POH

16 DEC 2002 37

TC APPROVED BHT-407-FMS-4

Figure 4-6. Rate of climb (takeoff power) (sheet 1 of 10)

407FMS-4-4-6-1

Page 258: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

38 16 DEC 2002

Figure 4-6. Rate of climb (takeoff power) (sheet 2 of 10)

407FMS-4-4-6-2

Page 259: Bell 407 - Flight Manual, POH

16 DEC 2002 39

TC APPROVED BHT-407-FMS-4

Figure 4-6. Rate of climb (takeoff power) (sheet 3 of 10)

407FMS-4-4-6-3

Page 260: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

40 16 DEC 2002

Figure 4-6. Rate of climb (takeoff power) (sheet 4 of 10)

407FMS-4-4-6-4

Page 261: Bell 407 - Flight Manual, POH

16 DEC 2002 41

TC APPROVED BHT-407-FMS-4

Figure 4-6. Rate of climb (takeoff power) (sheet 5 of 10)

407FMS-4-4-6-5

Page 262: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

42 16 DEC 2002

Figure 4-6. Rate of climb (takeoff power) (sheet 6 of 10)

407FMS-4-4-6-6

Page 263: Bell 407 - Flight Manual, POH

16 DEC 2002 43

TC APPROVED BHT-407-FMS-4

Figure 4-6. Rate of climb (takeoff power) (sheet 7 of 10)

407FMS-4-4-6-7

Page 264: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

44 16 DEC 2002

Figure 4-6. Rate of climb (takeoff power) (sheet 8 of 10)

407FMS-4-4-6-8

Page 265: Bell 407 - Flight Manual, POH

16 DEC 2002 45

TC APPROVED BHT-407-FMS-4

Figure 4-6. Rate of climb (takeoff power) (sheet 9 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 135 FT/MIN ABOVE2500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 5000 lb (2268 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

SNOW DEFLECTOR

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MAX OAT

LIMITOAT-°C

30

20

10

0

-10

-20-30

-40

M407_FMS-4__FIG_4-6_(9_OF_10).WMF

Page 266: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

46 16 DEC 2002

Figure 4-6. Rate of climb (takeoff power) (sheet 10 of 10)

407FMS-4-4-6-10

Page 267: Bell 407 - Flight Manual, POH

16 DEC 2002 47

TC APPROVED BHT-407-FMS-4

Figure 4-7. Rate of climb (maximum continuous power) (sheet 1 of 10)

407FMS-4-4-7-1

Page 268: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

48 16 DEC 2002

Figure 4-7. Rate of climb (maximum continuous power) (sheet 2 of 10)

407FMS-4-4-7-2

Page 269: Bell 407 - Flight Manual, POH

16 DEC 2002 49

TC APPROVED BHT-407-FMS-4

Figure 4-7. Rate of climb (maximum continuous power) (sheet 3 of 10)

407FMS-4-4-7-3

Page 270: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

50 16 DEC 2002

Figure 4-7. Rate of climb (maximum continuous power) (sheet 4 of 10)

407FMS-4-4-7-4

Page 271: Bell 407 - Flight Manual, POH

16 DEC 2002 51

TC APPROVED BHT-407-FMS-4

Figure 4-7. Rate of climb (maximum continuous power) (sheet 5 of 10)

407FMS-4-4-7-5

Page 272: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

52 16 DEC 2002

Figure 4-7. Rate of climb (maximum continuous power) (sheet 6 of 10)

407FMS-4-4-7-6

Page 273: Bell 407 - Flight Manual, POH

16 DEC 2002 53

TC APPROVED BHT-407-FMS-4

Figure 4-7. Rate of climb (maximum continuous power) (sheet 7 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 150 FT/MIN ABOVE1500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 4500 lb (2041 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

SNOW DEFLECTOR

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

OAT-°C

30

20

10

0

-10

-20

-30

-40

MA

X O

AT

LIMIT

0

-20

-40

M407_FMS-4__FIG_4-7_(7_OF_10).WMF

Page 274: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

54 16 DEC 2002

Figure 4-7. Rate of climb (maximum continuous power) (sheet 8 of 10)

407FMS-4-4-7-8

Page 275: Bell 407 - Flight Manual, POH

16 DEC 2002 55

TC APPROVED BHT-407-FMS-4

Figure 4-7. Rate of climb (maximum continuous power) (sheet 9 of 10)

407FMS-4-4-7-9

Page 276: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

56 16 DEC 2002

Figure 4-7. Rate of climb (maximum continuous power) (sheet 10 of 10)

407FMS-4-4-7-10

Page 277: Bell 407 - Flight Manual, POH

16 DEC 2002 57

TC APPROVED BHT-407-FMS-4

Figure 4-8. Rate of climb (takeoff power) (particle separator) (sheet 1 of 10)

407FMS-4-4-8-1

Page 278: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

58 16 DEC 2002

Figure 4-8. Rate of climb (takeoff power) (particle separator) (sheet 2 of 10)

407FMS-4-4-8-2

Page 279: Bell 407 - Flight Manual, POH

16 DEC 2002 59

TC APPROVED BHT-407-FMS-4

Figure 4-8. Rate of climb (takeoff power) (particle separator) (sheet 3 of 10)

407FMS-4-4-8-3

Page 280: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

60 16 DEC 2002

Figure 4-8. Rate of climb (takeoff power) (particle separator) (sheet 4 of 10)

407FMS-4-4-8-4

Page 281: Bell 407 - Flight Manual, POH

16 DEC 2002 61

TC APPROVED BHT-407-FMS-4

Figure 4-8. Rate of climb (takeoff power) (particle separator) (sheet 5 of 10)

407FMS-4-4-8-5

Page 282: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

62 16 DEC 2002

Figure 4-8. Rate of climb (takeoff power) (particle separator) (sheet 6 of 10)

407FMS-4-4-8-6

Page 283: Bell 407 - Flight Manual, POH

16 DEC 2002 63

TC APPROVED BHT-407-FMS-4

Figure 4-8. Rate of climb (takeoff power) (particle separator) (sheet 7 of 10)

407FMS-4-4-8-7

Page 284: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

64 16 DEC 2002

Figure 4-8. Rate of climb (takeoff power) (particle separator) (sheet 8 of 10)

407FMS-4-4-8-8

Page 285: Bell 407 - Flight Manual, POH

16 DEC 2002 65

TC APPROVED BHT-407-FMS-4

Figure 4-8. Rate of climb (takeoff power) (particle separator) (sheet 9 of 10)

RATE OF CLIMB

REDUCE RATE OF CLIMB 135 FT/MIN ABOVE2000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 45 FT/MIN FOR PURGE ON

Gross Weight 5000 lb (2268 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFF

PARTICLE SEPARATOR - PURGE OFFSNOW DEFLECTOR

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MAX OAT

LIMIT

OAT-°C

30

20

10

0

-10

-20

-30

-40

M407_FMS-4__FIG_4-8_(9_OF_10).WMF

Page 286: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

66 16 DEC 2002

Figure 4-8. Rate of climb (takeoff power) (particle separator) (sheet 10 of 10)

407FMS-4-4-8-10

Page 287: Bell 407 - Flight Manual, POH

16 DEC 2002 67

TC APPROVED BHT-407-FMS-4

Figure 4-9. Rate of climb (maximum continuous power) (particle separator) (sheet 1 of 10)

407FMS-4-4-9-1

Page 288: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

68 16 DEC 2002

Figure 4-9. Rate of climb (maximum continuous power) (particle separator) (sheet 2 of 10)

407FMS-4-4-9-2

Page 289: Bell 407 - Flight Manual, POH

16 DEC 2002 69

TC APPROVED BHT-407-FMS-4

Figure 4-9. Rate of climb (maximum continuous power) (particle separator) (sheet 3 of 10)

407FMS-4-4-9-3

Page 290: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

70 16 DEC 2002

Figure 4-9. Rate of climb (maximum continuous power) (particle separator) (sheet 4 of 10)

407FMS-4-4-9-4

Page 291: Bell 407 - Flight Manual, POH

16 DEC 2002 71

TC APPROVED BHT-407-FMS-4

Figure 4-9. Rate of climb (maximum continuous power) (particle separator) (sheet 5 of 10)

407FMS-4-4-9-5

Page 292: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

72 16 DEC 2002

Figure 4-9. Rate of climb (maximum continuous power) (particle separator) (sheet 6 of 10)

407FMS-4-4-9-6

Page 293: Bell 407 - Flight Manual, POH

16 DEC 2002 73

TC APPROVED BHT-407-FMS-4

Figure 4-9. Rate of climb (maximum continuous power) (particle separator) (sheet 7 of 10)

407FMS-4-4-9-7

Page 294: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

74 16 DEC 2002

Figure 4-9. Rate of climb (maximum continuous power) (particle separator) (sheet 8 of 10)

407FMS-4-4-9-8

Page 295: Bell 407 - Flight Manual, POH

16 DEC 2002 75

TC APPROVED BHT-407-FMS-4

Figure 4-9. Rate of climb (maximum continuous power) (particle separator) (sheet 9 of 10)

407FMS-4-4-9-9

Page 296: Bell 407 - Flight Manual, POH

BHT-407-FMS-4 TC APPROVED

76 16 DEC 2002

Figure 4-9. Rate of climb (maximum continuous power) (particle separator) (sheet 10 of 10)

407FMS-4-4-9-10

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BHT-407-FMS-21

* s SROR O F7MODEL

ROTORCRAFTFLIGHT MANUAL

SUPPLEMENT

FIRE DETECTION SYSTEM407-799-004

OR407-706-015

OR407-706-025

CERTIFIED2 MAY 1996

This supplement shall be attached to Model 407 FlightManual when FIRE DETECTION SYSTEM has been installed.

