BHT-212VFR-FM-1

BHT-212VFR-FM-1

REISSUE — 14 AUGUST 1995REVISION 6 — 29 MAY 2012

ROTORCRAFTFLIGHT MANUAL

THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS

COPYRIGHT NOTICECOPYRIGHT 2012BELL ® HELICOPTER TEXTRON INC.AND BELL HELICOPTER TEXTRONCANADA LTD.

ALL RIGHTS RESERVED

NOTICE PAGE

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

Bell Helicopter Textron Inc.P. O. Box 482

Fort Worth, Texas 76101-0482

NP Rev. 5 17 OCT 2011

BHT-212VFR-FM-1

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.

PROPRIETARY RIGHTS NOTICE

DESTINATION CONTROL STATEMENT

These commodities, technology, or software were exported from theUnited States in accordance with the Export Administration Regulations(EAR). Diversion contrary to U.S. law prohibited. The data contained inthis manual are classified as ECCN EAR99.

29 MAY 2012 Rev. 6 A/B

BHT-212VFR-FM-1

LOG OF PAGES

REVISION REVISIONNO. NO.PAGE PAGE

NOTE

Revised text is indicated by a black vertical line. A revised page with only a vertical line next to the page number indicates that text has shifted or that non-technical correction(s) were made

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 Insert latest revision pages; dispose of superseded pages.

Original ......................0 ..................... 29 OCT 70Reissue......................0 .....................14 AUG 95Revision.....................1 .....................29 MAY 96Revision.....................2 ......................12 SEP 97

Revision .................... 3 ..................... 01 MAY 98Revision .................... 4 ......................02 DEC 02Revision .................... 5 ......................17 OCT 11Revision .................... 6 ..................... 29 MAY 12

Cover............................................................ 5Title .............................................................. 6NP................................................................. 5A/B................................................................ 6C/D................................................................ 6i – ii............................................................... 5iii/iv............................................................... 51-1 – 1-2 .......................................................51-3................................................................. 41-4................................................................. 21-4A/1-4B ..................................................... 21-5................................................................. 01-6 – 1-8 .......................................................51-9................................................................. 61-10............................................................... 51-11 – 1-12 ................................................... 01-13 – 1-15 ................................................... 11-16............................................................... 51-17 – 1-18 ................................................... 11-19 – 1-20 ................................................... 51-21/1-22 ...................................................... 12-1/2-2 .......................................................... 22-3................................................................. 02-4 – 2-5 .......................................................52-6................................................................. 22-7 – 2-8 .......................................................52-9................................................................. 02-10 – 2-16 ................................................... 52-17/2-18 ...................................................... 0

3-1 – 3-2....................................................... 53-3 – 3-4....................................................... 43-5 – 3-7....................................................... 23-8 ................................................................ 53-9 ................................................................ 63-10 – 3-11................................................... 53-12 – 3-15................................................... 23-16 – 3-19................................................... 03-20 .............................................................. 23-21 – 3-22................................................... 04-1 – 4-2....................................................... 54-3 – 4-4....................................................... 04-5/4-6.......................................................... 54-7 – 4-11..................................................... 54-12 – 4-26................................................... 04-27 – 4-78................................................... 24-79/4-80...................................................... 25-1/5-2.......................................................... 05-3 ................................................................ 05-4 ................................................................ 55-5/5-6.......................................................... 55-7 – 5-13..................................................... 05-14 – 5-17................................................... 55-18 – 5-24................................................... 05-25/5-26...................................................... 0A-1/A-2......................................................... 5A-3 – A-4...................................................... 5A-5/A-6......................................................... 5

LOG OF REVISIONS

29 MAY 2012 Rev. 6 C/D

BHT-212VFR-FM-1

Original ..................... 0...................... 29 OCT 70Reissue ..................... 0......................14 AUG 95Revision .................... 1......................29 MAY 96Revision .................... 2...................... 12 SEP 97

Revision ....................3 ..................... 01 MAY 98Revision ....................4 ..................... 02 DEC 02Revision ................... 5* .................... 17 OCT 11Revision ................... 6* .................... 29 MAY 12

LOG OF FAA/ODA* APPROVED REVISIONS

ORGANIZATION DESIGNATION AUTHORIZATION (ODA)

APPROVED DATE

FRED STELLARBHTI ODA LEAD ADMINISTRATORODA-710621-SWP.O. BOX 482FT. WORTH, TX 76101

BHT-212VFR-FM-1

GENERAL INFORMATION

17 OCT 2011 Rev. 5 iECCN EAR99

ORGANIZATION

This Fl ight Manual is divided into f ivesections and an appendix:

Section 1 through Section 4 contain FAAapproved data necessary to operatehelicopter in a safe and efficient manner.

Section 5 contains weight and balance datanecessary for flight planning.

Appendix A contains a list of FAA approvedsupplements for optional equipment, whichshall be used in conjunction with basic FlightManual when respective optional equipmentkits are installed.

The Manufacturer ' s Data manual(BHT-212-MD-1) contains information to beused in conjunction with the Flight Manual.The Manufacturer's Data manual is dividedinto four sections:

TERMINOLOGY

WARNINGS, CAUTIONS, AND NOTES

Warnings, cautions, and notes are usedthroughout th is manual to emphasizeimportant and critical instructions and areused as follows:

WARNING

AN OPERATING PROCEDURE,PRACTICE, ETC., WHICH, IF NOTCORRECTLY FOLLOWED, COULDRESULT IN PERSONAL INJURY ORLOSS OF LIFE.

CAUTION

AN OPERATING PROCEDURE,PRACTICE, ETC., WHICH, IF NOTSTRICTLY OBSERVED, COULDRESULT IN DAMAGE TO ORDESTRUCTION OF EQUIPMENT.

NOTE

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

USE OF PROCEDURAL WORDS

Procedura l word usage and in tendedmeaning, which has been adhered to inpreparing this manual, is as follows:

SHALL and MUST have been used onlywhen application of a procedure ismandatory.

SHOULD has been used only whenapplication of a procedure isrecommended.

Section 1 LIMITATIONS

Section 2 NORMAL PROCEDURES

Section 3 EMERGENCY AND MALFUNCTION PROCEDURES

Section 4 PERFORMANCE

Section 5 WEIGHT AND BALANCE

Appendix A OPTIONAL EQUIPMENT SUPPLEMENTS

Section 1 SYSTEMS DESCRIPTION

Section 2 HANDLING AND SERVICING

Section 3 CONVERSION TABLES

Section 4 EXPANDED PERFORMANCE

BHT-212VFR-FM-1

ii Rev. 5 17 OCT 2011 ECCN EAR99

MAY and NEED NOT have been usedonly when application of a procedure isoptional.

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

ABBREVIATIONS AND ACRONYMS

Abbreviations and acronyms used throughoutthis manual are defined as follows:

AC — Alternating Current

AGL — Above Ground Level

ALT — Altitude

ALTN — Alternate

AMP(S) — Ampere(s)

ANTI COLL — Anticollision

BLWR — Blower

C — Celsius

CAS — Calibrated Airspeed

C BOX — Combining Gearbox

CG — Center of Gravity

COND — Conditioner

DC — Direct Current

DECR — Decrease

DEG — Degree(s)

ELT — Emergency Locator Transmitter

ENG — Engine

EXT — Extinguisher

F — Fahrenheit

FAA — Federal Aviation Administration

FAIL — Failure

FDR — Flight Data Recorder

FS — Fuselage Station

FT — Foot, Feet

FWD — Forward

GAS PROD RPM (N1)

— Gas Producer RPM

GEN — Generator

GOV — Governor

GW — Gross Weight

HD — Density Altitude

HP — Pressure Altitude

HTR — Heater

HV — Height-Velocity

HYDR SYS — Hydraulic System

IAS — Indicated Airspeed

ICS — Intercommunication System

IGE — In Ground Effect

IGN — Ignition

IN — Inch(es)

INCR — Increase

INTCON — Interconnect

INV — Inverter

ITT — Interturbine Temperature

KCAS — Knots Calibrated Airspeed

KG — Kilogram(s)

KIAS — Knots Indicated Airspeed

KTAS — Knots True Airspeed

LB — Pound(s)

LT — Light

M — Meter(s)

MAN — Manual

MAX — Maximum

MIN — Minimum, Minute(s)

MM — Millimeter(s)

N1 — Gas Producer RPM

BHT-212VFR-FM-1

17 OCT 2011 Rev. 5 iii/ivECCN EAR99

N2 — Power Turbine RPM

NAV — Navigation

NON ESS — Non Essential

NORM — Normal

NR — Rotor RPM

OAT — Outside Air Temperature

OEI — One Engine Inoperative

OGE — Out of Ground Effect

OVHT — Overheating

OVRD — Override

PART SEP — Particle Separator

PRESS — Pressure

PRI — Primary

PSI — Pound(s) per Square Inch

PWR — Power

QTY — Quantity

REL — Release

ROTOR BK — Rotor Brake

RPM — Revolutions per Minute

SEL — Selection

SYS — System

TEMP — Temperature

TEMP CONT — Temperature Control

VAC — Volts Alternating Current

VCAL — Calibrated Airspeed

VDC — Volts Direct Current

VFR — Visual Flight Rules

VNE — Never Exceed Speed

VTOCS — Takeoff Climbout Speed

WARN — Warning

WAT — Weight Altitude Temperature

XFEED — Crossfeed

XMSN — Transmission

FAA APPROVED BHT-212VFR-FM-1

17 OCT 2011 Rev. 5 1-1ECCN EAR99

Section 1LIMITATIONS

1TABLE OF CONTENTS

Paragraph PageSubject Number Number

Introduction ............................................................................................ 1-1 ........... 1-3Basis of Certification ............................................................................. 1-2 ........... 1-3Types of Operation ................................................................................ 1-3 ........... 1-3Flight Crew ............................................................................................. 1-4 ........... 1-3Configuration ......................................................................................... 1-5 ........... 1-3

Required Equipment.......................................................................... 1-5-A ....... 1-3Optional Equipment........................................................................... 1-5-B ....... 1-4Doors Open/Removed ....................................................................... 1-5-C ....... 1-4Passengers......................................................................................... 1-5-D ....... 1-4Cargo................................................................................................... 1-5-E ....... 1-4

Internal Cargo Configuration ........................................................ 1-5-E-1 .... 1-4Baggage.......................................................................................... 1-5-E-2 .... 1-4

Weight and Center of Gravity ............................................................... 1-6 ........... 1-4Weight ................................................................................................. 1-6-A ....... 1-4Center of Gravity................................................................................ 1-6-B ....... 1-4

Longitudinal Center of Gravity ..................................................... 1-6-B-1 .... 1-4Lateral Center of Gravity ............................................................... 1-6-B-2 .... 1-5

Airspeed.................................................................................................. 1-7 ........... 1-5Altitude.................................................................................................... 1-8 ........... 1-5Maneuvering........................................................................................... 1-9 ........... 1-5

Prohibited Maneuvers ....................................................................... 1-9-A ....... 1-5Climb and Descent............................................................................. 1-9-B ....... 1-5

Height-Velocity....................................................................................... 1-10 ......... 1-5Ambient Temperatures.......................................................................... 1-11 ......... 1-6Electrical ................................................................................................. 1-12 ......... 1-6

Battery................................................................................................. 1-12-A ..... 1-6Generator............................................................................................ 1-12-B ..... 1-6Starter ................................................................................................. 1-12-C ..... 1-6Ground Power Unit ............................................................................ 1-12-D ..... 1-6

Power Plant ............................................................................................ 1-13 ......... 1-6Gas Producer RPM (N1)..................................................................... 1-13-A ..... 1-7

Twin Engine Operation.................................................................. 1-13-A-1 .. 1-7One Engine Inoperative (OEI) ....................................................... 1-13-A-2 .. 1-7

Power Turbine RPM (N2) ................................................................... 1-13-B ..... 1-7Interturbine Temperature .................................................................. 1-13-C ..... 1-7Engine Torque.................................................................................... 1-13-D ..... 1-8

BHT-212VFR-FM-1 FAA APPROVED

1-2 Rev. 5 17 OCT 2011 ECCN EAR99

TABLE OF CONTENTS (CONT)


One Engine Inoperative (OEI) ....................................................... 1-13-D-1.. 1-8Fuel Pressure ..................................................................................... 1-13-E ..... 1-8Engine Oil Pressure........................................................................... 1-13-F ..... 1-8Engine Oil Temperature .................................................................... 1-13-G..... 1-8Combining Gearbox Oil Pressure .................................................... 1-13-H..... 1-8Combining Gearbox Oil Temperature.............................................. 1-13-J...... 1-9