Information contained herein supplements information inthe basic Flight Manual. For Limitations, Procedures, andPerformance Data not contained in this supplement, refer tothe basic Flight Manual.

COPYRIGHT NOTICE ICOPYRIGHT 2004 Be!! HIaH. Lq.aLv.wBELL HELICOPTER TEXTRON INC . I ,i tAND BELL HELICOPTER TEXTRON A Textron Company

ALL RIGHT S RESERVED POST OFFICE BOX 2 FORT WOR. TEALL RIGHTS RESERVED POST OFFICE BOX 482 . FORT WORTH, TEXAS 76101

REISSUE - 07 JULY 2004

Page 344: Bell 407 - Flight Manual, POH

BHT-407-FMS-21

NOTICE PAGE

PROPRIETARY RIGHTS NOTICE

These data are proprietary to Bell Helicopter Textron Inc. Disclosure,reproduction, or use of these data for any purpose other than helicopteroperation is forbidden without prior written authorization from BellHelicopter Textron Inc.

Additional copies of this publication may be obtained by contacting:Commercial Publication Distribution Center

Bell Helicopter Textron Inc.P. 0. Box 482

Fort Worth, Texas 76101-0482

NP 07 JUL 2004

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BHT-407-FMS-21

LOG OF REVISIONS

Original ..................... 0 02 MAY 96 Reissue ............................................ 07 JUL 04Reissue ..................... 0...................... 08 SEP 98

LOG OF PAGES

REVISIONNO.PAGE

REVISIONNO.PAGE

FLIGHT MANUAL

TitleNPA/BC/DE/Fi/ii1 -2

0000000

NOTE

Revised text is indicated by a black vertical line. Insert latest revision pages; dispose ofsuperseded pages.

07 JUL 2004 A/B

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LOG OF TC APPROVED REVISIONS

Original ..................... 0Reissue ..................... 0

02 MAY 9608 SEP 98

* APPROVED

* FoX CHIEF, FLIGHT TESTFORDIRECTOR - AIRCRAFT CERTIFICATIONTRANSPORT CANADA

Reissue......................0 07 JUL 04

DATE 7 J/_Ly CJ0o4

07 JUL 2004 C/D

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BHT-407-FMS-21

LOG OF FAA APPROVED REVISIONS

Original ..................... 0 02 MAY 96 Reissue......................0 02 SEP 04Reissue ..................... 0...................... 08 SEP 98

07 JUL 2004 E/F

Page 348: Bell 407 - Flight Manual, POH

BHT-407-FMS-21

GENERAL INFORMATION

Bell Fire Detection System (407-799-004, 407-706-015 or 407-706-025) will illuminate ENGINE FIREwarning light on instrument panel if an excessive temperature or fire develops in enginecompartment.

07 JUL 2004 i/ii

TC APPROVED

Page 349: Bell 407 - Flight Manual, POH

BHT-407-FMS-21

* aSection 1

1-6. WEIGHT AND CENTER OFGRAVITY

Actual weight change shall be determined._ after system is installed and

Section 2

readjusted, if necessary, to return emptyweight CG to within allowable limits.

ballast

.-. I -

2-4. INTERIOR ANDCHECK

PRESTART

FIRE DET TEST switch - Press, ENGINE FIRElight illuminates, release, ENGINE FIRE lightextinguishes.

07 JUL 2004 1

TC APPROVED

Page 350: Bell 407 - Flight Manual, POH

BHT-407-FMS-21

Section 3. ... S*~1

PANEL WORDING

ENGINE FIRE

Table 3-1.

FAULT CONDITION

Excessive temperaturecondition in enginecompartment

CORRECTIVE ACTION

Immediately enter autorotation.

Throttle - Close.

FUEL VALVE switch - OFF.

If time permits, FUEL BOOST/XFRcircuit breaker switches - OFF

Execute a normal autorotation andlanding

BATT switch - OFF.

NOTE

Do not restart engine until cause of fire has been determined and corrected.

02 07 JUL 2004

TC APPROVED

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BHT-407-FMS-25

ROTORCRAFTFLIGHT MANUAL

SUPPLEMENT

QUIET CRUISE MODE407-706-016

CERTIFIED8 MAY 1998

This supplement shall be attached to Model 407 FlightManual when QUIET CRUISE MODE kit is installed.

Information contained herein supplements informationof basic Flight Manual. For Limitations, Procedures, andPerformance Data not contained in this supplement, orother applicable supplements, consult basic FlightManual.

REISSUED — 17 DECEMBER 2002

2002

Page 371: Bell 407 - Flight Manual, POH

BHT-407-FMS-25

NP 17 DEC 2002

Additional copies of this publication may be obtained by contacting:Commercial Publication Distribution Center

Bell Helicopter Textron Inc.P. O. Box 482

Fort Worth, Texas 76101-0482

NOTICE PAGE

Manufacturer’s Data portion of this supplement is proprietary to BellHelicopter Textron Inc. Disclosure, reproduction, or use of these data forany purpose other than helicopter operation is forbidden without priorwritten authorization from Bell Helicopter Textron Inc.

PROPRIETARY RIGHTS NOTICE

Page 372: Bell 407 - Flight Manual, POH

BHT-407-FMS-25

NOTE

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

LOG OF REVISIONS

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Reissue........................0 ............... 17 DEC 2002

LOG OF PAGES

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FLIGHT MANUAL

Title............................................................ 0NP.............................................................. 0A — B ........................................................ 0C/D............................................................. 0i/ii ............................................................... 01 — 12 ....................................................... 013/14 .......................................................... 015/16 .......................................................... 0

MANUFACTURER’S DATA

17 — 18......................................................0

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LOG OF TC APPROVED REVISIONS

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B 17 DEC 2002

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LOG OF FAA APPROVED REVISIONS

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17 DEC 2002 C/D

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BHT-407-FMS-25

GENERAL INFORMATION

Installation of Quiet Cruise Mode kit (407-706-016) permits flight operations at 92% NR whenabove 50 KIAS and 200 feet AGL. Flyovernoise level is reduced by 3.8 dBA SEL when in

Quiet Cruise Mode. Kit consists of electricalselector switch on collective, annunciator oninstrument panel and additional markings ondual tachometer.

17 DEC 2002 i/ii

Page 376: Bell 407 - Flight Manual, POH

17 DEC 2002 1

TC APPROVED BHT-407-FMS-25

Section 1LIMITATIONS

11-3. TYPES OF OPERATION

Quiet cruise mode is approved for VFRoperations only.

1-5. CONFIGURATION

1-5-A. REQUIRED EQUIPMENT

FADEC system software 5.201 or higher isrequired for Quiet Cruise Mode operations.

1-5-B. OPTIONAL EQUIPMENT

Helicopters S/N 53000 – 53074 shall be incompliance with Technical Bulletin 407-96-2(Increase in VNE).

1-5-D. CARGO HOOK

Cargo hook operations while in Quiet CruiseMode is not approved.

1-6. WEIGHT AND CENTER OF GRAVITY

Actual weight change shall be determinedafter kit is installed and ballast readjusted, ifnecessary, to return empty CG to withinallowable limits. Refer to Center of gravity vsweight empty chart in BHT-407-MM-2.

1-6-A. WEIGHT

M axim u m GW fo r Qu ie t C r u i se M o d eoperation is 5000 pounds (2268 kilograms).

1-6-B. CENTER OF GRAVITY — QUIET CRUISE MODE OPERATION

For longitudinal CG limits refer to Grossweight longitudinal center of gravity limitschart (Figure 1-1).

For lateral CG limits refer to Gross weightlateral center of gravity limits chart (Figure 1-2).

1-7. AIRSPEED

1-7-A. QUIET CRUISE MODE

NOTE

Refer to Section 4, HEIGHT – VELOCITYENVELOPE.

Minimum airspeed is 50 KIAS.

VNE is 100 KIAS.

1-8. ALTITUDE

NOTE

Refer to Section 4, HEIGHT – VELOCITYENVELOPE.

Minimum altitude is approximately 200 feetAGL.

Maximum altitude is 6,000 feet HD.

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1-13. POWER PLANT

1-13-B. POWER TURBINE RPM (NP)

1-13-B-1. QUIET CRUISE MODE

1-13-D. ENGINE TORQUE

Engine torque is restricted to maximumcontinuous power (93.5%) while in QuietCruise Mode.

1-15. ROTOR

1-15-A. ROTOR RPM – POWER ON

1-15-A-1. QUIET CRUISE MODE

1-20. INSTRUMENT MARKINGS AND PLACARDS

Refer to Figure 1-3 for Placards and decals.

Refer to Figure 1-4 for Instrument markings.

Minimum 91.5%

Continuous operation 91.5 to 92.5%

Maximum continuous 92.5%

Continuous operation 91.5 to 92.5%

Maximum continuous 92.5%

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Figure 1-1. Gross weight longitudinal center of gravity limits (Sheet 1 of 2)

118 119 120 121 122 123 124 125 126 127 128 129 130

FUSELAGE STATION - INCHES

2400

2600

2800

3000

3200

3400

3600

3800

4000

4200

4400

4600

4800

5000

5200

5400

GR

OS

S W

EIG

HT

-

PO

UN

DS

FS 127.0

QUIET CRUISE MODE AFT LIMIT

LONGITUDINAL C.G.

M407_FMS-25__FIG_1-1_(1_OF_2).WMF

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Figure 1-1. Gross weight longitudinal center of gravity limits (Sheet 2 of 2)

3000 3025 3050 3075 3100 3125 3150 3175 3200 3225 3250 3275 3300

FUSELAGE STATION - MILLIMETERS

1100

1200

1300

1400

1500

1600

1700

1800

1900

2000

2100

2200

2300

2400

GR

OS

S W

EIG

HT

-

KIL

OG

RA

MS

3226

QUIET CRUISE MODE AFT LIMIT

2268

LONGITUDINAL C.G.