Transmission ......................................................................................... 1-14......... 1-9Transmission Oil Pressure ............................................................... 1-14-A..... 1-9Transmission Oil Temperature......................................................... 1-14-B..... 1-9Transmission Torque ........................................................................ 1-14-C..... 1-9

Twin Engine Operation (Transmission Scale (Δ)) ....................... 1-14-C-1.. 1-9Rotor ....................................................................................................... 1-15......... 1-9

Rotor RPM — Power ON ................................................................... 1-15-A..... 1-9Rotor RPM — Power OFF.................................................................. 1-15-B..... 1-9

Hydraulic ................................................................................................ 1-16......... 1-9Hydraulic Pressure ............................................................................ 1-16-A..... 1-9Hydraulic Temperature...................................................................... 1-16-B..... 1-10

Fuel and Oil ............................................................................................ 1-17......... 1-10Fuel ..................................................................................................... 1-17-A..... 1-10Oil — Engine and Combining Gearbox............................................ 1-17-B..... 1-10Oil — Transmission, Intermediate, and Tail Rotor Gearboxes...... 1-17-C..... 1-10

Rotor Brake ............................................................................................ 1-18......... 1-10Landing Gear.......................................................................................... 1-19......... 1-10Instrument Markings and Placards ...................................................... 1-20......... 1-10Heater...................................................................................................... 1-21......... 1-10

LIST OF FIGURES

Figure PageSubject Number Number

Weight-Altitude-Temperature Limitations for Takeoff, Landing, andIn-Ground Effect Maneuvers Chart ...................................................... 1-1........... 1-11Gross Weight Center of Gravity Chart................................................. 1-2........... 1-12Placards and Decals.............................................................................. 1-3........... 1-13Single Engine Height-Velocity Chart ................................................... 1-4........... 1-15Instrument Markings ............................................................................. 1-5........... 1-16


Section 1LIMITATIONS

1-1. INTRODUCTION

NOTECompliance with limitations in thissection is required by appropriateoperating rules.

Minimum and maximum limits, and normal andcautionary operating ranges for helicopter andsubsystems are indicated by instrumentmarkings and placards. Instrument markingsand p lacards represent ae rodynamiccalculations that are substanti ated by flighttest data.

Anytime an operating limit is exceeded, anappropriate entry shall be made in helicopterlog book. E ntry shall state which limit wasexceeded, duration of time, extreme valueattained, and any additional informationessential in de termining maintenance actionrequired.

1-2. BASIS OF CERTIFICATIONThis helicopter is certified under FAR Part 29,Category B.

1-3. TYPES OF OPERATIONThe basic configured helicopter is app rovedas a fifteen-place helicopter and is certified foroperation in day or night VFR non-icingconditions.

1-4. FLIGHT CREW

Minimum cockpit (FS 47.0) weight is170 pounds (77.1 kilograms). Referto Section 5.

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

Left crew seat may be used f or an additionalpilot for VFR day and night operations whenapproved dual controls and copilot instrumentkits are installed.

Refer to applicable operating rulesfor internal cargo operations.

1-5. CONFIGURATION

1-5-A. REQUIRED EQUIPMENT

Heated pitot-static system

Pilot windshield wiper

Force trim system

NOTE

NOTE

02 DEC 2002 Rev. 4 1-3

BHT-212VFR-FM-1

1-5-8. OPTIONAL EQUIPMENT

Refer to appropriate Flight ManualSupplement(s) for additional limitations,pro c e d u res, and per f.o r man ~ e d at arequired for optional equipment Installed.Refer to Appendix A.

1-5-C. DOORS OPEN/REMOVED

Helicopter may be flown with doors openor removed only with Bell Helicopterstandard interior installed. Doorconfiguration shall be:

Both crew doors removed.

Both sliding doors locked open orremoved with both hinged panelsinstalled or removed.

In all cases, door configuration shall besymmetrical.

NOTE

Opening or removing doors shiftshelicopter center of gravity andreduces VNE• Refer to Section 5and to Airspeed Limitations.

1-5-0. PASSENGERS

NOTE

Refer to Section 5 for loadingtables to be used in weight/CGcomputations.

With passenger seat kit installed, thehelicopter is certified for operations as afifteen place aircraft.

The above loading does not apply if cargoor a combination of cargo and passengersare being transported. It shall be theresponsibility of the pilot to ensu.rehelicopter is properly loaded so entIreflight is conducted within limits of grossweight center of gravity charts (Figure 12).

1-4 Rev. 2

FAA APPROVED

1-5-E. CARGO

1-5-E-1. INTERNAL CARGOCONFIGURATION

Allowable deck loading for cargo is 100pounds per square foot (4.9 kilograms/100square centimeters). Deck mountedtiedown fittings are provided and have anairframe structural capacity of 1250pounds (567.0 kilograms) vertical and 500pounds (226.8 kilograms) horizontal perfitting. Provisions for installation of .cargotiedown fittings are incorporated In aftcabin bulkhead and transmission supportstructure and have an airframe structuralcapacity of 1250 pounds (567.0 kilograms)at 90 degrees to bulkhead and 500 pounds(226.8 kilograms) in any direction parallelto bulkhead. Cargo shall be secured by anapproved restraint method that will notimpede access to cargo in an emergency.All cargo and equipment shall be securely Itied down when operating with aft cabindoors open or removed.

1-5-E-2. BAGGAGE

Baggage compartment maximum .allowableloading is 400 pounds (181.4 kilograms),not to exceed 100 pounds per square foot(4.9 kilograms/100 square centimeters).

1-6. WEIGHT AND CENTER OFGRAVITY

1-6-A. WEIGHT

Maximum GW is 11,200 pounds (5080.3kilograms).

Refer to Weight-altitude-temperaturelimitations for takeoff, landing and inground effect maneuvers chart (figure 1-1).

1-6-8. CENTER OF GRAVITY

1-6-B-1. LONGITUDINAL CENTEROF GRAVITY

FAA APPROVED

Longitudinal CG limits are from station130.0 to 144.0.

Longitudinal CG operational range isvariable (figure 1-2), depending upon GW,and shall be computed from weight andbalance data.

BHT-212VFR-FM-1

NOTE

Station 0 (datum) is located 20inches (508 millimeters) aft ofmost forward point of cabin nose.

Rev. 2 1-4A11-4B I

FAA APPROVED

1-6-8-2. LATERAL CENTER OFGRAVITY

Lateral CG limits are 4.7 inches (119.4millimeters) left and 6.5 inches (165.1millimeters) right of fuselage centerline.

1-7. AIRSPEED

7500 pounds (3402 kilograms) GW - VNE130 KIAS.

11,200 pounds (5080.3 kilograms) GW VNE 100 KIAS.

Doors open/off operation - VNE 100 KIAS(any GW).

VNE decreases linearly from 130 knots to100 knots with GW (Refer to Placards AndDecals, Figure 1-3).

VNE decreases 3 knots per 1000 feet above3000 feet Ho.

Maximum airspeed when operating abovemaximum continuous torque (87.5%) is 80KIAS.

1-8. ALTITU DE

Maximum operating - 20,000 feet Hp •

Refer to applicable operating rules for highaltitude oxygen requirements.

··················ti CAUTION •t•••••••••••••••••t

MONITOR ITT WHEN STARTINGENGINE IN MANUAL FUELCONTROL MODE.

Above 15,000 feet Hp , restart shall beaccomplished in manual fuel control modeonly. (No airspeed restrictions.)

Below 15,000 feet H p , restart may beattempted in either manual or automaticfuel control mode.

BHT-212VFR-FM-1

1-9. MANEUVERING

1-9-A. PROHIBITED MANEUVERS

Aerobatic maneuvers are prohibited.

1-9-B. CLIMB AND DESCENT

Refer to Section 4, PERFORMANCE.

1-10. HEIGHT-VELOCITY

The height-velocity limitations are criticalin the event of a single engine failureduring takeoff, landing, and otheroperation near the surface (figure 1-4).The AVOID area of the Height-Velocitychart defines the combinations of airspeedand height above ground from which asafe single engine landing on a smooth,level, firm surface cannot be assured.

The H-V chart is valid only when theWeight-Altitude-Temperature limitationsare not exceeded (figure 1-1). The diagramdoes not define the conditions whichassure continued flight following anengine failure nor the conditions fromwhich a safe power off landing can bemade.

When takeoffs are made in accordancewith HV charts, proceed as follows:

Determine hover torque at a four footskid height.

Perform takeoff with no more than15% torque above hover power whileaccelerating to Takeoff ClimboutSpeed (VTOCS)' Refer to Section 4 forVTOCS '

NOTE

Downwind takeoffs are notrecommended since publishedtakeoff distance performance willnot be achieved. When near zerowind conditions prevail, determinetrue direction of wind.

1-5


1-6 Rev. 5 17 OCT 2011 ECCN EAR99

1-11. AMBIENT TEMPERATURES

Maximum sea level ambient air temperaturefor operation is +52°C (+125°F) and decreaseswith altitude at standard lapse rate (2°C per1000 feet H P ) . M in imum ambien t a i rtemperature at all altitudes is -54°C (-65°F).Refer to Weight -Al t i tude-TemperatureL imi ta t ions for Takeoff , Landing, andIn-Ground Ef fect Maneuvers Char t(Figure 1-1).

1-12. ELECTRICAL

1-12-A. BATTERY

WARNING

BATTERY SHALL NOT BE USEDFOR ENGINE START AFTERILLUMINATION OF BATTERY TEMPLIGHT (IF INSTALLED). BATTERYSHALL BE REMOVED ANDSERVICED IN ACCORDANCE WITHMANUFACTURER’S INSTRUCTIONSPRIOR TO RETURNING BATTERY TOSERVICE.

Maximum battery case temperature — 54.5°C(130°F).

Maximum battery internal temperature —62.7°C (145°F).

1-12-B. GENERATOR

NOTE

To attain published single engineperformance, generator loads shouldnot exceed 75 amps each during twinengine operation.

Ammeter needle may deflect fullscale momentarily during generatorassisted start of second engine.

1-12-C. STARTER

Starter energizing times shall be limited asfollows:

30 seconds ON

60 seconds OFF

30 seconds ON

5 minutes OFF

30 seconds ON

15 minutes OFF

Above energizing cycle may then be repeated.

Above 15 ,000 H P, res tar t sha l l beaccomplished in manual fuel control modeonly.

Below 15,000 HP, restart may be attempted ineither manual or automatic fuel control mode.

1-12-D. GROUND POWER UNIT

28 VDC ground power units for starting shallbe rated at a minimum of 400 amps and amaximum of 1000 amps.

1-13. POWER PLANT

Pratt and Whitney Canada PT6T-3B or PT6T-3.

NOTE

Opera t ion in 2 1 /2 minu te or30 minute OEI range is intended foremergency use only, when oneengine becomes inoperative due toactual malfunction. OEI ranges shallnot be used for training.

Maximum 150 amps per ammeter



1-13-A. GAS PRODUCER RPM (N1)

1-13-A-1. TWIN ENGINE OPERATION

PT6T-3B (Gauge 212-075-037-101/-105)

PT6T-3B (Gauge 212-075-037-113)

PT6T-3

1-13-A-2. ONE ENGINE INOPERATIVE (OEI)

PT6T-3B (Gauge 212-075-037-101/-105)

PT6T-3B (Gauge 212-075-037-113)

1-13-B. POWER TURBINE RPM (N2)

1-13-C. INTERTURBINE TEMPERATURE

PT6T-3B (TWIN ENGINE OPERATION)

NOTE

If ITT remains above 810°C longerthan 15 seconds or exceeds otherlimits, ITT and duration shall berecorded in helicopter logbook.Re fer to Pra t t and Whi tneyMaintenance Manual for inspectionrequirements.