M407_FMS-25__FIG_1-1_(2_OF_2).WMF

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TC APPROVED BHT-407-FMS-25

Figure 1-2. Gross weight lateral center of gravity limits (Sheet 1 of 2)

-3 -2 -1 0 1 2 3

BUTTOCK LINE - INCHES

2400

2600

2800

3000

3200

3400

3600

3800

4000

4200

4400

4600

4800

5000

5200

5400G

RO

SS

WE

IGH

T

- P

OU

ND

S

0.9 -0.7

1.3 -1.1

QUIET CRUISE MODE LIMITS

LATERAL C.G.

M407_FMS-25__FIG_1-2_(1_OF_2).WMF

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Figure 1-2. Gross weight lateral center of gravity limits (Sheet 2 of 2)

-60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60

BUTTOCK LINE - MILLIMETERS

1100

1200

1300

1400

1500

1600

1700

1800

1900

2000

2100

2200

2300

2400

GR

OS

S W

EIG

HT

-

KIL

OG

RA

MS

33 -28

23 -18

QUIET CRUISE MODE LIMITS

2268

LATERAL C.G.

M407_FMS-25__FIG_1-2_(2_OF_2).WMF

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TC APPROVED BHT-407-FMS-25

Figure 1-3. Placards and decals (typical)

407 AIRSPEED LIMITATIONS – KNOTS – IAS

407FS25-1-3

Airspeed limits shown are valid only for corresponding altitudes and temperatures. Hatched areas indicate conditions which exceed approved temperature or density altitude limitations.

0 2 4 6 8 10 12 14 16 18 20

52 137

45 139 132 125

40 140 133 126 119

35 140 135 128 120 113

30 140 137 129 122 115 108

25 140 138 131 124 116 109 102 95

20 140 140 133 125 118 111 103 96 89

0 140 140 140 132 125 117 110 103 95 88

-25 140 140 140 135 130 125 119 111 104 97 89

-40 137 133 128 123 118 114 110 105 101 97 93

QUIET MODE VNE 100 KIAS

MAXIMUM QUIET MODE ALTITUDE IS 6000 FT HD

PRESSURE ALTITUDE FT x 1000

407 AIRSPEED LIMITATIONS - KIAS

OAT °C

MAXIMUM AUTOROTATION VNE 100 KIAS

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8 17 DEC 2002

Figure 1-4. Instrument markings

NP (POWER TURBINE RPM)

Quiet Cruise Mode

91.5% Minimum

91.5 to 92.5% Continuous operation

92.5% Maximum continuous

Normal Operations

99% Minimum

99 to 100% Continuous operation

100% Maximum continuous

NR (ROTOR RPM)

85% Minimum (power off)

85 to 107% Continuous operation (power off)

107% Maximum (power off)

407FS25-1-4

8

Page 384: Bell 407 - Flight Manual, POH

17 DEC 2002 9

TC APPROVED BHT-407-FMS-25

Section 2NORMAL PROCEDURES

22-4. INTERIOR AND

PRESTART CHECK

QUIET NORMAL mode switch — NORMAL.

QUIET and ON annunciators illuminate andextinguish with FADEC lights.

2-6. SYSTEMS CHECK

2-6-E. QUIET CRUISE MODE CHECK

NOTE

If QUIET NORMAL mode switch iscycled at less than 92% NR, increasethrottle to 100% NR to reset QUIET, ONannunciator.

1. NR — 100% RPM.

2. QUIET NORMAL mode switch — QUIET.

3. QUIET and ON annunciators — Illuminated.

4. NR — 92% RPM.

5. Throttle — Retard below 88% NR. Confirm RPM warning illuminates with audio.

6. Throttle — FLY detent position.

7. QUIET NORMAL mode switch — NORMAL.

8. NR — 100% RPM.

9. QUIET and ON annunciators — Extinguished.

2-9. IN-FLIGHT OPERATIONS

2-9-A. IN QUIET CRUISE MODE

Flight at altitudes above 200 AGL and atairspeeds above 50 KIAS:

QUIET NORMAL mode switch — QUIET.

QUIET and ON annunciator — Illuminated.

NR — 92%RPM.

2-10. DESCENT AND LANDING

2-10-B. IN QUIET CRUISE MODE

Prior to descending below 200 AGL or 50KIAS:

QUIET NORMAL mode switch — NORMAL. Monitor engine parameters.

NR — 100% RPM

QUIET and ON annunciators — Extinguished.

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BHT-407-FMS-25 TC APPROVED

10 17 DEC 2002

Section 3EMERGENCY/MALFUNCTION PROCEDURES

33-14. QUIET CRUISE MODE

OPERATION

NOTE

In Quiet Cruise Mode, low rotor audioand RPM caution light activated at 88%NR.

If Quiet Cruise Mode fails engaged, planlan d in g i n to w i nd . Tr an s ien t tor q ueexcursions up to 100% during landing ispermitted.

NOTE

Landings into winds up to 35 knotsfrom azimuths of ± 45 degrees off noseof helicopter have been demonstrated.

Use of FADEC MAN mode will immediatelydeselect Quiet Cruise Mode and reset lowrotor audio and RPM light activation point to95% NR. To insure smooth transition toFADEC MAN mode, match throttle position toNG indication.

I f e i th er QU IET o r ON seg ment is n otilluminated, return QUIET MODE switch toNORMAL position.

Table 3-1. Warning (red) lights

PANEL

WORDING FAULT CONDITION CORRECTIVE ACTION

Warning (red) lights

RPM(with low RPM audio) NR below 88%. Reduce collective and ensure throttle is in FLY detent position. Light will extinguish and audio will cease when NR increases above 88%.

NR above 88%, QUIET light not illuminated.

Return to NORMAL mode.

Table 3-2. Caution (amber) and advisory (white/green) lights

PANEL

WORDING FAULT CONDITION CORRECTIVE ACTION

HYDRAULIC SYSTEM Hydraulic pressure below limit. Exit Quiet Cruise Mode, returning to 100% NR. Verify HYD SYS switch position. Accomplish hydraulic system failure procedure.

Page 386: Bell 407 - Flight Manual, POH

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TC APPROVED BHT-407-FMS-25

Section 4PERFORMANCE

44-4. HEIGHT – VELOCITY

ENVELOPE

The Height-velocity diagram (Figure 4-1)defines conditions from which a safe landingcan be made on a smooth, level, firm surface,following an engine failure. Limitationsrespecting minimum airspeed and minimumheight above ground for Quiet Cruise Modeoperation are marked on the Height-velocitydiagram for clarity. The Height-velocitydiagram is valid only when helicopter grossweight does not exceed limits of the Altitudeversus gross weight for height-velocitydiagram (Figure 4-2)

CAUTION

IF ENGINE FAILURE OCCURS DURINGFLIGHT CONDITIONS WITHIN HEIGHT-VELOCITY DIAGRAM “AVOID AREA”,SA F E L A N DI N G MA Y N OT BEPOSSIBLE.

4-7. CLIMB AND DESCENT

4-7-A. CLIMB

Reduce rate of climb data 100 feet per minutewhen operating in Quiet Cruise Mode.

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12 17 DEC 2002

Figure 4-1. Height – velocity diagram

0 10 20 30 40 50 60 70 80 90 100 110 120

INDICATED AIRSPEED - KNOTS

0

50

100

150

200

250

300

350

400

450

500

550

600

650

700

750

800

SK

ID H

EIG

HT

- F

EE

T

HEIGHT-VELOCITY DIAGRAM

0

20

40

60

80

100

120

140

160

180

200

220

240

SK

ID H

EIG

HT

- M

ET

ER

S 200 FT MINIMUM HEIGHT ABOVE GROUND

50

KIA

S M

INIM

UM

AIR

SP

EE

D

AVOID

M407_FMS-25__FIG_4-1.WMF

Page 388: Bell 407 - Flight Manual, POH

TC APPROVED BHT-407-FMS-25

Figure 4-2. Altitude vs gross weight for height – velocity diagram

ALTITUDE VS GROSS WEIGHTFOR HEIGHT-VELOCITY DIAGRAM

13 14 15 16 17 18 19 20 21 22 23 24

GROSS WEIGHT - KG x 100

-40 -20 0 20 40 60

OAT - °C

30 34 38 42 46 50 54

GROSS WEIGHT - LBS x 100

8000

6000

4000

2000

SE

A L

EV

EL

Hp

- F

T

10,0

00

6000 FT HD

-200

0

MIN

IMU

M O

AT

LIM

IT

50

00 L

B M

AX

IMU

M IN

TE

RN

AL

GR

OS

S W

EIG

HT

MA

XIM

UM

OA

T L

IMIT

HEIGHT-VELOCITYAVOID AREA APPLIES

M407_FMS-25__FIG_4-2.WMF

17 DEC 2002 13/14

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BHT-407-FMS-25

Section 5WEIGHT AND BALANCE

55-1. INTRODUCTION

This section presents loading information andinstructions necessary to ensure that flightcan be performed within approved grossweight and center of gravity limitations asdefined in Section 1.

5-3. GROSS WEIGHT CENTER OF GRAVITY

5-3-B. CENTER OF GRAVITY

Gross weight longitudinal center of gravityand Gross weight lateral center of gravitycharts for Quiet Cruise operations are inLimitations Section 1 .