PT6T-3B (SINGLE ENGINE OPERATION)

Continuous operation 61 to 100.8%

Maximum continuous 100.8%

Maximum for takeoff 100.8%

Maximum transient (not to exceed 30 seconds)

102.4%

Continuous operation 61 to 101.8%


Maximum for takeoff 101.8%


103.4%

Maximum continuous 100%


101.5%

2 1/2 minute range 100.8 to 102.4%

Maximum 102.4%

2 1/2 minute range 101.8 to 103.4%

Maximum 103.4%

Takeoff 100%

Minimum 97%

Continuous operation 97 to 100%

Maximum continuous 100%

Transient (not to exceed 10 seconds)

101.5%

Continuous operation 300 to 765°C

Maximum continuous 765°C

5 minute takeoff range 765 to 810°C

Maximum for takeoff 810°C


850°C

Maximum for starting (not to exceed 2 seconds above 960°C)

1090°C

30 minute OEI range 765 to 822°C

2 1/2 minute OEI range 822 to 850°C

Maximum OEI 850°C


1-8 Rev. 5 17 OCT 2011 ECCN EAR99

PT6T-3

1-13-D. ENGINE TORQUE

NOTE

For normal twin engine operation,maximum permissible torque needlesplit is 4% total.

1-13-D-1. ONE ENGINE INOPERATIVE (OEI)

PT6T-3B — INSTRUMENT MARKED 71.8%RED LINE

PT6T-3B — INSTRUMENT MARKED 79.4%RED LINE

PT6T-3

1-13-E. FUEL PRESSURE

1-13-F. ENGINE OIL PRESSURE

1-13-G. ENGINE OIL TEMPERATURE

NOTE

Helicopters with PT6T-3B engineshall use only gauges marked 0 to115°C. Helicopters with PT6T-3engine may use either gauge.

PT6T-3B OR PT6T-3

PT6T-3 ONLY

1-13-H. COMBINING GEARBOX OILPRESSURE

5 minute range (twin engine operation)

765 to 810°C

30 minute range (single engine operation)

765 to 810°C

Maximum continuous limit (single or twin engine operation)

765°C

Power change transient limit (5 seconds above 810°C not to exceed 850°C)

850°C

Starting transient limit (not to exceed 2 seconds above 810°C)

1090°C


30 minute power range 63.9 to 71.8%

Maximum 71.8%



Maximum 79.4%



Maximum 71.8%

Minimum 4 PSI

Continuous operation 4 to 35 PSI

Maximum 35 PSI

Minimum(below 79% N1)

40 PSI

79 to 100% N1 80 to 115 PSI

Maximum 115 PSI

Minimum 0°C


Maximum 115°C

Minimum 5°C

Maximum 107°C

Minimum for idle 40 PSI

Operation below 94% N2 40 to 60 PSI


Maximum 80 PSI


29 MAY 2012 Rev. 6 1-9ECCN EAR99

1-13-J. COMBINING GEARBOX OILTEMPERATURE

NOTE

Helicopters with PT6T-3B engineshall use only gauges marked 0 to115°C. Helicopters with PT6T-3engine may use either gauge.

PT6T-3B OR PT6T-3

PT6T-3 ONLY

1-14. TRANSMISSION

1-14-A. TRANSMISSION OIL PRESSURE

1-14-B. TRANSMISSION OILTEMPERATURE

1-14-C. TRANSMISSION TORQUE

1-14-C-1. TWIN ENGINE OPERATION(TRANSMISSION SCALE (Δ))

1-15. ROTOR

1-15-A. ROTOR RPM — POWER ON

1-15-B. ROTOR RPM — POWER OFF

1-16. HYDRAULIC

NOTE

Refer to BHT-212-MD-1 for approvedfluids, vendors, and allowable mixingof approved fluids.

Hydraulic fluid MIL-PRF-87257 (NATO H-538)or MIL-PRF-5606 (NATO H-515) may be usedat all ambient temperatures.

Both hydraulic systems shall be operativeprior to takeoff.

1-16-A. HYDRAULIC PRESSURE

Minimum 0°C

Maximum 115°C

Minimum 0°C

Maximum 107°C

Minimum for idle 30 PSI

Idle range 30 to 40 PSI


Maximum 70 PSI


Maximum 110°C


Takeoff power range(5 minutes)

87.5 to 100%

Maximum 100%

Minimum 97%

Maximum 100%

Minimum 91%

Maximum 104.5%

Minimum 600 PSI

Caution range 600 to 900 PSI

Normal operation 900 to 1100 PSI

Maximum 1100 PSI


1-10 Rev. 5 17 OCT 2011 ECCN EAR99

1-16-B. HYDRAULIC TEMPERATURE

1-17. FUEL AND OIL

1-17-A. FUEL

NOTE

Refer to BHT-212-MD-1 for approvedfuels.

Fuel conforming to ASTM D-6615 Jet B, NATOF-40, or MIL-DTL-5624 Grade JP-4 may beused at all ambient air temperatures.

Fuel conforming to ASTM D-1655 Jet A or A-1,NATO F-44, MIL-DTL-5624 Grade JP-5, NATOF-34, or MIL-DTL-83133 Grade JP-8 is limitedto ambient air temperatures above -30°C(-22°F).

1-17-B. OIL — ENGINE AND COMBININGGEARBOX

NOTE

Refer to BHT-212-MD-1 for approvedvendors.

Oil conforming to PWA Specification No. 521Type I and MIL-PRF-7808 (NATO O-148) maybe used at all ambient air temperatures.

Oil conforming to PWA Specification No. 521Type II and MIL-PRF-23699 (NATO O-156) maybe used at all ambient air temperatures above-40°C (-40°F).

1-17-C. OIL — TRANSMISSION,INTERMEDIATE, AND TAILROTOR GEARBOXES

Oil conforming to MIL-PRF-7808 (NATO O-148)may be used at all ambient temperatures.

O i l conforming to DOD-PRF-85734 orMIL-PRF-23699 (NATO O-156) may be used atall ambient air temperatures above -40°C(-40°F).

NOTE

DOD-PRF-85734 or MIL-PRF-23699 isrecommended.

1-18. ROTOR BRAKE

Engine starts with rotor brake engaged areprohibited. Rotor brake application is limitedto ground operation and shall not be applieduntil engines have been shut down andROTOR RPM has decreased to 40% or less.

1-19. LANDING GEAR

Refer to BHT-212-MD-1.

1-20. INSTRUMENT MARKINGSAND PLACARDS

Refer to Figure 1-3 for placards and decals.Refer to Figure 1-5 for instrument rangemarkings.

1-21. HEATER

Heater shall not be operated when OAT isabove 21°C (69.8°F).

Maximum 88°C


NOTE: ALLOWABLE GROSS WEIGHTS OBTAINED FROM THIS CHART MAY EXCEEDCONTINUOUS HOVER CAPABILITY UNDER CERTAIN AMBIENT CONDITIONS.REFER TO HOVER CEILING CHARTS IN SECTION 4

8000

6000t:a

4000 ::J:

-2000

2000

o

14,000

12,000

10,000

-40009 10 11 12 LB X 1000

Ir--~I----"'I----r-I ---'138 42 46 50 54 KG X 100

GROSS WEIGHT

86040

14,000 FT. DEN. ALT. UMIT

-40 -20 0 20OAT - °c

,..~V" V /\ 1\

..bY W C\/.

\.... \ MA "1M ~M

/ Y ~ V\ \ GJ; OS n~ EIG HT/ . or

/ / V \~ \/ / / / " \l'() ,0

/ / ~7 / \~ \

/ 1/ ~./ / \ \/ / ~';I /

\ r\.... v

/ ~// /\ \:ce /

0 V / ~ / V It=:/ V / .~V /r;~

/ / Y ~~~r~ I

I / / ~~ !Y I:/1

V J / ? ~~'" l'()//1

/ V f{~ .In;v }

/ / ~~~ / /1_C"I

/ iL4v !/ W I

I / /I

J

212VFR-FM-1-1

Figure 1-1. Weight-altitude-temperature limitations for takeoff, landing and in groundeffect maneuvers chart

1·11


7,000

9,000

8,000

L:'·:'·:·:·:·:·:·:·:·:·:·:·:·:·:·:·:·:·:·:·:·:·:·:·:·:.:.:.:.:.:•.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.,:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.11,000

6,000

en 10,000cz;:)

oc.II-:::J:C)

~enenoex:C)

.......: :.:.:.:.:.:.:.:.:,.:. :.:.:.:.:.:.:.:.:.:.:. :.:.:.:.:.:.:.:.:.:.:. ::.:.:.:.:.:.:.:.:.:.: .:.:.:.:.:.:.:.:.:.:.: .:.:.:.:.:.:.:.:.:.:.: .:.:,.:,.:.:.:.:.:.:. :.:,.:.:.:.:.:.:.:.:. :.:.:.:.:.:.:.:.:.:.:. :.:.:.:.:.:.:.:.:.:.:.

5,000130 132 134 136 138 140 142

LONGITUDINAL C.G. STATION - INCHES

144

212VFR-FM-1-2

Figure 1-2. Gross weight center of gravity chart

1-12

FAA APPROVED

DO NOT OPERATEHEATER ABOVE 21

DEG C OUT AIR TEMP

BHT-212VFR-FM-1

BAGGAGE FIRE

TEST SWITCH

~~~

~~ .:"lIl

~~

IN ALTN POSITION MAINTAININSTRUMENT ACCURACY BY

CLOSING WINDOWS AIRVENTSAND TURNING HEATER OFF

(if installed)

en 11200...J..:. 10500G10000W 9500~ 9000~ 8500~ 8000~ 7500

100 110 120 130INDICATED AIR SPEED-KNOTS

DECREASE VNE 3 KNOTS PER 1000 FT.ALT ABOVE 3000 FT.

FUEL SYSTEM CAPACITYTOTAL BASIC SHIP 1400 LB.WITH 044 KIT 1700 LBWITH 045 KIT 2600 LB.

(TYPICAL)

PANEL AFT END OF OVERHEAD CONSOLE

THIS HEll CO PTE R MUS T BE 0 PER ATE DIN COMPLIANCE WITH THE OPERATING

LIMITATIONS SPECIFIED IN THE FAAAPPROVED ROTORCRAFT fliGHT MAN.

212VFR·FM-1·3-1

Figure 1-3. Placards and decals

Rev. 1 1-131


TWIN & 30 MIN OEI 100.8%2'/2 MIN OEI 102.4%

TWIN & 30 MIN OEI 101.8%2'/2 MIN OEI 103.4%

NOTES:

ffi USED WITH GAS PRODUCER GAGE PIN 212-075-037-101

& USED WITH GAS PRODUCER GAGE PIN 212-075-037-113

212VFR-FM-1-3-2

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

1-14 Rev. 1


450 r--~-~-r--"""-..,.---r---r--.,......---r---r--~"""'""'T-""'T"'"-'

50KNOTS

AVOID FLIGHTSIN SHADED AREAS

NOTE: THE HELICOPTERCONFIGURATIONSHALL COMPLY WITH THE WEIGHTALTITUDE-TEMPERATURECHARTFOR HEIGHT-VELOCITY DIAGRAMTO BE VALID

~~~=±==~1000LBLESSTHAN ~~-+_+-~WATllMIT

~::\i--+-~I---lWAT LIMIT

400 l--+--+--+---+---+-1

350 HI,:~+---1---+--+--4--I--+--4--+--+--+--+--t---;

l-

t::: 300 ,I.L.

Figure 1-4. Single engine height-velocity chart

Rev. 1 1-15


1-16 Rev. 5 17 OCT 2011 ECCN EAR99

Figure 1-5. Instrument Markings (Sheet 1 of 6)

GAS PRODUCER RPM (N1)

212-075-037-101/-1051

212-075-037-1131

1 Either gauge may be installed, in pairs.

212_FM_VFR_01_0005a+

NOTE


INSTRUMENT MARKINGS - PT6T-38INTERTURBINE TEMPERATUAE (ITI)

-c:::J-,

300 to 765cC

765 to Bloce

Continuous operation

5 minute takeoff range

Maximum for takeoff

Maximum 30 minute DEI

Maximum 2V~ minute DEI

Mall;mum for slarting12 seconds max. above960D e)

ENGINE Oil TEMPERATURE

& NOTE: This gage may be used in helicopters equipped with either PT6T·3B or PT6T·3 engine.- DoC

Oto115OC- , , SoC

& ENGINE Oil PRESSURE- 40 PSI

c:::J 40 to 80 PSI

80 to ',5 PSI- 115 PSI

Minimum


Maximum

Minimum lor flight idle

Conditional operation Below 79% NI RPM


Maximum

COMBINING GEAABOXOIL TEMPERATURE

_ DoC Minimum


Maximum

Conditional operation Below 94% Nil RPM

Minimum for flight idle

_ 11SoC

COMBINING GEARBOX OIL PRESSURE

_ 40PSI

c:=J 40 to 60 PSI

,\ I,

t"lS 1°8 ....10 OIL til.-'

sT't PS1P4"

°/Xl0\"// - "III

c:J 60 to BO PSI

_ BOPSI


Maximum

212VFR·FM·'·5·2

Figure 1·5. Instrument markings (Sheet 2 of 6)

Rev. 1 1-171

BHT·212VFR-FM·l FAA APPROVED

INSTRUMENT MARKINGS - PT6T-3

GASPRODUCER

TACHOMETER

55% to 100%100%

ENGINE OilTEMPERATURE AND

PRESSURE&. NOTE: This gage Is fot helicopters equipped with PT6T·3 engine only.