For Quiet Cruise operations maintaininglongitudinal CG within limits can be achievedby the following:

With helicopter Weight empty within envelope (BHT-407-MM-2) the helicopter will stay within Quiet Cruise limits provided both pilot and co-pilot seats are occupied. This assumes a

standard crew/passenger weight of 170 pounds (77.1 kilograms) and that fuel and payload are adjusted to stay within Maximum Gross Weight limit.

If co-pilot/forward passenger seat is unoccupied then cabin payload must be adjusted to maintain flight envelope.

For helicopters operating without respect toWei gh t em pty en ve l op e th e p i lo t isresponsible for ensuring that when operatingin Quiet Cruise mode, helicopter weight andCG are within limits.

For Quiet Cruise operations maintainingLateral CG within limits can be achieved bythe following:

Seats should be occupied such that maximum asymmetric loading is no more than one person (170 pounds (77.1 kilograms)).

With this arrangement, a helicopter whosebasic lateral CG is ±0.3 inch (7.62 mm), willremain within lateral limits.

17 DEC 2002 15/16

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17 DEC 2002 17

MANUFACTURER’S DATA BHT-407-FMS-25

Section 1SYSTEM DESCRIPTION

This kit incorporates a two position switch oncollective (Figure 1-1) permitt ing pilotselection of operation at 100% NR or 92% NR(Quiet Cruise Mode). A two (2) segmentannunciator located on instrument panel(Figure 1-2), when illuminated, displaysQUIET and ON. QUIET light is illuminatedwhen low rotor audio and RPM light activationpo i nt is res e t to 88 % N R . ON l ig h t isilluminated when FADEC is not in 100% NRmode. Both segments are green and willdeno te opera t ion a t 92% NR has beenselected. Dual tachometer has additionalmarkings to reflect permissible operation at92% NP.

NOTE

Selection of FADEC switch to MANmode, for training purposes, while inQuiet Cruise Mode, will immediatelydeselect Quiet Cruise Mode and resetlow rotor audio and RPM lightactivation point to 95% NR (triggeringlow rotor audio and RPM light). QUIETand ON segments will also extinguish.Transition back to AUTO mode shouldbe accomplished at approximately100% NP to reduce engine powertransients.

A FADEC system failure (FADEC FAILlight with FADEC fail audio), while inQuiet Cruise Mode, will retainactivation point of low rotor audio andRPM light at 88%. QUIET segment willremain illuminated and ON segmentwill extinguish. Selection of FADECMAN mode will immediately deselectQuiet Cruise Mode and reset low rotoraudio and RPM activation point to 95%NR, extinguishing the QUIET segment.

1-55. NOISE LEVELS

1-55-A. FAR PART 36 STAGE 2 NOISE LEVEL

Flyover noise level in Quiet Cruise Mode forthe Model 407 is 81.3 dBA SEL.

1-55-B. CANADIAN AIRWORTHINESS MANUAL CHAPTER 516 AND ICAO ANNEX 16 NOISE LEVEL

Flyover noise level in Quiet Cruise Mode forthe Model 407 is 81.3 dBA SEL.

Page 391: Bell 407 - Flight Manual, POH

BHT-407-FMS-25 MANUFACTURER’S DATA

18 17 DEC 2002

Figure 1-1. Pilot collective stick

Figure 1-2. Quiet mode annunciator

Page 392: Bell 407 - Flight Manual, POH

BHT-407-FMS-28

ROTORCRAFTFLIGHT MANUAL

SUPPLEMENT

INCREASED INTERNAL GROSS WEIGHT407-706-020

CERTIFIED16 MARCH 1999

This supplement shall be attached to Model 407 FlightManual when INCREASED INTERNAL GROSS WEIGHTkit is installed.

Information contained herein supplements informationof basic Flight Manual. For Limitations, Procedures, andPerformance Data not contained in this supplement, orother applicable supplements, consult basic FlightManual.

REISSUED — 16 DECEMBER 2002

2002

Page 393: Bell 407 - Flight Manual, POH

BHT-407-FMS-28

NP 16 DEC 2002

Additional copies of this publication may be obtained by contacting:Commercial Publication Distribution Center

Bell Helicopter Textron Inc.P. O. Box 482

Fort Worth, Texas 76101-0482

NOTICE PAGE

Manufacture’s Data portion of this supplement is proprietary to BellHelicopter Textron Inc. Disclosure, reproduction, or use of these data forany purpose other than helicopter operation is forbidden without priorwritten authorization from Bell Helicopter Textron Inc.

PROPRIETARY RIGHTS NOTICE

Page 394: Bell 407 - Flight Manual, POH

BHT-407-FMS-28

NOTE

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

LOG OF REVISIONS

Original ....................... 0................... 16 MAR 99 Reissue........................0 ................... 16 DEC 02

LOG OF PAGES

REVISION REVISIONNO. NO.PAGE PAGE

FLIGHT MANUAL

Title............................................................ 0NP.............................................................. 0A — B ........................................................ 0C/D ........................................................... 01 — 92 ..................................................... 0

16 DEC 2002 A

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LOG OF TC APPROVED REVISIONS

Original ........................0 ...................16 MAR 99 Reissue ....................... 0 ....................16 DEC 02

B 16 DEC 2002

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LOG OF FAA APPROVED REVISIONS

Original ....................... 0......................7 MAY 99Reissue ....................... 0.................... 24 SEP 03

16 DEC 2002 C/D

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TC APPROVED BHT-407-FMS-28

Section 1LIMITATIONS

11-6. WEIGHT AND CENTER

OF GRAVITY

1-6-A. WEIGHT

Maximum approved internal gross weight fortakeoff and landing is 5250 pounds (2381k i l o gr ams ) o r as sh o wn i n IG E h o verperformance charts, Section 4.

CAUTION

LOADS THAT RESULT IN GW ABOVE5,250 POUNDS (2381 KILOGRAMS)SHALL BE CARRIED ON THE CARGOHOOK.

1-6-B. CENTER OF GRAVITY

For longitudinal CG limits, refer to GrossWeight Longitudinal center of gravity limitscharts (Figure 1-1).

For lateral CG limits, refer to Gross WeightLateral center of gravity limits chart(Figure 1-2).

1-7. AIRSPEED

VNE is 140 KIAS, sea level to 3000 feet HD.Decrease VNE for ambient conditions in

accordance with AIRSPEED LIMITATIONSPlacards and decals (Figure 1-3).

1-8. ALTITUDE

1-8-A. DENSITY

Maximum HD for takeoff, landing, and in

ground effect manuevers is 11,000 feet (3353meters).

1-8-B. DELETED

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Figure 1-1. Gross Weight Longitudinal center of gravity limits (sheet 1 of 2)

118 119 120 121 122 123 124 125 126 127 128 129 130

FUSELAGE STATION - INCHES

2400

2600

2800

3000

3200

3400

3600

3800

4000

4200

4400

4600

4800

5000

5200

5400

5600

5800

6000

6200

GR

OS

S W

EIG

HT

- P

OU

ND

S

5250

6000

5000

4500

2800

2650

120.5 127.6

128.7 119.8

119.0

128.0 129.0

EXTERNAL LOAD ONLY

LONGITUDINAL C.G.

M407_FMS-28__FIG_1-1_(1_OF_2).WMF

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Figure 1-1. Gross Weight Longitudinal center of gravity limits (sheet 2 of 2)

3000 3025 3050 3075 3100 3125 3150 3175 3200 3225 3250 3275 3300

FUSELAGE STATION - MILLIMETERS

1100

1200

1300

1400

1500

1600

1700

1800

1900

2000

2100

2200

2300

2400

2500

2600

2700

2800

GR

OS

S W

EIG

HT

- K

ILO

GR

AM

SLONGITUDINAL C.G.

2268

EXTERNAL LOAD ONLY

2381

3241 3061

2722

32683042

2041

1270

1202 3023

3251 3277

M407_FMS-28__FIG_1-1_(2_OF_2).WMF

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Figure 1-2. Gross Weight Lateral center of gravity limits (sheet 1 of 2)

-5 -4 -3 -2 -1 0 1 2 3 4 5

BUTTOCK LINE - INCHES

2400

2600

2800

3000

3200

3400

3600

3800

4000

4200

4400

4600

4800

5000

5200

5400

5600

5800

6000

6200

GR

OS

S W

EIG

HT

- P

OU

ND

S

5000

-1.5

LATERAL C.G.

EXTERNAL LOAD ONLY

MAX AIRSPEED 100 KIAS

-0.9 1.4

1.9-1.4

2.0

-4.0 -2.5 3.0 4.0

3500

2650

5250

3500

6000

EXTERNALLOAD ONLY

MAX AIRSPEED100 KIAS

EXTERNALLOAD ONLY

MAX AIRSPEED100 KIAS

M407_FMS-28__FIG_1-2_(1_OF_2).WMF

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TC APPROVED BHT-407-FMS-28

Figure 1-2. Gross Weight Lateral center of gravity limits (sheet 2 of 2)

-125 -100 -75 -50 -25 0 25 50 75 100 125

BUTTOCK LINE - MILLIMETERS

1100

1200

1300

1400

1500

1600

1700

1800

1900

2000

2100

2200

2300

2400

2500

2600

2700

2800

GR

OS

S W

EIG

HT

- K

ILO

GR

AM

SLATERAL C.G.

EXTERNAL LOAD ONLY

MAX AIRSPEED 100 KIAS

EXTERNALLOAD ONLY

MAX AIRSPEED100 KIAS

EXTERNALLOAD ONLY

MAX AIRSPEED100 KIAS

-102 -64 76 102

1588 1588

1202

-39 52

-35 48 2268

2381

-23 36

2722

M407_FMS-28__FIG_1-2_(2_OF_2).WMF

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Figure 1-3. Placards and Decals (typical)

407FS28-1-3

0 2 4 6 8 10 12 14 16 18 20

52 137

45 139 132 123

40 140 133 125 113

35 140 135 128 116 104

30 140 137 129 118 106 99

25 140 138 131 121 109 100 93 86

20 140 140 133 124 112 102 94 87 80

0 140 140 140 132 123 111 101 94 86 79

-25 140 140 140 135 130 125 114 102 95 88 80

-40 137 133 128 123 118 114 110 105 101 93 86

PRESSURE ALTITUDE FT x 1000

407 (5250 LB) AIRSPEED LIMITATIONS - KIAS

OAT °C

MAXIMUM AUTOROTATION VNE 100 KIAS

Airspeed limits shown are valid only for corresponding altitudes and temperatures. Hatched areas indicate conditions which exceed approved temperature or density altitude limitations.

Location: Adjacent to existing airspeed limitations placard (typical).

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TC APPROVED BHT-407-FMS-28

Section 2NORMAL PROCEDURES

2No change from basic manual.

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8 16 DEC 2002

Section 3EMERGENCY/MALFUNCTION PROCEDURES

3No change from basic manual.

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TC APPROVED BHT-407-FMS-28

Section 4PERFORMANCE

44-1. INTRODUCTION

Refer to appropriate performance charts inaccordance with optional equipment installed.

4-4. HEIGHT – VELOCITY ENVELOPE

Altitude vs gross weight for height-velocitydiagram (Figure 4-1) and Height-velocity(Figure 4-2) diagrams define conditions fromwhich a safe landing can be made on asmooth, level, firm surface following anengine failure. Height velocity diagram is validonly when helicopter gross weight does notexceed limits of the Altitude vs Gross Weightdiagram.

4-5. HOVER CEILING

NOTE

Hover performance charts are based on100% ROTOR RPM.

Satisfactory stability and control have beendemonstrated in each area of the Hoverceiling charts with winds as depicted onHover ceiling wind accountability chart (referto Basic Flight Manual).

Hover ceiling – in ground effect charts(Figures 4-3 and 4-4) and Hover ceiling – outof ground effect charts (Figures 4-5 and 4-6)present hover performance as allowablegross weight for conditions of HP and OAT.

These hovering weights are obtainable in zerowind conditions. Each chart is divided intotwo areas. Area A (non shaded area) of hover

ceiling charts presents hover performance(r ela t ive to GW ) for cond i t io ns whereadequate control margins exist for all relativewind conditions up to 35 knots, for lateral CGnot exceeding ±2.5 inches (±63 mm); and upto 17 knots, for lateral CG to ±4.0 inches (±102mm); for hover, takeoff, and landing. Area B(shaded area) of hover ceiling charts presentshover performance (relative to GW) whereadequate control margins exist for relativewinds within ± 45° of nose of helicopter up to35 knots, for lateral CG not exceeding ±2.5inches (±63 mm); and up to 17 knots, forlateral CG to ±4.0 inches (±102 mm); for hover,takeoff, and landing.

4-7. CLIMB AND DESCENT

4-7-A. RATE OF CLIMB

Rate of climb (takeoff power) charts arepresented in Figure 4-7, and Rate of climb(maximum continuous power) charts arepresented in Figure 4-8.

4-10. NOISE LEVELS

4-10-A.FAR PART 36 STAGE 2 NOISE LEVEL

Model 407 is certified as a Stage 2 helicopteras prescribed in FAR Part 36, Subpart H, forgross weights up to and including certificatedmaximum takeoff and landing weight of 5250pounds (2382 kilograms).

Certified flyover noise level for Model 407 is85.5 dBA SEL.

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4-10-B.CANADIAN AIRWORTHINESS MANUAL CHAPTER 516 AND ICAO ANNEX 16 NOISE LEVEL

Model 407 complies with noise emissionstandards applicable to helicopter as set out

by International Civil Aviation Organization(ICAO) in Annex 16, Volume 1, Chapter 11, forgross weights up to and including certifiedmaximum takeoff and landing weight of 5250pounds (2382 kilograms).

Flyover noise level for Model 407 is 85.5 dBASEL.

Page 407: Bell 407 - Flight Manual, POH

16 DEC 2002 11

TC APPROVED BHT-407-FMS-28

Figure 4-1. Altitude vs gross weight for height – velocity diagram

ALTITUDE VS GROSS WEIGHTFOR HEIGHT-VELOCITY DIAGRAM

13 14 15 16 17 18 19 20 21 22 23 24

GROSS WEIGHT - KG x 100

-40 -20 0 20 40 60

OAT - °C

30 34 38 42 46 50 54

GROSS WEIGHT - LBS x 100

8000

6000

4000

2000

SEA LEVEL

Hp

- FT

10,0

00

14,000 FT HD

MA

XIM

UM

OA

T

-200

0

MIN

IMU

M O

AT

LIM

IT

12,0

00

14,0

00

MA

XIM

UM

INT

ER

NA

L G

RO

SS

WE

IGH

T =

525

0 L

B

DEMONSTRATEDTO 9000 FEET

DENSITY ALTITUDE

9000 FT HD

GR

OS

S WEIG

HT R

EGIO

NS A

B

C

D

M407_FMS-28__FIG_4-1.EMF

Page 408: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

12 16 DEC 2002

Figure 4-2. Height – velocity diagram

0 10 20 30 40 50 60 70 80 90 100 110 120

INDICATED AIRSPEED - KNOTS

0

50

100

150

200

250

300

350

400

450

500

550

600

650

700

750

800

SK

ID H

EIG

HT

- F

EE

T

HEIGHT-VELOCITY DIAGRAMFOR GROSS WEIGHT REGIONS A TO D

0

20

40

60

80

100

120

140

160

180

200

220

240

SK

ID H

EIG

HT

- M

ET

ER

S

NOTE: LOW HOVER POINT IS AT 6 FT SKID HEIGHT

AVOID

AV

OID

AR

EA

S

REG

ION "A" BELO

W TH

IS LINE

RE

GIO

N "B

" BE

LOW

THIS

LINE

RE

GIO

N "C

" BE

LOW

THIS

LINE

RE

GIO

N "D

" BE

LOW

THIS

LINE

M407_FMS-28__FIG_4-2.EMF

Page 409: Bell 407 - Flight Manual, POH

16 DEC 2002 13

TC APPROVED BHT-407-FMS-28

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 1 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER AND ANTI-ICE OFF

BASIC INLET

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-3_(1_OF_16).EPS

Page 410: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

14 16 DEC 2002

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 2 of 16)

SKID HEIGHT 4 FT (1.2 METER)

ANTI-ICE ON

BASIC INLET

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-3_(2_OF_16).EPS

Page 411: Bell 407 - Flight Manual, POH

16 DEC 2002 15

TC APPROVED BHT-407-FMS-28

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 3 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER ON

BASIC INLET

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-3_(3_OF_16).EPS

Page 412: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

16 16 DEC 2002

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 4 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER AND ANTI-ICE ON

BASIC INLET

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-3_(4_OF_16).EPS

Page 413: Bell 407 - Flight Manual, POH

16 DEC 2002 17

TC APPROVED BHT-407-FMS-28

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 5 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER AND ANTI-ICE OFF

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

HOVER CEILINGIN GROUND EFFECT

PARTICLE SEPARATOR

M407_FMS-28__FIG_4-3_(5_OF_16).EPS

Page 414: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

18 16 DEC 2002

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 6 of 16)

SKID HEIGHT 4 FT (1.2 METER)

ANTI-ICE ON

PARTICLE SEPARATOR

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

M407_FMS-28__FIG_4-3_(6_OF_16).EPS

Page 415: Bell 407 - Flight Manual, POH

16 DEC 2002 19

TC APPROVED BHT-407-FMS-28

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 7 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER ON

PARTICLE SEPARATOR

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

M407_FMS-28__FIG_4-3_(7_OF_16).EPS

Page 416: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

20 16 DEC 2002

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 8 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER AND ANTI-ICE ON

PARTICLE SEPARATOR

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

M407_FMS-28__FIG_4-3_(8_OF_16).EPS

Page 417: Bell 407 - Flight Manual, POH

16 DEC 2002 21

TC APPROVED BHT-407-FMS-28

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 9 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER AND ANTI-ICE OFF

BASIC INLET

SNOW BAFFLES

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-3_(9_OF_16).EPS

Page 418: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

22 16 DEC 2002

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 10 of 16)

SKID HEIGHT 4 FT (1.2 METER)

ANTI-ICE ON

BASIC INLET

SNOW BAFFLES

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-3_(10_OF_16).EPS

Page 419: Bell 407 - Flight Manual, POH

16 DEC 2002 23

TC APPROVED BHT-407-FMS-28

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 11 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER ON

BASIC INLET

SNOW BAFFLES

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-3_(11_OF_16).EPS

Page 420: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

24 16 DEC 2002

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 12 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER AND ANTI-ICE ON

BASIC INLET

SNOW BAFFLES

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-3_(12_OF_16).EPS

Page 421: Bell 407 - Flight Manual, POH

16 DEC 2002 25

TC APPROVED BHT-407-FMS-28

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 13 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER AND ANTI-ICE OFF

PARTICLE SEPARATOR

SNOW BAFFLES

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

M407_FMS-28__FIG_4-3_(13_OF_16).EPS

Page 422: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

26 16 DEC 2002

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 14 of 16)

SKID HEIGHT 4 FT (1.2 METER)

ANTI-ICE ON

PARTICLE SEPARATOR

SNOW BAFFLES

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

M407_FMS-28__FIG_4-3_(14_OF_16).EPS

Page 423: Bell 407 - Flight Manual, POH

16 DEC 2002 27

TC APPROVED BHT-407-FMS-28

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 15 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER ON