~

(s 10 Oil 10JrlI 5 Tc::::::> P

X 10 5

~.o.~ n->';

~

TEMPERATURE IT!

PRESSURE (PI

40 PSI40 to 80 PSI80 to 115 PSI115 PSI

COMBINING GEARBOXOil TEMPERATURE

AND PRESSURE

TEMPERATURE HI

212VFR-FM-1-5-J

O·C0° 10 lQ7°el07°e

PRESSURE IPI

40 PSI40 to 60 PSI60 to 80 PSIBOPSI

Figure 1-5. Instrument markings (Sheet 3 of 6)

11-18 Rev. 1


17 OCT 2011 Rev. 5 1-19ECCN EAR99


212_FM_VFR_01_0005d

INSTRUMENT MARKINGS — PT6T-3

INTERTURBINE TEMPERATURE

200 to 765°C765 to 810°C810°C

DUAL TORQUE INDICATOR

TRANSMISSION (TWIN ENGINE OPERATION)

0 to 87.5%87.5 to 100%100%

ENGINE (SINGLE ENGINE OPERATION)

63.9 to 71.8%71.8%

1 212-070-240

1 212-075-562

1

NOTEEither gauge may be installed.

7

234

56

ITT°Cx100

8

12

9


1-20 Rev. 5 17 OCT 2011 ECCN EAR99


212_FM_VFR_01_0005e

FUEL PRESSURE

4 PSI4 to 35 PSI35 PSI

AIRSPEED

0 to 25 knots25 to 100 knots100 to 130 knots130 knots

ROTOR

TRIPLE TACHOMETER

91%91 to 104.5%104.5%

ENGINE

97%97 to 100%100%

AMMETER

0 to 75 amps75 to 150 amps150 amps


INSTRUMENT MARKINGS

TRANSMISSION OilTEMPERATUREAND PRESSURE

I.INSTALLED INHELICOPTER SIN30597 AND SUB.

600 PSI600 to 900 PSI900 to' 100 PSI1100 PSI

PRESSURE

30 PSI30 to 40 PSI40 to 70 PSI70 PSI

.HYORAULICINDICATOR

TEMPERATURE ITI

HYDRAULIC

TEMPERATURE

HYDRAULICPRESSURE

600 PSI600 to 900 PSI900 to 1100 PSI1100PSI

212VFR·FM·'·5·6

Figure 1~5. Instrument markings (Sheet 6 of 6)

Rev. 1 1-21/1-22

•••

•••

FAA APPROVED

Section 2

TABLE OF CONTENTS

Subject

INTRODUCTION .FLIGHT PLANNING •••••••••••••••••••............••••••••.••••.•

TAKEOFF AND LANDING .WEIGHT AND BALANCE ..

PREFLIGHT CHECK .BEFORE EXTERIOR CHECK .EXTERIOR CHECK •.......•.••.••••.•••.•.•...•..........••

INTERIOR AND PRESTART CHECK .ENGINE START••........••.•.••••••.••••••••••••••••••••••••••••

ENGINE 1 START .••••••••••••••....................••••••••ENGINE 2 START ......••••••....................•••••••••••POST START .......•....•••••••••••.•••.•...••••.••••••••••ENGINE FAILS TO START ••••••••••••••.••.••...••••••••••DRY MOTORING RUN •••••••••••••................ ~ ••••••••

SYSTEMS CHECK .FORCE TRIM CHECK .PRELIMINARY HYDRAULIC CHECK ..•••..................ENGINE FUEL CONTROL CHECK.••.••••••.•......•••••••.GOVERNOR CHECK •••••...•.•...•.........................FUEL CROSSFEED VALVE CHECK .ELECTRICAL SYSTEMS CHECK ..........•••.••••••••••••.CABIN HEATER CHECK .•.......................•••••••••••HYDRAULIC SYSTEMS CHECK ••.••....•.....•............

BEFORE TAKEOFF ••••••••••••••••••••••••.•••.•..•..••.•..•••.•POWER ASSURANCE CHECK ..

TAKEOFF .INFLIGHT OPERATIONS .DESCENT AND LANDING •••••••.••.•.••••••.•••............•..•ENGINE SHUTDOWN •••••••••••••.•.•.••••••.•....•.•••...•••.••POSTFLIGHT CHECK ..•.....••••••••••.•••••••••••••••••.......

LIST OF FIGURES

Title

Exterior check diagram •.......•••••••.•.......•.•.•...•.....•..

BHT-212VFR-FM-1

PageParagraph Number

2-1 ........... 2·32·2 .••.••...•• 2-32-2-A ........ 2-32-2-B ........ 2-32-3 ......••••• 2·32·3·A ........ 2-32-3-B ........ 2-42-4 .......••.. 2-62-5 .•..•••••.• 2·72·5·A ........ 2-82-5-B ........ 2-92-5-C ........ 2-92-5-D ........ 2·102·5·E ........ 2-102-6 ••••••••••• 2-102-6-A ........ 2·102-6-B ........ 2-102-6-C ........ 2·112·6·D ........ 2-112-6-E ........ 2-112-6-F ••.•••••• 2-122-6-G ........ 2-122-6-H ........ 2-132-7 ......••••• 2·142·7·A ........ 2-142-8 ••••••••••. 2-142-9 •••........ 2-152-10 ......... 2-152-11 ......... 2·15

I2-12 ......... 2-16

Figure PageNumber Number

2-1 ........... 2-17

Rev. 2 2-1/2-2

•••

•••

FAA APPROVED

Section 2

2-1. INTRODUCTION

This section contains instructions andprocedures for operating helicopter fromplanning stage, through actual flightconditions, to securing helicopter afterlanding.

Normal and standard conditions areassumed in these procedures. Pertinentdata in other sections is referenced whenapplicable.

Instructions and procedures containedherein are written for purpose ofstandardization and are not applicable toall situations.

2-2. FLIGHT PLANNING

Planning of mission to be accomplishedwill provide pilot with data to be usedduring flight. Information to be used canbe compiled as follows:

Check type of mission to be performedand destination.

Select appropriate performance chartsto be used from Section 4.

2-2-A. TAKEOFF AND LANDING

Refer to Section 1 for takeoff and landingweight limits and to Section 4 for takeoffand landing dlllta.

2-2-B. WEIGHT AND BALANCE

Determine proper weight and balance ofhelicopter as follows:

BHT·212VFR·FM·1

Consult applicable weight and balanceinstructions provided in Section 5.

Determine weight of fuel, oil, load, etc.,compute takeoff and anticipated landingGW, and check helicopter CG locations.

Ensure weight and balance limitations InSection 1 are not exceeded.

2-3. PREFLIGHT CHECK

Pilot is responsible for determiningwhether helicopter is in condition for safeflight.

NOTE

Preflight check Is not intended tobe a detailed mechanicalinspection, but a guide to checkcondition of helicopter. Thischeck may be made ascomprehensive as conditionswarrant.

All areas checked shall include avisual check for evidence ofcorrosion, particularly whenhelicopter Is flown near or oversalt water or in areas of highindustrial emissions.

2-3-A. BEFORE EXTERIORCHECK

Flight planning - Completed.

Publications - Check.

Ensure helicopter has been serviced asrequired.

2-3


2-4 Rev. 5 17 OCT 2011 ECCN EAR99

2-3-B. EXTERIOR CHECK

WARNING

IF HELICOPTER HAS BEENEXPOSED TO SNOW OR ICINGCONDIT IONS, SNOW AND ICESHALL BE REMOVED PRIOR TOFLIGHT.

1. FUSELAGE — FRONT

Rotor blade — Condition and cleanliness.

Cabin area — Condition, all glass clean.

Pitot tube(s) — Cover(s) removed,unobstructed.

Static ports (left and right) —Unobstructed.

Remote hydraulic filter bypass indicator— Verify normal.

Cabin nose ventilators — Unobstructed.

Nose compartment — Condition anddoors secured.

Battery vent and drain tubes —Unobstructed.

Searchlight and landing light — Stowed.

Antenna — Condition, security.

Fuel sumps — Drain samples as follows:

ENGINE 1 BOOST PUMP andENGINE 2 BOOST PUMP switches —OFF.

ENGINE 1 FUEL and ENGINE 2 FUELswitches — OFF.

BATTERY BUS 1 switch — ON.

Fuel sump drain buttons (left andright) — Press.

Fuel filters — Drain before first flight ofday as follows:

ENGINE 1 BOOST PUMP andENGINE 2 BOOST PUMP switches —ON.

ENGINE 1 FUEL and ENGINE 2 FUELswitches — ON.

Fuel filters (left and right) — Drainsamples.

ENGINE 1 FUEL and ENGINE 2 FUELswitches — OFF.

ENGINE 1 BOOST PUMP andENGINE 2 BOOST PUMP switches —OFF.

BATTERY BUS 1 switch — OFF.

2. FUSELAGE — CABIN LEFT SIDE

Copilot and passenger doors —Condition and operation, glass clean.Security of emergency release handles.

Position lights — Condition.

Landing gear — Condition, groundhandling wheels removed.

Engine air intake — Cover removed,unobstructed.

3. FUSELAGE — AFT LEFT SIDE

Drain lines — Clean, unobstructed.

Engine compartment — Check.

Engine oil level — Verify presence of oilin sight gauge and proper oil level.

Engine governor spring — Condition.

Engine fire extinguisher — Bottlepressure gauge and temperature range.

Combining gearbox filter — Bypassindicator retracted.

Access doors and engine cowling —Secured.

Engine exhaust ejector tubes — Coversremoved, unobstructed.



4. FUSELAGE — AFT

Tailboom — Condition.

Tail rotor driveshaft covers — Secured.

Synchronized elevator — Condition,security.

Main rotor blade — Condition,cleanliness. Remove tie-down.

Tail rotor gearbox — Verify presence ofoil and proper level in sight gauge, fillercap, and chip detector plug security.

Tail rotor — Condition, free movement onflapping axis.

Tail rotor yoke — Evidence of static stopcontact damage (deformed static stopyield indicator).

Intermediate gearbox — Verify presenceof oil and proper level in sight gauge,filler cap, and chip detector plug security.

Tail skid — Condition, security.

Synchronized elevator — Condition,security.

Tailboom — Condition.

Baggage compartment — Check smokedetector; condition and security. Cargoand door secured.

5. FUSELAGE — AFT RIGHT SIDE

Engine fire extinguisher — Bottlepressure gauge and temperature range.

Combining gearbox oil — Verify presenceof oil and proper level in sight gauge.Close access door.

Engine compartment — Check.

Engine oil level — Verify presence of oiland proper level in sight gauge.

Access doors and engine cowling —Secured.

Fuel filler — Check fuel quantity, securecap.

6. FUSELAGE — CABIN RIGHT SIDE

Engine air intake — Cover removed,unobstructed.

Transmission oil — Verify presence of oiland proper level in sight gauge.

Pilot and passenger doors — Conditionand operation, glass clean. Security ofemergency release handles.

Position lights — Condition.

Landing gear — Condition, groundhandling wheels removed.

7. CABIN TOP

Main rotor and controls — Condition,fluid levels in all reservoirs.

Transmission oil filler cap — Secured.

Hydraulic oil reservoirs — Check sightglasses for proper fluid levels. Capssecured.

Antenna(s) — Condition and security.

Combining gearbox oil filler cap —Secured.

Anticollision light — Condition andsecurity.

CAUTION

IF ANY TEMP-PLATE IS MISSING ORHAS BLACK DOTS, MAINTENANCEPERSONNEL SHALL ASSIST INDETERMINING AIRWORTHINESS ASSTATED IN THE BHT-212-MM.

BHT-212VFR·FM·1

Main drlveshaft and coupling Condition, security, and grease leakage.Check Temp-Plates (four places eachcoupling) for evidence of elevatedtemperature indicated by dot changingcolor to black.

Engine air intakes - Unobstructed,particle separator doors closed.

Engine and transmission cowling Secured.

I Fresh air inlet screen - Unobstructed.

2-4. INTERIOR ANDPRESTART CHECK

Cabin Interior - Cleanliness, security ofequipment.

Portable fire extinguishers - Propercharge, secured.

Passenger seats - Secured, eachoccupied seat equipped with seat belt.

Crew and passenger doors - Secured.

Cargo load - Secured.

Protective breathing equipment (ifrequired) - Condition and properlyserviced.

Seat and pedals - Adjust.

Seat belt and shoulder harness Fasten and adjust.

Shoulder harness inertia reel and lock Check.

Flight controls - Freedom of movement,position for start.

Cyclic - Centered, friction as desired.

Collective - Full down.

Transmission chip detector indicators (ifinstalled) - Check.

2-6 Rev. 2

FAA APPROVED

Lower pedestal circuit breakers - In.

Collective control head switches - OFF.

COMPASS CONTROL slaving switch(es)- MAG (slave position).

Radio equipment - OFF.

Fuel INTCON switch - Normal.

ENGINE 1 BOOST PUMP and ENGINE 2BOOST PUMP switches - OFF.

Fuel XFEED switch - NORM.

ENGINE 1 FUEL and ENGINE 2 FUELswitches - OFF.

ENGINE NO.1 PART SEP and ENGINENO. 2 PART SEP switches - NORM (ifinstalled).

ENGINE NO. 1 GOV and ENGINE NO. 2GOV switches - AUTO.

HYDR SYS NO. 1 and HYDR SYS NO. 2switches - ON.

STEP switch (if installed) - As desired.

FORCE TRIM switch - ON, cover down.

Instruments - Static check.

STATIC SOURCE switch (if installed) PRI.

Altlmeter(s) - Set.

Clock - Set and running.

FIRE EXT switch - OFF.

FIRE PULL handles - In (forward).

AFT DOM E LT rheostat and switch OFF.

PITOT STATIC HEATERS switch - OFF.

•••

•••



WIPERS switch — OFF.

CARGO REL switch (if installed) — OFF.

VENT BLWR switch — OFF.

HEAT AFT OUTLET switch — OFF.

SYSTEM SELECTOR switch — OFF.

AIR COND TEMP CONT switch (ifinstalled) — As desired.

NAV AC switch (if installed) — NORM.

Overhead circuit breakers — In.

All light rheostats — OFF.

EXTERIOR LIGHT POSITION switch —OFF.

EXTERIOR LIGHT ANTI COLL switch —OFF.

INV 1, INV 2, and INV 3 switches — OFF.

NON ESS BUS switch — NORMAL.

GEN 1 and GEN 2 switches — OFF.

External power — Connect (as desired).Check DC voltmeters for 27 ±1 volts.Adjust external power source, if required.

BATTERY BUS 1 and BATTERY BUS 2switches — ON, check BATTERY cautionl ight i l lumina tes (S /N 30554 andsubsequent).

NOTE

Test all lights when night flights areplanned or anticipated. Accomplishlight tests with external powerconnected or during engine run-up.

MASTER CAUTION switch (overhead) —TEST, check all caution panel lightsextinguish except CAUTION PANELsegment and MASTER CAUTION light.(Both ENG OUT lights and RPM light willd im dur ing tes t (S /N 30597 andsubsequent.))

CAUTION

ROTOR BRAKE HANDLE SHALL BEIN DETENT POSITION (OFF) AT ALLTIMES WHEN ENGINES ARERUNNING.

ROTOR BRAKE lights (if installed) —Test. Pull brake lever and check that bothlights illuminate; return to off and checklights extinguish.

FIRE PRESS TO TEST switch — Pressand release. FIRE PULL 1 and FIREPULL 2 warning lights illuminate whenswitch is pressed and extinguish whenswitch is released.

BAGGAGE FIRE warning light TESTbutton — Press to test (verify lightflashes).

CARGO RELEASE ARMED light (ifinstalled) — TEST.

Caution panel light test switch — TESTand RESET.

INV 1 switch — ON, check No. 1 ACvoltmeter for 104 to 122 volts (S/N 30554and subsequent).

INV 2 switch — ON, check No. 2 ACvoltmeter for 104 to 122 volts (S/N 30554and subsequent).

FUEL QTY SEL switch — LEFT, thenRIGHT; check fue l quant i ty gaugeindicates lower fuel cell quantity of 270 to300 pounds (each).

2-5. ENGINE START

NOTE

If helicopter has been cold soaked inambient temperatures of -18°C (0°F)or less, both throttles will be difficultto move and follow-through couplingmay be increased.


2-8 Rev. 5 17 OCT 2011 ECCN EAR99

Throttles — Rotate engine 1 throttle fullopen, then back against id le stop.Actuate ENG 1 IDLE STOP REL, rollengine 1 throttle to full closed, thenadjust f r ic t ion as des ired . Repeatprocedure using engine 2 throttle andENG 2 IDLE STOP REL.

NOTE

When either IDLE STOP REL isactuated, appropriate idle stopplunger is automatically held openfor 5 seconds. Idle stop plunger willnot release if pressure is appliedtoward closed position of throttle.

Moderate frictions should be appliedto overcome follow-through couplingbetween throttles.

RPM INCR DECR switch — DECR for8 seconds.

NOTE

Either engine may be started first;however, following procedure isprovided for starting engine 1 first.

2-5-A. ENGINE 1 START

ENGINE 1 BOOST PUMP switch — ON,check ENG 1 FUEL BOOST caution lightextinguished.

ENGINE 1 FUEL switch — ON. (ENG 1FUEL VALVE caution light will illuminatemomentar i ly (S /N 30597 andsubsequent)).

Engine 1 FUEL PRESS — Check.

Rotor — Clear.

CAUTION

PROLONGED EXPOSURE TOAMBIENT TEMPERATURES OF 0°C(32°F) OR LESS MAY FREEZEMOISTURE IN ENGINE FUELCONTROL SYSTEM. MONITOR ENG

RPM (N2) DURING COLD WEATHERSTARTING FOR OVERSPEED. IF ANOVERSPEED APPEARS IMMINENT,ABORT START AND CLOSETHROTTLE TO OFF POSITION.

EITHER WAIT 3 MINUTES ANDRESTART THE ENGINE OR STARTTHE OTHER ENGINE. THE HEATGENERATED WILL MELT THEMOISTURE, ALLOWING THE FUELCONTROL TO FUNCTIONNORMALLY.

START switch — ENG 1 position.Observe starter limitations.

Engine 1 ENGINE OIL pressure —Indicating.

Engine 1 throttle — Open to idle at 12%GAS PROD RPM (N1) minimum.

Engine 1 ITT — Monitor to avoid a hotstart . Maximum ITT during star t is1090°C, not to exceed 2 seconds above810°C for PT6T-3 or 2 seconds above960°C for PT6T-3B. If ITT continues torise, abort start by activating ENG 1 IDLESTOP release and rolling throttle fullyclosed. Starter should remain engageduntil ITT decreases. Do not attemptrestart until corrective maintenance hasbeen accomplished.

NOTE

If engine fails to start, refer toENGINE FAILS TO STARTprocedures in this section.

START switch — Off at 55% GAS PRODRPM (N1).

GAS PROD RPM (N1) — Check 61 ±1%when throttle is on idle stop.

If battery start:

GAS PROD RPM (N1) — Check 71%minimum.

GEN 1 switch — ON.

•••

••

FAA APPROVED

AMPS 1 - Check at or below 150amps.

NOTE

During extremely cold ambienttemperatures, idle rpm will behigh and ENGINE OIL, XMSN OIL,and GEAR BOX OIL pressuresmay exceed maximum limits forup to 2 minutes after starting.

Do not increase ROTOR above80% RPM until XMSN OILtemperature is above 15°C.

ENGINE OIL, XMSN OIL, AND GEAR BOXOIL pressures - Check.

ENG 1 PART SEP OFF caution light Extinguished.

Engine 1 throttle - Increase to 85% ENGRPM (N2). Friction as desired.

2-5-8. ENGINE 2 START

ENGINE 2 BOOST PUMP switch - ON,check ENG 2 FUEL BOOST caution lightextinguished (FUEL XFEED caution lightwill illuminate momentarily SN 30597and subsequent.)

ENGINE 2 FUEL switch - ON. (ENG 2FUEL VALVE caution light will Illuminatemomentarily SN 30597 and subsequent.)

Engine 2 FUEL PRESS - Check.

START switch - ENG 2 position.Observe starter limitations.

Engine 2 ENGINE OIL pressure Indicating.

Engine 2 throttle - Open to idle at 12%GAS PROD RPM (NI) minimum.

Engine 2 ITT - Monitor. Observe ITTlimitations.

START switch - Off at 55% GAS PRODRPM (NI).

BHT-212VFR-FM-1

GAS PROD RPM (NI) - Check 61 ± 1%when engine 2 throttle is on idle stop.

1 1I.:.~.~~~~.~..i

ENSURE SECOND ENGINEENGAGES AS THROTTLE ISINCREASED. A NON-ENGAGEDENGINE IS INDICATED BY 10 TO15% HIGHER ENG RPM (N2) THANENGAGED ENGINE AND NEARZERO TORQUE. IF A NONENGAGEMENT OCCURS, CLOSETHROTTLE OF NON-ENGAGEDENGINE. WHEN NON-ENGAGEDENGINE HAS STOPPED, SHUTDOWN ENGAGED ENGINE.

IF SUDDEN (HARD)ENGAGEMENT OCCURS, SHUTDOWN BOTH ENGINES.MAINTENANCE ACTION ISREQUIRED.

Engine 2 throttle - Increase slowly to85% ENG RPM (N2). Monitor tachometerand torquemeter to verify engagement ofsecond engine.

Engine 2 ENGINE OIL pressure - Check.

ENG 2 PART SEP OFF light Extinguished.

2-5-C. POST START

External power - Disconnect if used,GEN 1 switch - ON.

GEN 2 switch - ON (BATTERY BUS 1will switch OFF automatically SN 30554and subsequent).

1'··..............1i.:~~~~.•i

IF OPERATING ON BATTERY BUS1, POSITION INV 3 SWITCH TO ONDC BUS 1 (SN 30554 andsubsequent).

2-9


2-10 Rev. 5 17 OCT 2011 ECCN EAR99

ONLY ONE BATTERY SWITCHSHALL BE ON DURING FLIGHT(S/N 30554 AND SUBSEQUENT).

Caution lights — Check all extinguished.

ENGINE OIL, XMSN OIL, and GEAR BOXOIL temperatures and pressures —Within limits.

AMPS 1 and AMPS 2 — Within limits.

NOTE

AMPS 2 will indicate a higher loadthan AMPS 1 until battery is fullycharged.

Radios — ON, as required.

ELT (if installed) — Check for inadvertenttransmission.

2-5-D. ENGINE FAILS TO START

When engine fails to light off within15 seconds after thrott le has beenopened to idle, fol lowing action isrecommended:

IDLE STOP REL switch — Actuate.

Throttle — Fully closed.

START switch — OFF.

ENGINE (1 or 2) BOOST PUMP switch— OFF.

ENGINE (1 or 2) FUEL switch — OFF.

After GAS PROD RPM (N1) has decreasedto zero, allow 30 seconds for fuel to drainfrom engine. Conduct a dry motoring run(paragraph 2-5-E) before attemptinganother start.

2-5-E. DRY MOTORING RUN

The following procedure is used to clear anengine whenever it is deemed necessary toremove internally trapped fuel and vapor.

Throttle — Fully closed.

ENGINE (1 or 2) BOOST PUMP switch —ON.

ENGINE (1 or 2) FUEL switch — ON.

ENG IGN SYS circuit breaker — Pull out.

START switch — Engage for 15 seconds,then disengage.


ENGINE (1 or 2) BOOST PUMP switch —OFF.

ENG IGN SYS circuit breaker — In.

Allow required cooling period for starterbefore proceeding. Follow normal startsequence as described on precedingpages. Refer to Section 1, paragraph1-12-C.

2-6. SYSTEMS CHECK

2-6-A. FORCE TRIM CHECK

Flight controls — Friction off; collectivelock removed.

Cyclic and pedals — Move slightly eachdirection to check force gradients.

Cyclic FORCE TRIM release button —Press; check trim releases with buttonpressed, reengages with button released.

FORCE TRIM switch — OFF; check trimdisengages.

FORCE TRIM switch — ON.

2-6-B. PRELIMINARY HYDRAULICCHECK

Throttles — Set to idle.