PARTICLE SEPARATOR

SNOW BAFFLES

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

M407_FMS-28__FIG_4-3_(15_OF_16).EPS

Page 424: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

28 16 DEC 2002

Figure 4-3. Hover ceiling IGE – takeoff power (sheet 16 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER AND ANTI-ICE ON

PARTICLE SEPARATOR

SNOW BAFFLES

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

M407_FMS-28__FIG_4-3_(16_OF_16).EPS

Page 425: Bell 407 - Flight Manual, POH

16 DEC 2002 29

TC APPROVED BHT-407-FMS-28

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 1 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER AND ANTI-ICE OFF

BASIC INLET

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-4_(1_OF_16).EPS

Page 426: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

30 16 DEC 2002

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 2 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

ANTI-ICE ON

BASIC INLET

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-4_(2_OF_16).EPS

Page 427: Bell 407 - Flight Manual, POH

16 DEC 2002 31

TC APPROVED BHT-407-FMS-28

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 3 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER ON

BASIC INLET

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-4_(3_OF_16).EPS

Page 428: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

32 16 DEC 2002

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 4 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER AND ANTI-ICE ON

BASIC INLET

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-4_(4_OF_16).EPS

Page 429: Bell 407 - Flight Manual, POH

16 DEC 2002 33

TC APPROVED BHT-407-FMS-28

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 5 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER AND ANTI-ICE OFF

PARTICLE SEPARATOR

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

M407_FMS-28__FIG_4-4_(5_OF_16).EPS

Page 430: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

34 16 DEC 2002

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 6 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

ANTI-ICE ON

PARTICLE SEPARATOR

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

M407_FMS-28__FIG_4-4_(6_OF_16).EPS

Page 431: Bell 407 - Flight Manual, POH

16 DEC 2002 35

TC APPROVED BHT-407-FMS-28

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 7 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER ON

PARTICLE SEPARATOR

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

M407_FMS-28__FIG_4-4_(7_OF_16).EPS

Page 432: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

36 16 DEC 2002

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 8 of 16)

HOVER CEILINGIN GROUND EFFECT

MAXIMUM CONTINUOUS POWER SKID HEIGHT 4 FT (1.2 METER)ENGINE RPM 100% HEATER AND ANTI-ICE ONGENERATOR 180 AMPS PARTICLE SEPARATOR

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

14 16 18 20 22 24 26GROSS WEIGHT - 100 KG

-40 -20 0 20 40 60

OAT - °C

32 36 40 44 48 52 56 60

GROSS WEIGHT - 100 LB

8000

6000

4000

2000

SEA L

EVEL

Hp

- FT

10,0

00

11,000 FT HD

MA

XIM

UM

OA

T

-200

0

MIN

IMU

M O

AT

12,0

00

JE

TT

ISO

NA

BL

E E

XT

ER

NA

L=

6000

LB

MA

X G

WIN

TE

RN

AL

=52

50 L

B

100

-10

-20-30

-40

OAT - °C

M407_FMS-28__FIG_4-4_(8_OF_16).EMF

Page 433: Bell 407 - Flight Manual, POH

16 DEC 2002 37

TC APPROVED BHT-407-FMS-28

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 9 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER AND ANTI-ICE OFF

BASIC INLET

SNOW BAFFLES

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-4_(9_OF_16).EPS

Page 434: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

38 16 DEC 2002

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 10 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

ANTI-ICE ON

BASIC INLET

SNOW BAFFLES

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-4_(10_OF_16).EPS

Page 435: Bell 407 - Flight Manual, POH

16 DEC 2002 39

TC APPROVED BHT-407-FMS-28

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 11 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER ON

BASIC INLET

SNOW BAFFLES

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-4_(11_OF_16).EPS

Page 436: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

40 16 DEC 2002

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 12 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER AND ANTI-ICE ON

BASIC INLET

SNOW BAFFLES

HOVER CEILINGIN GROUND EFFECT

M407_FMS-28__FIG_4-4_(12_OF_16).EPS

Page 437: Bell 407 - Flight Manual, POH

16 DEC 2002 41

TC APPROVED BHT-407-FMS-28

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 13 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER AND ANTI-ICE OFF

PARTICLE SEPARATOR

SNOW BAFFLES

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

M407_FMS-28__FIG_4-4_(13_OF_16).EPS

Page 438: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

42 16 DEC 2002

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 14 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

ANTI-ICE ON

PARTICLE SEPARATOR

SNOW BAFFLES

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

M407_FMS-28__FIG_4-4_(14_OF_16).EPS

Page 439: Bell 407 - Flight Manual, POH

16 DEC 2002 43

TC APPROVED BHT-407-FMS-28

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 15 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER ON

PARTICLE SEPARATOR

SNOW BAFFLES

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

M407_FMS-28__FIG_4-4_(15_OF_16).EPS

Page 440: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

44 16 DEC 2002

Figure 4-4. Hover ceiling IGE – maximum continuous power (sheet 16 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 4 FT (1.2 METER)

HEATER AND ANTI-ICE ON

PARTICLE SEPARATOR

SNOW BAFFLES

HOVER CEILINGIN GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 55 LBS

M407_FMS-28__FIG_4-4_(16_OF_16).EPS

Page 441: Bell 407 - Flight Manual, POH

16 DEC 2002 45

TC APPROVED BHT-407-FMS-28

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 1 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE OFF

BASIC INLET

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(1_OF_16).EPS

Page 442: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

46 16 DEC 2002

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 2 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

ANTI-ICE ON

BASIC INLET

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(2_OF_16).EPS

Page 443: Bell 407 - Flight Manual, POH

16 DEC 2002 47

TC APPROVED BHT-407-FMS-28

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 3 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER ON

BASIC INLET

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(3_OF_16).EPS

Page 444: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

48 16 DEC 2002

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 4 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE ON

BASIC INLET

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(4_OF_16).EPS

Page 445: Bell 407 - Flight Manual, POH

16 DEC 2002 49

TC APPROVED BHT-407-FMS-28

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 5 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE OFF

PARTICLE SEPARATOR

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(5_OF_16).EPS

Page 446: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

50 16 DEC 2002

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 6 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

ANTI-ICE ON

PARTICLE SEPARATOR

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(6_OF_16).EPS

Page 447: Bell 407 - Flight Manual, POH

16 DEC 2002 51

TC APPROVED BHT-407-FMS-28

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 7 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER ON

PARTICLE SEPARATOR

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(7_OF_16).EPS

Page 448: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

52 16 DEC 2002

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 8 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE ON

PARTICLE SEPARATOR

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(8_OF_16).EPS

Page 449: Bell 407 - Flight Manual, POH

16 DEC 2002 53

TC APPROVED BHT-407-FMS-28

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 9 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE OFF

BASIC INLET

SNOW BAFFLES

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(9_OF_16).EPS

Page 450: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

54 16 DEC 2002

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 10 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

ANTI-ICE ON

BASIC INLET

SNOW BAFFLES

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(10_OF_16).EPS

Page 451: Bell 407 - Flight Manual, POH

16 DEC 2002 55

TC APPROVED BHT-407-FMS-28

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 11 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER ON

BASIC INLET

SNOW BAFFLES

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(11_OF_16).EPS

Page 452: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

56 16 DEC 2002

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 12 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE ON

BASIC INLET

SNOW BAFFLES

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(12_OF_16).EPS

Page 453: Bell 407 - Flight Manual, POH

16 DEC 2002 57

TC APPROVED BHT-407-FMS-28

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 13 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE OFF

PARTICLE SEPARATOR

SNOW BAFFLES

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(13_OF_16).EPS

Page 454: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

58 16 DEC 2002

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 14 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

ANTI-ICE ON

PARTICLE SEPARATOR

SNOW BAFFLES

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(14_OF_16).EPS

Page 455: Bell 407 - Flight Manual, POH

16 DEC 2002 59

TC APPROVED BHT-407-FMS-28

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 15 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER ON

PARTICLE SEPARATOR

SNOW BAFFLES

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(15_OF_16).EPS

Page 456: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

60 16 DEC 2002

Figure 4-5. Hover ceiling OGE – takeoff power (sheet 16 of 16)

TAKEOFF POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE ON

PARTICLE SEPARATOR

SNOW BAFFLES

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-5_(16_OF_16).EPS

Page 457: Bell 407 - Flight Manual, POH

16 DEC 2002 61

TC APPROVED BHT-407-FMS-28

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 1 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE OFF

BASIC INLET

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-6_(1_OF_16).EPS

Page 458: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

62 16 DEC 2002

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 2 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

ANTI-ICE ON

BASIC INLET

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-6_(2_OF_16).EPS

Page 459: Bell 407 - Flight Manual, POH

16 DEC 2002 63

TC APPROVED BHT-407-FMS-28

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 3 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER ON

BASIC INLET

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-6_(3_OF_16).EPS

Page 460: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

64 16 DEC 2002

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 4 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE ON

BASIC INLET

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-6_(4_OF_16).EPS

Page 461: Bell 407 - Flight Manual, POH

16 DEC 2002 65

TC APPROVED BHT-407-FMS-28

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 5 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE OFF

PARTICLE SEPARATOR

HOVER CEILINGOUT OF GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

M407_FMS-28__FIG_4-6_(5_OF_16).EPS

Page 462: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

66 16 DEC 2002

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 6 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

ANTI-ICE ON

PARTICLE SEPARATOR

HOVER CEILINGOUT OF GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

M407_FMS-28__FIG_4-6_(6_OF_16).EPS

Page 463: Bell 407 - Flight Manual, POH

16 DEC 2002 67

TC APPROVED BHT-407-FMS-28

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 7 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER ON

PARTICLE SEPARATOR

HOVER CEILINGOUT OF GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

M407_FMS-28__FIG_4-6_(7_OF_16).EPS

Page 464: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

68 16 DEC 2002

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 8 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE ON

PARTICLE SEPARATOR

HOVER CEILINGOUT OF GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

M407_FMS-28__FIG_4-6_(8_OF_16).EPS

Page 465: Bell 407 - Flight Manual, POH

16 DEC 2002 69

TC APPROVED BHT-407-FMS-28

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 9 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE OFF

BASIC INLET

SNOW BAFFLES

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-6_(9_OF_16).EPS

Page 466: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

70 16 DEC 2002

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 10 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

ANTI-ICE ON

BASIC INLET

SNOW BAFFLES

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-6_(10_OF_16).EPS

Page 467: Bell 407 - Flight Manual, POH

16 DEC 2002 71

TC APPROVED BHT-407-FMS-28

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 11 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER ON

BASIC INLET

SNOW BAFFLES

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-6_(11_OF_16).EPS

Page 468: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

72 16 DEC 2002

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 12 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE ON

BASIC INLET

SNOW BAFFLES

HOVER CEILINGOUT OF GROUND EFFECT

M407_FMS-28__FIG_4-6_(12_OF_16).EPS

Page 469: Bell 407 - Flight Manual, POH

16 DEC 2002 73

TC APPROVED BHT-407-FMS-28

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 13 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE OFF

PARTICLE SEPARATOR

SNOW BAFFLES

HOVER CEILINGOUT OF GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

M407_FMS-28__FIG_4-6_(13_OF_16).EPS

Page 470: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

74 16 DEC 2002

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 14 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

ANTI-ICE ON

PARTICLE SEPARATOR

SNOW BAFFLES

HOVER CEILINGOUT OF GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

M407_FMS-28__FIG_4-6_(14_OF_16).EPS

Page 471: Bell 407 - Flight Manual, POH

16 DEC 2002 75

TC APPROVED BHT-407-FMS-28

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 15 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER ON

PARTICLE SEPARATOR

SNOW BAFFLES

HOVER CEILINGOUT OF GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

M407_FMS-28__FIG_4-6_(15_OF_16).EPS

Page 472: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

76 16 DEC 2002

Figure 4-6. Hover ceiling OGE – maximum continuous power (sheet 16 of 16)

MAXIMUM CONTINUOUS POWER

ENGINE RPM 100%

GENERATOR 180 AMPS

SKID HEIGHT 40 FT (12.2 METER)

HEATER AND ANTI-ICE ON

PARTICLE SEPARATOR

SNOW BAFFLES

HOVER CEILINGOUT OF GROUND EFFECT

WITH PARTICLE SEPARATOR PURGE ON, REDUCE GROSS WEIGHT BY 50 LBS

M407_FMS-28__FIG_4-6_(16_OF_16).EPS

Page 473: Bell 407 - Flight Manual, POH

16 DEC 2002 77

TC APPROVED BHT-407-FMS-28

Figure 4-7. Rate of climb – takeoff power (sheet 1 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MIN ABOVE4000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 5250 lb (2381 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X OA

T LIMIT

OAT-°C

30

20

10

0

-10

-20-30

-40

40

50

M407_FMS-28__FIG_4-7_(1_OF_8).WMF

Page 474: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

78 16 DEC 2002

Figure 4-7. Rate of climb – takeoff power (sheet 2 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MIN ABOVE1000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 5250 lb (2381 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

BASIC INLET

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

OAT-°C

20

10

0

-10

-20

-30

-40

M407_FMS-28__FIG_4-7_(2_OF_8).WMF

Page 475: Bell 407 - Flight Manual, POH

16 DEC 2002 79

TC APPROVED BHT-407-FMS-28

Figure 4-7. Rate of climb – takeoff power (sheet 3 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MIN ABOVE3500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 45 FT/MIN FOR PURGE ON

Gross Weight 5250 lb (2381 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFF

PARTICLE SEPARATOR - PURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X OA

T LIMIT

OAT-°C

30

20

10

0

-10

-20

-30

-40

40

50

M407_FMS-28__FIG_4-7_(3_OF_8).WMF

Page 476: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

80 16 DEC 2002

Figure 4-7. Rate of climb – takeoff power (sheet 4 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MIN ABOVE500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 45 FT/MIN FOR PURGE ON

Gross Weight 5250 lb (2381 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

PARTICLE SEPARATOR - PURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

OAT-°C

20

10

0

-10

-20

-30

-40

M407_FMS-28__FIG_4-7_(4_OF_8).WMF

Page 477: Bell 407 - Flight Manual, POH

16 DEC 2002 81

TC APPROVED BHT-407-FMS-28

Figure 4-7. Rate of climb – takeoff power (sheet 5 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MIN ABOVE2500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 5250 lb (2381 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

SNOW DEFLECTOR

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MAX OAT

LIMITOAT-°C

30

20

10

0

-10

-20

-30

-40

M407_FMS-28__FIG_4-7_(5_OF_8).WMF

Page 478: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

82 16 DEC 2002

Figure 4-7. Rate of climb – takeoff power (sheet 6 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MINFOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 5250 lb (2381 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

BASIC INLETSNOW DEFLECTOR

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

OAT-°C

20

10

0

-10

-20-30

-40

M407_FMS-28__FIG_4-7_(6_OF_8).WMF

Page 479: Bell 407 - Flight Manual, POH

16 DEC 2002 83

TC APPROVED BHT-407-FMS-28

Figure 4-7. Rate of climb – takeoff power (sheet 7 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MIN ABOVE2000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 45 FT/MIN FOR PURGE ON

Gross Weight 5250 lb (2381 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFF

PARTICLE SEPARATOR - PURGE OFFSNOW DEFLECTOR

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MAX OAT

LIMITOAT-°C

30

20

10

0

-10

-20

-30

-40

M407_FMS-28__FIG_4-7_(7_OF_8).WMF

Page 480: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

84 16 DEC 2002

Figure 4-7. Rate of climb – takeoff power (sheet 8 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MINFOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 45 FT/MIN FOR PURGE ON

Gross Weight 5250 lb (2381 kg)

TAKEOFF POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

PARTICLE SEPARATOR - PURGE OFFSNOW DEFLECTOR

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

OAT-°C

20

10

0

-10

-20

-30 -40

M407_FMS-28__FIG_4-7_(8_OF_8).WMF

Page 481: Bell 407 - Flight Manual, POH

16 DEC 2002 85

TC APPROVED BHT-407-FMS-28

Figure 4-8. Rate of climb – maximum continuous power (sheet 1 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MIN ABOVE2500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 5250 lb (2381 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X O

AT LIM

IT

OAT-°C

30

20

10

0

-10

-20

-30

-40

40

50

M407_FMS-28__FIG_4-8_(1_OF_8).WMF

Page 482: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

86 16 DEC 2002

Figure 4-8. Rate of climb – maximum continuous power (sheet 2 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MINFOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 5250 lb (2381 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

BASIC INLET

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

OAT-°C

20

10

0

-10

-20

-30

-40

M407_FMS-28__FIG_4-8_(2_OF_8).WMF

Page 483: Bell 407 - Flight Manual, POH

16 DEC 2002 87

TC APPROVED BHT-407-FMS-28

Figure 4-8. Rate of climb – maximum continuous power (sheet 3 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MIN ABOVE2000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 45 FT/MIN FOR PURGE ON

Gross Weight 5250 lb (2381 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFF

PARTICLE SEPARATOR - PURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

RE

AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

RE

AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

MA

X OA

T LIMIT

OAT-°C

30

20

10

0

-10

-20

-30

-40

40

50

M407_FMS-28__FIG_4-8_(3_OF_8).WMF

Page 484: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

88 16 DEC 2002

Figure 4-8. Rate of climb – maximum continuous power (sheet 4 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MINFOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 45 FT/MIN FOR PURGE ON

Gross Weight 5250 lb (2381 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

PARTICLE SEPARATOR - PURGE OFF

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

PR

ES

SU

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AL

TIT

UD

E

- F

EE

T

0 1 2 3 4 5 6 7 8 9 10

RATE OF CLIMB - M/SEC

0

1

2

3

4

5

6

PR

ES

SU

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AL

TIT

UD

E

- 1

00

0 M

ET

ER

S

OAT-°C

20

10

0

-10

-20

-30

-40

M407_FMS-28__FIG_4-8_(4_OF_8).WMF

Page 485: Bell 407 - Flight Manual, POH

16 DEC 2002 89

TC APPROVED BHT-407-FMS-28

Figure 4-8. Rate of climb – maximum continuous power (sheet 5 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MIN ABOVE1000 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 5250 lb (2381 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFFBASIC INLET

SNOW DEFLECTOR

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

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M407_FMS-28__FIG_4-8_(5_OF_8).WMF

Page 486: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

90 16 DEC 2002

Figure 4-8. Rate of climb – maximum continuous power (sheet 6 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MINFOR ANTI-ICE ON (5°C AND COLDER)

Gross Weight 5250 lb (2381 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

BASIC INLETSNOW DEFLECTOR

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

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M407_FMS-28__FIG_4-8_(6_OF_8).WMF

Page 487: Bell 407 - Flight Manual, POH

16 DEC 2002 91

TC APPROVED BHT-407-FMS-28

Figure 4-8. Rate of climb – maximum continuous power (sheet 7 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MIN ABOVE500 FT Hp FOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 45 FT/MIN FOR PURGE ON

Gross Weight 5250 lb (2381 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER OFF

PARTICLE SEPARATOR - PURGE OFFSNOW DEFLECTOR

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

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M407_FMS-28__FIG_4-8_(7_OF_8).WMF

Page 488: Bell 407 - Flight Manual, POH

BHT-407-FMS-28 TC APPROVED

92 16 DEC 2002

Figure 4-8. Rate of climb – maximum continuous power (sheet 8 of 8)

RATE OF CLIMB

REDUCE RATE OF CLIMB 130 FT/MINFOR ANTI-ICE ON (5°C AND COLDER)

REDUCE RATE OF CLIMB 45 FT/MIN FOR PURGE ON

Gross Weight 5250 lb (2381 kg)

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER ON

PARTICLE SEPARATOR - PURGE OFFSNOW DEFLECTOR

0 200 400 600 800 1000 1200 1400 1600 1800 2000

RATE OF CLIMB - FT/MIN

0

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Page 489: Bell 407 - Flight Manual, POH

A Subsidiary of Textron Inc.