NOTE

Uncommanded control movement ormotoring with either hydraulicsystem off may indicate hydraulicsystem malfunction.

HYDR SYS NO. 1 switch — OFF, then ON.


17 OCT 2011 Rev. 5 2-11ECCN EAR99

HYDR SYS NO. 2 switch — OFF, then ON.

2-6-C. ENGINE FUEL CONTROL CHECK

Throttles — Idle.

NOTE

Do not allow GAS PROD (N1) RPM todecrease below 50%.

At approximately 8000 feet HP, GASPROD RPM (N1) may not changesignificantly when manual fuelcontrol is selected.

GOV switch (ENGINE NO. 1 or 2) —MANUAL, observe change in GAS PRODRPM (N1). Open respective thrott lecarefully to ensure GAS PROD RPM (N1)responds upward, then return throttle toidle. Return GOV switch to AUTO. Checkfor return to original GAS PROD RPM(N1). Check other governor in samemanner.

2-6-D. GOVERNOR CHECK

No. 1 throttle — Full open. Check ENGRPM (N2) stabilizes at 95 ±1%.

No. 2 throttle — Full open. Check ENGRPM (N2) increases 2% and both enginesstabilize at 97 ±1%.

RPM INCR DECR switch — INCR to 100%(N2).

2-6-E. FUEL CROSSFEED VALVECHECK

2-6-E-1. S/N PRIOR TO 30554

FUEL PUMP CROSSFEED switch—NORMAL. Position ENGINE 1 BOOSTPUMP switch to OFF. Note pressure dropon No. 1 FUEL PRESS gauge, followed bya return to normal indication, showingcrossfeed valve has opened and checkvalve is functioning properly.

Position ENGINE 1 BOOST PUMP switchto ON and position ENGINE 2 BOOST

PUMP switch to OFF. Note pressure dropon No. 2 FUEL PRESS gauge, followed bya return to normal indication, showingcrossfeed valve has opened and checkvalve is functioning properly.

NOTE

If in either of the above checks; fuelpressure is 4 to 6 PSI below normal(10 ±4 PSI), appropriate check valveis not functioning properly.

ENGINE 2 BOOST PUMP switch — ON.

FUEL PUMP CROSSFEED switch —OVERRIDE CLOSE. Posit ion eitherBOOST PUMP switch to OFF. Note fuelpressure drops to zero. Position BOOSTPUMP switch to ON and FUEL PUMPCROSSFEED switch to NORMAL.

2-6-E-2. S/N 30554 AND SUBSEQUENT

FUEL XFEED test switch — TEST BUS 1and hold.

NOTE

If, after turning either boost pump off,fuel pressure remains 4 to 6 PSIbe low normal (10 ±4 PS I ) ,appropriate check valve is notfunctioning properly.

ENGINE 1 BOOST PUMP switch — OFF.Check No. 1 FUEL PRESS decreases,then returns to normal. (This indicatesthat crossfeed valve has opened by busNo . 1 power and check va lve isfunctioning properly.) ENGINE 1 BOOSTPUMP switch — ON.

FUEL XFEED test switch — TEST BUS 2and hold.

ENGINE 2 BOOST PUMP switch — OFF.Check No. 2 FUEL PRESS decreases,then returns to normal. ENGINE 2 BOOSTPUMP switch — ON.

FUEL XFEED test switch — NORM.


2-12 Rev. 5 17 OCT 2011 ECCN EAR99

FUEL XFEED switch — OVRD CLOSE.

ENGINE 1 (or ENGINE 2) BOOST PUMPswitch — OFF. Check fuel pressure dropsto zero on selected system. ENGINE 1 (orENGINE 2) BOOST PUMP switch — ON.

FUEL XFEED switch — NORM.

2-6-F. ELECTRICAL SYSTEMS CHECK

DC voltmeters — Check 27 ±1 VDC.

AC voltmeters — Check 104 to 122 VAC.

AC system — Check as follows:

INV 3 switch (if installed) — ON DCBUS 2; check INVERTER 3 cautionlight extinguishes.

INV 2 switch — OFF, INVERTER 2caution light illuminates. Check No. 2AC voltmeter for indicationINVERTER 3 (if installed) hasassumed the load.

INV 2 switch — ON.

INV 3 switch (if installed) — OFF;confirm INVERTER 2 caution lightextinguishes and INVERTER 3caution light illuminates.

INV 3 switch (if installed) — ON DCBUS 1, check INVERTER 3 cautionlight extinguishes.

INV 1 switch — OFF, INVERTER 1caution light illuminates. Check No. 1AC voltmeter for indicationINVERTER 3 (if installed) hasassumed the load.

INV 1 switch — ON.

INV 3 switch (if installed) — OFF,confirm INVERTER 1 caution lightextinguishes and INVERTER 3caution light illuminates.

INV 3 switch (if installed) — ON DCBUS 2; check INVERTER 3 cautionlight extinguishes.

2-6-G. CABIN HEATER CHECK

GAS PROD — Check 75% RPM (N1)minimum (both engines).

Thermostat knob — Full COLD.

CAUTION

HEATER SWITCH SHALL BETURNED OFF WHEN HEATEDAIRFLOW DOES NOT SHUT OFFAFTER THERMOSTAT IS TURNEDTO FULL COLD, HEATER AIR LINELIGHT ILLUMINATES, OR CABINHTR CIRCUIT BREAKER TRIPS.

CAUTION

DO NOT OPERATE HEATER ABOVE21°C OAT.

HEATER switch — ON.

VENT BLOWER switch — ON.

Thermostat setting — Increase andobserve heated airflow.

DEFROST lever — ON. Check airflow isd iver ted f rom pedesta l out le ts towindshield nozzles. Return lever to OFF.

AFT OUTLET switch — ON. Check airflowdistributed equally between pedestaloutlets and aft outlets. Return switch toOFF.

NOTE

Heater operat ion a f fectsperformance. Refer to Hover Ceilingand Rate of Climb charts for HEATERON in Section 4.

HEATER switch — As desired.

VENT BLOWER switch — As desired.


17 OCT 2011 Rev. 5 2-13ECCN EAR99

2-6-H. HYDRAULIC SYSTEMS CHECK

NOTE

This check is to determine properoperation of hydraulic actuators foreach f l ight cont ro l system. I fabnormal forces, unequal forces,control binding, or motoring isencountered, it may be an indicationof a malfunction of a flight controlactuator.

FORCE TRIM switch — OFF.

Collective — Down, friction removed.

ROTOR RPM (NR) — Set to 100%.

Cyclic — Centered, friction removed.

Hydraulic system — Check as follows:

HYDR SYS NO. 1 switch — OFF. CheckMASTER CAUTION light illuminates andHYDRAULIC caution light illuminates.Hydraul ic system No. 1 pressuredecreases.

Cyclic — Check normal operation bymoving cyclic in an ‘X’ pattern, rightforward to left aft, then left forward toright aft (approximately 1 inch). Centercyclic.

Collective — Check normal operation byincreasing col lect ive sl ightly (1 to2 inches). Return to down position.

NOTE

Boost for tail rotor controls isfurnished by hydraulic system No. 1only. When hydraulic system No. 1 isbeing checked, tail rotor controls willbe unboosted.

Pedals — Displace slightly left andright. Note an increase in forcerequired to move pedals.

WARNING

DO NOT TURN BOTH HYDRAULICSYSTEMS OFF AT SAME TIME DUETO EXCESSIVE FORCE REQUIREDTO MOVE FLIGHT CONTROLS.

HYDR SYS NO. 1 switch — ON. CheckMASTER CAUTION light extinguishesand hydraulic system No. 1 pressurereturns to normal. HYDRAULIC cautionlight extinguishes.

HYDR SYS NO. 2 switch — OFF. CheckMASTER CAUTION light illuminates andhydrau l ic system No. 2 pressuredecreases. HYDRAULIC caution lightilluminates.

Cyclic — Check normal operation ofcyclic controls by moving cyclic in an ‘X’pattern, right forward to left aft, then leftforward to right aft (approximately1 inch). Center cyclic.

Collective — Check normal operation byincreasing col lect ive sl ightly (1 to2 inches). Return to down position.

Pedals — Displace slightly left and right.Note no increase in force required tomove pedals.

HYDR SYS NO. 2 switch — ON. CheckMASTER CAUTION light extinguishesand hydraulic system No. 2 pressurereturns to normal. HYDRAULIC cautionlight extinguishes.

Cyclic and collective friction — Asdesired.


2-14 Rev. 5 17 OCT 2011 ECCN EAR99


WARNING

BOTH HYDRAULIC SYSTEMS SHALLBE OPERATIONAL PRIOR TOTAKEOFF.

System 1 will normally operate 10 to 20°Ccooler than system 2.

2-7. BEFORE TAKEOFF

Engine, transmission, gearbox,hydraulic, and electrical instruments —Check readings within operational range.

Flight instruments — Check operationand set.

Position lights — As required.

Magnetic compass — Fluid level andheading.

Anticollision lights — As required.

Pitot heater — As required.

Radio(s) — Check operation and set.

Cyclic — Friction as desired.

NOTE

Moderate friction shall be applied toeach thro t t le to overcomefollow-through coupling betweentwist grips.

Throttles — Full open, adjust friction.

ENG RPM (N2 ) — 100% (bothengines).

FORCE TRIM switch — As desired.

COCKPIT VOICE RECORDER TESTswitch (if installed) — Press and holdfor 3 seconds. Verify meter indicatesGOOD.

Passenger step switch (if installed)— As desired.

Passenger seat belts — Fastened.

All doors — Secured.

Caut ion and warn ing l ights —Extinguished.

2-7-A. POWER ASSURANCE CHECK

Perform power assurance checkdaily. Refer to Section 4.

2-8. TAKEOFF

ENG RPM (N2) — 100%.

NOTE

No more than 15% torque abovehover power sha l l be usedaccelerating to Takeoff ClimboutSpeed.

Collective — Initiate takeoff from ahover height of 4 feet.

NOTE

Takeof f must be executed inaccordance with height-velocitylimitations for type of operationbeing conducted. Refer to Section 1.

Refer to Section 4 for additionalclimb performance data.


17 OCT 2011 Rev. 5 2-15ECCN EAR99

2-9. IN-FLIGHT OPERATIONS

ENG RPM (N2) — Adjust INCR DECRswitch to select desired RPM between 97and 100% (100% is normal RPM.)

Airspeed — Within limits for GW andflight altitude.

Engine, gearbox, and transmissioninstruments — Within limits.

NOTE

Refer to applicable operating rulesfor high altitude operations.

2-10. DESCENT AND LANDING

CAUTION

CONDITIONS INCLUDING, BUT NOTLIMITED TO, WIND DIRECTION ANDVELOCITY, CENTER OF GRAVITY,AND THE CONDIT ION OF THESLOPE (LOOSE ROCK, SOFT MUD,SNOW, WET GRASS, ETC.) MAYLIMIT THE MAXIMUM SLOPE THEHELICOPTER CAN BE SAFELYLANDED ON.

Flight controls — Adjust friction asdesired.

Throttles — Full open.

ENG RPM (N2) — 100%.

FORCE TRIM switch — As desired.

Passenger STEP switch — As desired.

Flight path — Avoid critical areas of HVdiagram from which a safe landing maynot be made in case of single enginefailure. For landing distance informationin event o f engine fa i lure dur ingapproach, refer to Section 4.

2-11. ENGINE SHUTDOWN

Collective — Down.

Cyclic control and pedals — Centeredand frictioned.


Throttles — Idle.

ITT — Stabilize for 1 minute at idle priorto shutdown.

Engine instruments — Within limits.

ELT (if installed) — Check for inadvertenttransmission.

Radios — OFF.

IDLE STOP REL switch — ENG 1.

Engine 1 throttle — Closed. Check ITTand GAS PROD RPM (N1) decreasing.

BATTERY BUS 1 switch — ON (S/N 30554and subsequent).

IDLE STOP REL switch — ENG 2.

Engine 2 throttle — Closed. Check ITTand GAS PROD RPM (N1) decreasing.

GEN 1 and 2 switches — OFF.

All invertors — OFF.

ENGINE 1 FUEL switch — OFF.

ENGINE 1 BOOST PUMP switch — OFF.

ENGINE 2 FUEL switch — OFF.

ENGINE 2 BOOST PUMP switch — OFF.

CAUTION

AVOID RAPID ENGAGEMENT OFROTOR BRAKE IF HELICOPTER ISON ICE OR OTHER SLIPPERY ORLOOSE SURFACE TO PREVENTROTATION OF HELICOPTER.