POST OFFICE BOX 482 FORT WORTH, TEXAS 76101

Bell HelicopterCOPYRIGHTBELL ® HELICOPTER TEXTRON INC.AND BELL HELICOPTER TEXTRON INC.A DIVISION OF TEXTRON CANADA LTD.

ALL RIGHTS RESERVED

2002

COPYRIGHT NOTICE

BHT-407-FMS-CAA

UNITED KINGDOM REGISTEREDHELICOPTERS

CAA CERTIFIEDTBD XX, 2001

08 JANUARY 2002

This supplement shall be attached to the Bell HelicopterModel 407 Flight Manual when the helicopter is registered inthe United Kingdom.

Information contained herein supplements information ofbasic Flight Manual. For Limitations, Procedures, andPerformance Data not contained in this supplement, consultbasic Flight Manual.

ROTORCRAFTFLIGHT MANUAL

SUPPLEMENT

Page 490: Bell 407 - Flight Manual, POH

BHT-407-FMS-CAA

NP 08 JAN 2002

Additional copies of this publication may be obtained by contacting:Commercial Publication Distribution Center

Bell Helicopter Textron Inc.P. O. Box 482

Fort Worth, Texas 76101-0482

NOTICE PAGE

Page 491: Bell 407 - Flight Manual, POH

BHT-407-FMS-CAA

NOTE

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

LOG OF REVISIONS

Original ....................0 ....................... 08 JAN 02

LOG OF PAGES

REVISION REVISIONNO. NO.PAGE PAGE

Title............................................................ 0NP.............................................................. 0

A — B........................................................ 01 — 4......................................................... 05/6 ............................................................. 0

08 JAN 2002 A

Page 492: Bell 407 - Flight Manual, POH

BHT-407-FMS-CAA CAA APPROVED

CIVIL AVIATION AUTHORITYSAFETY REGULATION GROUPAVIATION HOUSESOUTH AREAGATWICK AIRPORTGATWICKWEST SUSSEX RH6 OYR

APPROVED:

LOG OF APPROVED REVISIONS

Original ....................0 ........................08 JAN 02

B 08 JAN 2002

Page 493: Bell 407 - Flight Manual, POH

CAA APPROVED BHT-407-FMS-CAA

PERFORMANCESection 4

4t4-1. TAKEOFF DISTANCE OVER 100-FOOT OBSTACLEThe Takeoff Distance Over 100-Foot Obstaclechar t (F igure 4 -1 ) p rov ides takeof fperformance data. The takeoff is initiated froma stabilized 4-foot (1.2 meter) skid heighthover. Increase power smoothly to hoverpower plus 20% torque or Takeoff Power,whichever is less, and simultaneously startnosedown pitch rotation so that the aircraftaccelerates along a flight path within thetakeoff corridor defined by the Height-Velocitydiagram (Figure 4-4 in Basic Manual). As thehelicopter goes through 50 KIAS, start noseup rotation while increasing power to TakeoffPower. With the aircraft starting to climb,continue accelerating up to 65 KIAS. Enginepower limitations are imposed to precludeunsafe nosedown attitude while in the flightpath required to remain clear of criticalheight-velocity l imitat ions. Good pilottechnique is requi red to ach ieve thepublished takeoff performance. Wind factorsare not considered.

NOTE

Downwind takeof fs a re notrecommended because the publishedtakeoff distance performance cannotbe achieved.

The power should be applied at a ratesufficient to expedite the manoeuverbut not so rapid as to overshoot thetorque va lue (approx imate ly 6

seconds). Once power is set, it shouldnot be further adjusted until the aircraftgoes through 50 KIAS. At this airspeed,start nose up rotation while increasingpower to Takeoff Power. While startingto climb, continue accelerating up to 65KIAS.

EXAMPLE:

What takeoff distance is required to clear a100-foot obstacle under the fol lowingconditions:

OAT 20°CHP 1500 feetGW 4500 pounds

SOLUTION:

Enter the Takeoff Distance Over 100-FootObstacle chart (Figure 4-1) at a pressurealtitude of 1500 feet, proceed horizontally tothe 20°C temperature l ine. Drop downvertically to the 4500 lb gross weight line andmove horizontally again to read a takeoffdistance of 1010 feet.

4-2. PARTIAL POWER CLIMBTorque limited partial power rate of climbcharts are presented for an aircraft with basicinlet installed and with the heater and engineanti-ice both OFF (Figure 4-2).

The recommended best rate of climb airspeedis 60 KIAS.

08 JAN 2002 1

Page 494: Bell 407 - Flight Manual, POH

BHT-407-FMS-CAA CAA APPROVED

EXAMPLE:

Find the maximum rate of climb that can beattained using 65% torque under the followingconditions:

HEATER OFFENGINE ANTI-ICE OFFOAT -10°CHP 7000 feetGW 4000 pounds

SOLUTION:

Enter the appropriate gross weight chart,4000 lbs (Figure 4-2, Sheet 1 of 2). Starting ata pressure altitude of 7000 feet, proceedhorizontally to the -10°C temperature line.Drop down vertically and read a rate of climbof 1225 feet per minute.

2 08 JAN 2002

Page 495: Bell 407 - Flight Manual, POH

CAA APPROVED BHT-407-FMS-CAA

Figure 4-1. Takeoff Distance Over 100-Foot Obstacle

08 JAN 2002 3

700

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TAKEOFF DISTANCEOVER 100 FOOT OBSTACLE

CONDITIONS:ROTOR RPM 100%ROTATION AIRSPEED 50 KIASCLIMB AIRSPEED 65 KIASZERO WIND

TECHNIQUE:LEVEL ACCELERATION FROM 4 FT (1.2 M) SKID

HEIGHT USING HOVER POWER + 20% TORQUE(NOT TO EXCEED 100%) UP TO 50 KIAS AND

CLIMB AT TAKEOFF POWER THEREAFTER

4000

4500

5000

5250

GROSS WEIGHT - LBS

MAX OAT

OAT - °C

-10-20

-30-40

010

2030

5040

3500 AND BELOW

Page 496: Bell 407 - Flight Manual, POH

BHT-407-FMS-CAA CAA APPROVED

Figure 4-2. Rate of Climb — Partial Power (Sheet 1 of 2)

4 08 JAN 2002

750 800 850 900 950 1000 1050 1100 1150 1200 1250 1300 1350RATE OF CLIMB - FT/MIN

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ENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER / ANTI-ICE OFF

BASIC INLET

3020

100

-10

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0

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EG C

40

GROSS WEIGHT = 4000 LBS

Page 497: Bell 407 - Flight Manual, POH

CAA APPROVED BHT-407-FMS-CAA

Figure 4-2. Rate of Climb — Partial Power (Sheet 2 of 2)

08 JAN 2002 5/6

450 475 500 525 550 575 600 625 650 675 700 725 750RATE OF CLIMB - FT/MIN

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0 -10

-30-20

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PARTIAL POWER RATE OF CLIMBRATE OF CLIMB LIMITED BY 65% TORQUE

ENGINE RPM 100%GENERATOR 180 AMPS

60 KIASHEATER / ANTI-ICE OFF

BASIC INLET

GROSS WEIGHT = 5000 LBS

Page 498: Bell 407 - Flight Manual, POH

LOG OF TEMPORARY REVISIONS

For tracking purposes, Temporary Revisions are now being numbered.

This Log of Temporary Revisions provides the current status of each Temporary Revision issued againstthe basic Flight Manual. It should be inserted at the back of the Flight Manual binder for quick and easyreference.

TEMP. REV. NO. TITLE DATE ISSUED DATE CANCELED

BHT-407-FM-1 FADEC Fault AnnunciationInterpretation

Revision 103 December 1996

15 June 2000

BHT-407-FM-1 NP Overspeed Trip Increase 03 December 1996 15 June 2000

BHT-407-FM-1 Airspeed Change to 125 KIAS and Temporary Pedal Stop

16 December 1998 10 March 1999

BHT-407-FM-1 FADEC Software Version 5.202 22 December 1998 17 December 2002

BHT407-FM-1 Hover Performance Correction for Temporary Tail Rotor Pedal Stop

10 March 1999 17 December 2002

BHT-407-FM-1 VNE Increase to 130 KIAS Reissue3 June 1999

17 December 2002

BHT-407-FM-1 FADEC Direct Reversion to Manual System, ASB 407-99-31

4 June 1999 17 December 2002

BHT-407-FM-1 VNE Increase to 140 KIAS Revision 127 June 2000

17 December 2002

BHT-407-FM-1 (TR-9)

Sustained Hover and Vertical Takeoff/Landing Operations with Tailwind

15 January 2002

BHT-407-FM-1 (TR-10)

Incorporation of Oil Cooler Blower Inlet Ducts and Bearing Airflow Shields

Revision 125 July 2002

BHT-407-FM-1

17 DECEMBER 2002