Rotor brake — Apply at or below 40%ROTOR RPM (NR); return to stowedposition after main rotor stops.

Pilot — Remain at flight controls untilrotor has come to a complete stop.


2-16 Rev. 5 17 OCT 2011 ECCN EAR99

Lighting and miscellaneous switches —OFF.

BATTERY switch(es) — OFF.

2-12. POSTFLIGHT CHECK

Main rotor and tail rotor blades — Tiedown when any of following conditionsexist:

• Thunderstorms exist in local area orare forecast.

• Winds in excess of 20 knots or agust spread of 15 knots exist or isforecast.

• Helicopter is parked within 150 feetof hovering or taxiing aircraft thatare in excess of basic helicopter GW.

• Helicopter is to be left unattended.

Protective covers (engine exhaust andpitot tube) — Install.

•FAA APPROVED BHT-212VFR-FM-1

••

••• Figure 2-1. Exterior check diagram

212VFR-FM-2-1

2-1712-18



Section 3EMERGENCY AND MALFUNCTION PROCEDURES

3TABLE OF CONTENTS


Introduction ............................................................................................ 3-1 ........... 3-3Definitions .............................................................................................. 3-2 ........... 3-3Engine ..................................................................................................... 3-3 ........... 3-3

Single Engine Failure ........................................................................ 3-3-A ....... 3-3Engine Restart In Flight..................................................................... 3-3-B ....... 3-4Dual Engine Failure ........................................................................... 3-3-C ....... 3-5Engine Underspeed ........................................................................... 3-3-D ....... 3-6Engine Overspeed — Fuel Control/Governor Failure..................... 3-3-E ....... 3-7Engine Overspeed — Driveshaft Failure ......................................... 3-3-F........ 3-8Engine Compressor Stall .................................................................. 3-3-G....... 3-9Engine Hot Start/Shutdown .............................................................. 3-3-H ....... 3-9Engine Oil Hot .................................................................................... 3-3-I......... 3-9

Fire .......................................................................................................... 3-4 ........... 3-9Engine Fire ......................................................................................... 3-4-A ....... 3-9

During Start .................................................................................... 3-4-A-1 .... 3-9Engine Fire During Takeoff or Approach..................................... 3-4-A-2 .... 3-10Engine Fire In Flight ...................................................................... 3-4-A-3 .... 3-10

Cabin Smoke or Fumes ..................................................................... 3-4-B ....... 3-11Baggage Compartment Fire.............................................................. 3-4-C ....... 3-11

Tail Rotor ................................................................................................ 3-5 ........... 3-11Complete Loss of Tail Rotor Thrust................................................. 3-5-A ....... 3-11Loss of Tail Rotor Thrust at Hover................................................... 3-5-B ....... 3-11Loss of Tail Rotor Thrust in Climb ................................................... 3-5-C ....... 3-11Loss of Tail Rotor Thrust in Level Flight or Descent ..................... 3-5-D ....... 3-12Loss of Tail Rotor Components ....................................................... 3-5-E ....... 3-12Tail Rotor Fixed Pitch Failures ......................................................... 3-5-F........ 3-12Fixed Pitch Failure at a Hover........................................................... 3-5-G....... 3-13Fixed Pitch Failure In Flight .............................................................. 3-5-H ....... 3-13Loss of Pitch Change Control Linkage............................................ 3-5-J........ 3-14

Hydraulic System................................................................................... 3-6 ........... 3-14Electrical System ................................................................................... 3-7 ........... 3-14

DC Failure to Produce Power ........................................................... 3-7-A ....... 3-14AC — Failure to Produce Power....................................................... 3-7-B ....... 3-14

Fuel System............................................................................................ 3-8 ........... 3-14Fuel Boost Pump Failure................................................................... 3-8-A ....... 3-14Fuel Filter Partially Blocked.............................................................. 3-8-B ....... 3-15


3-2 Rev. 5 17 OCT 2011 ECCN EAR99

TABLE OF CONTENTS (CONT)


Fuel Quantity Indication Malfunctions............................................. 3-8-C....... 3-15Automatic Flight Controls System....................................................... 3-9........... 3-15Communication System........................................................................ 3-10......... 3-15

Navigation Radio Failure................................................................... 3-10-A..... 3-15Intercom Failure................................................................................. 3-10-B..... 3-15

Cabin Heater........................................................................................... 3-11......... 3-15Landing Gear.......................................................................................... 3-12......... 3-16Static Port Obstruction ......................................................................... 3-13......... 3-16

LIST OF TABLES

Table PageSubject Number Number

Warning Lights....................................................................................... 3-1........... 3-17Caution Lights........................................................................................ 3-2........... 3-19


Section 3EMERGENCY/MALFUNCTION PROCEDURES

/secttitle>3-1. INTRODUCTION

Following procedures contain indications ofequipment or system failure or malfunction,use of emergency features of primary andbackup systems, and appropriate warnings,cautions, and explanatory notes. Table 3-1lists fault conditions and corrective actionsrequired for illumination of red warning lights.Table 3-2 addresses malfunction proceduresassociated with yellow caution lights.

Corrective action procedures listed hereinassume pilot gives first priority to helicoptercontrol and a safe flight path.

Helicopter should not be operated followingany precautionary landing until cause ofmalfunction has been determined andcorrective maintenance action taken.

3-2. DEFINITIONS

Following terms indicate degree of urgency inlanding helicopter.

LAND AS SOON AS POSSIBLE — Landwithout delay at nearest suitable area (i.e.,open field) at which a safe approach andlanding is reasonably assured.

LAND AS SOON AS PRACTICAL — Duration offlight and landing site are at discretion of pilot.Extended flight beyond nearest approvedlanding area is not recommended.

Fol lowing terms are used to describeoperating condition of a system, subsystem,assembly, or component:

AFFECTED — Fails to operate in intended orusual manner.

NORMAL — Operates in intended or usualmanner.

3-3. ENGINE

3-3-A. SINGLE ENGINE FAILURE

ENG RPM (N2) of operating engine is allowedto droop to 97% during transition from twinengine operation to single engine operation.When best rate of climb airspeed (58 KIAS) isattained, N2 RPM should be increased to 100%if possible.

Flight can be continued on remaining engineuntil a desirable landing site is available. Thereare certain combinations of GW, altitude, andambient air temperatures that will result in OEItorque limit being exceeded. A run-on landingat 20 to 30 knots is recommended.

Loss of an engine while hovering at high GWand extremely cold conditions is likely toresult in exceeding OEI torque limit. If anovertorque is observed or suspected, an entrysha l l be made in log book . Refer toperformance charts in Section 4.

NOTE

Refer to ENGINE RESTART if anengine restart is to be attempted.

INDICATIONS:

ENG 1 OUT or ENG 2 OUT warning lightilluminated.

02 DEC 2002 Rev. 4 3-3


GAS PROD RPM (NI) below 61 ± 1% anddecreasing.

ENG RPM (N2) below 85% and decreasing.

ITT below 400 °C and decreasing.

ENG 1 or ENG 2 OIL PRESSURE, DCGENERATOR, and PART SEP OFF cautionlights illuminated.

PROCEDURES:

WARNING

DO NOT ALLOW ROTOR RPM (NR)TO DECAY BELOW MINIMUM LIMITS.

CAUTION

D U R I N G C O L D W E A T H E ROPERATIONS, MONITOR TORQUEOF OPERATING ENGINE WHENONE ENGINE FAILS OR IS SHUTDOWN IN FLIGHT.

Shut down affected engine as follows:

Collective — Reduce as required to maintainROTOR RPM (NR) within limits and powerwithin OEI limits.

NOTE

Airspeed — 55 to 65 KIAS forMinimum Power for level flight.

RPM INCR DECR switch — INCR, setremaining ENG RPM (N2) at 100% if possible.

Throttle — Closed.

Fuel Crossfeed switch — Override Close.

Fuel Interconnect switch — OPEN.

ENGINE (1 or 2) BOOST PUMP switch — OFF.

Verify FUEL BOOST caution light and FUEL switch to be turned off are all for affected engine.


GEN (1 or 2) switch — OFF.

MASTER CAUTION light — Reset.

Land as soon as practical.

If no. 2 engine failed:

INV 3 to DC BUS 1 (if installed).





3-3-B. ENGINE RESTART IN FLIGHT

Conditions which would warrant an attempt torestar t an engine would probably be af lameout, caused by a malfunction ofautomatic mode of fuel control unit. Decisionto attempt an engine restart during flight ispilot responsibility. If an engine restart is to bemade, proceed as follows:

CAUTION

MONITOR ITT WHEN RESTARTINGE N G I N E I N M A N U A L F U E LCONTROL MODE.

ENGINE RESTART:

ENGINE RESTART NO. 1:

Engine 1 throttle — Closed.

ENGINE 1 BOOST PUMP switch — ON.

Fuel Crossfeed switch — Normal.

ENGINE 1 FUEL switch — ON.

ENGINE NO. 1 GOV switch — MANUAL.



INV 1 and INV 2 switches — ON.

INV 3 switch (if equipped) — ON DC BUS 1.

START switch — ENG 1.

After 12% GAS PROD RPM (NI) isattained and oil pressure is indicating,slowly open throttle until a rise is seenin ITT which indicates engine is self-sustaining. Do not open throt t lefarther until GAS PROD RPM (NI) and

3-4 Rev. 4 02 DEC 2002

•••

•••

FAA APPROVED

ITT are stabilized. Continue to openthrottle slowly to complete start.Center START switch after 55"10 GASPROD RPM (N I) is attained. Adjustengine to desired power level. Caremust be taken to make smalladjustments with throttle ascompressor stall may result.

GEN 1 switch - ON.

BATTERY BUS 1 switch - OFF.

BATTERY BUS 2 switch - ON.

ENGINE RESTART (NO.2):

Engine 2 throttle - Closed.

ENGINE 2 BOOST PUMP switch - ON.

Fuel Crossfeed switch - Normal.

ENGINE 2 FUEL switch - ON.

ENGINE NO.2 GOV switchMANUAL.

BATTERY BUS 1 switch - OFF.

BATTERY BUS 2 switch - ON.

INV 1 and 2 switches - ON.

INV 3 switch (if equipped) - ON DCBUS 2.

START switch - ENG 2.

After 12"10 GAS PROD RPM (N I ) isattained and 011 pressure Is Indicating,slowly open throttle until a rise isseen In ITT which indicates engine isself sustaining. Do not open throttlefarther until GAS PROD RPM (NI) andITT are stabilized. Continue to openthrottle slowly to complete start.Center START switch after 55"10 GASPROD RPM (NI) is attained. Adjustengine to desired power level. Caremust be taken to make smalladjustments with throttle ascompressor stall may result.

GEN 2 switch - ON.

BHT-212VFR-FM-1

3-3-C. DUAL ENGINE FAILURE

INDICATIONS:

ENG 1 OUT and ENG 2 OUT warninglights Illuminated.

RPM caution light illuminated.

ROTOR RPM audio on.

GAS PROD RPM (N I) below 61 ± 1"10 RPMand decreasing (both engines).

ENG RPM (N 2 ) below 85"10 anddecreasing (both engines).

ITT below 400°C and decreasing (bothengines).

ENG 1 and ENG 2 OIL PRESSURE, DCGENERATOR, and PART SEP OFFcaution lights Illuminated.

PROCEDURES:

IWARNING ~

DO NOT ALLOW ROTOR RPM TODECAY BELOW MINIMUM LIMITS.

Collective - Reduce, establish Iautorotative glide. Minimum rate ofdescent (65 KIAS) or maximum glide (90KIAS).

Autorotatlve landing - Accomplish.

If time permits before landing and arestart will not be attempted, proceedas follows:

Throttles - Closed.

ENGINE 1 and ENGINE 2 FUEL switches-OFF.

ENGINE 1 and ENGINE 2 BOOST PUMPswitches - OFF.

After landing:

Engine shutdown - Complete.

Rev. 2 3-5

BHT-212VFR-FM-1

Helicopter - Exit.

3-3-0. ENGINE UNDERSPEED

NOTE

Normal deviations of ROTOR RPM(N R ) from the governed settingmay occur when large collectivechanges are made but should notbe confused with fuel controlfailure, unless a large steady-stateTORQUE split occurs.

If there is a low power demand (less thansingle engine power available) at time oflow side failure, ROTOR RPM (N R) and ENGRPM (N2) of affected engine will decreaseand stabilize, at or slightly below governedvalue. TORQUE, ITT, and GAS PROD RPM(N1) of affected engine will also decrease.As ROTOR RPM (N R) decreases, normalengine will increase TORQUE output toassume load. If power demand is nearzero, there might not be a significantTORQUE split.

If there is a high power demand (greaterthan single engine power available) at timeof low side failure, ROTOR RPM (NR) willdecrease along with ENG RPM (N 2 ),

TORQUE, ITI, and GAS PROD RPM (N1) ofaffected engine. As ROTOR RPM (N R)

decreases, normal engine will increase tomaximum power to assume load, causingsignificant increases in TORQUE, ITI, andGAS PROD RPM (N1) while ENG RPM (N2)

will remain below governed value.

INDICATIONS:

Low ENG RPM (N2) and ROTOR RPM (N R)

(possibly with RPM caution light andaudio if power demand is in excess ofsingle engine power available).

TORQUE split (proportional to powerdemand).

3·6 Rev. 2

FAA APPROVED

Low GAS PROD RPM (N 1), ITT, andTORQUE on affected engine.

PROCEDURES:

]WARNING ~

ROTOR RPM CAN DECAYEXCESSIVELY IF CORRECTIVEACTION IS NOT IMMEDIATELYINITIATED.

Collective - Adjust as necessary tomaintain ROTOR RPM (NR).

Airspeed - 55 to 65 KIAS for MinimumPower for level flight.

Affected engine - Identify.

Throttle friction - Tighten on normalengine, reduce on affected engine.

Throttle (affected engine) - Reduce toidle.

GOV switch (affected engine) MANUAL.

WHEN OPERATING IN MANUALFUEL CONTROL MODE, MAKESLOW, SMOOTH THROTTLEMOVEMENTS TO AVOIDCOMPRESSOR STALL,OVERTEMPERATURE, OVERSPEED, AND POSSIBLEDRIVETRAIN DAMAGE.

COORDINATE THROTTLE ANDCOLLECTIVE CHANGES TOAVOID OVERLOADING NORMALENGINE.

Throttle (affected engine) - Increaseslowly. Adjust throttle and collective asrequired to maintain TORQUE of affected

•••I

•••

•••

••

I

FAA APPROVED

engine slightly below TORQUE of normalengine.

MASTER CAUTION light - Reset.


3-3-E. ENGINE OVERSPEED FUEL CONTROUGOVERNORFAILURE

NOTE

Normal deviations of ROTOR RPM(N R) from the governed settingmay occur when large collectivechanges are made but should notbe confused with fuel controlfailure, unless a large steady-stateTORQUE split occurs.

If there is a low power demand (less thansingle engine power available) at time ofhigh side failure, ROTOR RPM (N R) andENG RPM (N 2 ) of affected engine willincrease considerably above governedvalue. TORQUE, ITT, and GAS PROD RPM(NI) of affected engine will also Increase.As ENG RPM (N2) and ROTOR RPM (N R)

increase above governed value, normalengine will reduce power to keep itselffrom overspeeding and will indicatesignificantly lower TORQUE, ITT, and GASPROD RPM (NI) than affected engine.

If there is a high power demand (greaterthan single engine power available) at timeof high side failure, ROTOR RPM (NR) andENG RPM (N 2 ) (of affected engine willsurge initially along with TORQUE, ITT,and GAS PROD RPM (NI). As ENG RPM(N 2 ) and ROTOR RPM (N R ) increase,normal engine will reduce power to keepitself from overspeeding. Affected enginethen tries to assume all of load, which isbeyond its capability due to high powerdemand. ENG RPM (N2) of affected engineand ROTOR RPM (NR) will then decreaseand rejoin ENG RPM (N2) of normal engine,stabilizing at or slightly above governed

BHT-212VFR-FM-1

value as normal engine adjusts poweroutput to share load.

INDICATIONS:

High ENG RPM (N2) and ROTOR RPM(NR) ,possibly with RPM caution light.

Definite TORQUE split (proportional topower demand).

High GAS PROD RPM (NIl. ITT, andTORQUE on affected engine.

Return of ENG RPM (N 2) and ROTORRPM (N R) to governed value (if powerdemand is very high).

PROCEDURES:

ROTOR RPM CAN OVERS PEEDEXCESSIVELY IF CORRECTIVEACTION IS NOT IMMEDIATELYINITIATED.

Collective - Adjust as necessary tomaintain ROTOR RPM (N R).

Affected engine - Identify.

Throttle (affected engine) - Reduce tomaintain TORQUE at or slightly belowTORQUE of normal engine.

Throttle friction - Tighten on normalengine, reduce on affected engine.

Throttle (affected engine) - Reduce toidle.

GOV switch (affected engine) MANUAL.

WHEN OPERATING IN MANUALFUEL CONTROL MODE, MAKESLOW, SMOOTH THROTTLEMOVEMENTS TO AVOID

Rev. 2 3·7


3-8 Rev. 5 17 OCT 2011 ECCN EAR99

COMPRESSOR STALL,OVERTEMPERATURE, OVERSPEED,AND POSSIBLE DRIVETRAINDAMAGE.

COORDINATE THROTTLE ANDCOLLECTIVE CHANGES TO AVOIDOVERLOADING NORMAL ENGINE.

Throttle (affected engine) — Increaseslowly. Adjust throttle and collective, asrequired, to maintain torque of affectedengine slightly below torque of normalengine.


NOTE

If values of overspeed parametersare unknown, or if NR exceeds 110%,or if transmission torque exceeds104%, land as soon as possible.


ENGINE OVERSPEED — GOVERNORACTUATOR FAILURE

• INDICATIONS:

ENG RPM (N2) and ROTOR RPM (NR)increase to approximately 101%.

RPM INCR DECR switch inoperative.

• PROCEDURE:

If this failure occurs during takeoff orlanding, no immediate corrective actionis necessary to complete e i thermaneuver.

As soon as practical, roll back boththrottles to maintain 97 to 100% ENGRPM (N 2 ) . Fur ther ad justment o fcollective and throttles simultaneouslywill allow full power at pilot discretion.


3-3-F. ENGINE OVERSPEED —DRIVESHAFT FAILURE

WARNING

FAILURE OF MAIN DRIVESHAFT TOTRANSMISSION WILL RESULT INCOMPLETE LOSS OF POWER TOMAIN ROTOR. ALTHOUGH COCKPITINDICATIONS FOR A DRIVESHAFTFAILURE ARE SOMEWHATCOMPARABLE TO A DUAL ENGINEFAILURE, IT IS IMPERATIVE THATAUTOROTATIVE FL IGHTPROCEDURES BE ESTABLISHEDIMMEDIATELY. FAILURE TO REACTIMMEDIATELY TO LOW ROTOR RPM(NR) AUDIO SIGNAL, CAUTIONLIGHT, AND TACHOMETER WILLRESULT IN LOSS OF CONTROL.

This is a situation involving a break in drivesystem, such as a severed main driveshaft totransmission. A failure of this type in poweredflight will result in nose of helicopter swingingto left (right side slip) and usually a roll offuselage. Nose down attitude may also bepresent. Severity of initial reaction will beaffected by airspeed, HD, GW, CG, and powerbeing used.

• INDICATIONS:

Left yaw.

Rapid decrease in ROTOR RPM (NR).

Rapid increase in ENG RPM (N2).

Illumination of ROTOR RPM (NR) cautionlight with audio.

Possible increase in noise due to:

• Overspeeding engine turbines

• Overspeeding combining gearbox

• Driveshaft breakage

• PROCEDURE:

Collective — As required to establishautorotative descent.


29 MAY 2012 Rev. 6 3-9ECCN EAR99

Airspeed — Establish for minimum rateof descent (65 KIAS) or maximum glide(90 KIAS).

Throttles — Close, if time permits.

Flight controls — As required forautorotative landing.

3-3-G. ENGINE COMPRESSOR STALL

• INDICATIONS:

Engine 'pops'.

High or erratic ITT.

Decreasing or erratic N1 and N2 RPM.

Torque oscillations.

• PROCEDURE:

Collective — Reduce; maintain slowcruise flight.

HEATER switch — ON.

ITT and N1 — Check for normalindications.

SEAT BELT and no smoking signs — ON.

If an audible compressor stall is noted, referto Maintenance Manual to determine cause.

3-3-H. ENGINE HOT START/SHUTDOWN

A hot start is caused by a combination ofexcessive fuel in combustion chamber anddelayed fuel ignition.

• INDICATIONS:

Rapid rise in ITT.

Flames emitting from exhaust.

• PROCEDURE:

Abort start of affected engine as follows:

Throttle — Closed, keep STARTswitch engaged.



START switch — Engaged until ITTdecreases to within limits.

Engine shutdown — Complete.

Helicopter — Exit, check for damage.

If ITT limits for starting were exceeded, referto engine Maintenance Manual for inspectionrequirements.

3-3-I. ENGINE OIL HOT

• INDICATIONS:

Engine oil temperature above limit of115°C.

• PROCEDURE:

Collective, airspeed — As required.

Throttle (affected engine) — Idle.

ENG switch — INCR; set ENG RPM (N2) at100% if possible.

If condition persists:

Throttle (affected engine) — Close.

Complete engine shutdown.


3-4. FIRE

3-4-A. ENGINE FIRE

3-4-A-1. DURING START

• INDICATIONS:

FIRE 1 PULL and/or FIRE 2 PULL handleilluminated.

• PROCEDURE:

Abort start of affected engine as follows:


FIRE PULL handle — PULL.

FIRE EXT switch — MAIN.

Fuel pump crossfeed switch —Override close.


3-10 Rev. 5 17 OCT 2011 ECCN EAR99

Fuel INTCON switch — OPEN.



Starter switch — Disengage.

If FIRE warning light remains illuminated formore than 10 seconds:

FIRE EXT switch — RESERVE.

Engine(s) shutdown — Complete.

Helicopter — Exit.

3-4-A-2. ENGINE FIRE DURING TAKEOFFOR APPROACH

• INDICATIONS:

FIRE 1 PULL and/or FIRE 2 PULL handleilluminated.

• PROCEDURE:

If a landing site is available, begindescent and approach. If landing sight isnot available, continue takeoff/approach.Proceed as follows:

Airspeed — 45 KIAS minimum.

Collective — Reduce, if possible.

Appropriate FIRE PULL handle —Pull.

FIRE EXT switch — MAIN.

If FIRE warning light remains illuminated formore than 10 seconds:


ENG RPM (N2) (remaining engine) — Setat 100%.

Land as soon as possible.



3-4-A-3. ENGINE FIRE IN FLIGHT

• INDICATIONS:

FIRE 1 and/or FIRE 2 PULL handleilluminated.

• PROCEDURE:

Immediately initiate emergency descent,if possible.

Shut down affected engine (1 or 2) asfollows:

FIRE PULL handle — Pull.

FIRE EXT switch — Main.


Fuel Crossfeed switch — Overrideclose.

Fuel interconnect switch — OPEN.

Engine BOOST PUMP — OFF.

Verify FIRE handle light, FUELBOOST caution light, and FUELswitch to be turned off are all foraffected engine.

Engine FUEL switch — OFF.

If FIRE warning light remains illuminated:


ENG RPM (N2) (remaining engine) — Setat 100%.


If a landing site is not readily available,proceed as follows:

FIRE PULL handle — In.

GEN (1 or 2) switch — OFF.

If No. 2 engine was shut down:

INV 3 to DC BUS 1 (if installed).




17 OCT 2011 Rev. 5 3-11ECCN EAR99

After landing:



3-4-B. CABIN SMOKE OR FUMES

• INDICATIONS:

Smoke, toxic fumes, etc. in cabin.

• PROCEDURE:

VENT BLOWER switch — ON.

Vents and accessible windows — Open.

If additional ventilation is required:

Airspeed — Reduce to 60 KIAS or less.

Passenger doors, windows, vents —Open.

If time and altitude permit and source issuspected to be electrical:

Affected system — Attempt to identifyand isolate.


3-4-C. BAGGAGE COMPARTMENT FIRE

• INDICATIONS:

BAGGAGE FIRE warning lightilluminated.

• PROCEDURE:

Reduce power to minimum required.


Inspect tailboom area for damage.

3-5. TAIL ROTOR

NOTE

The key to successful handling of atail rotor emergency lies in pilotability to quickly recognize type of

malfunction and to select properemergency procedure. Following is adiscussion of some types of tail rotormalfunctions and their probableeffects.

3-5-A. COMPLETE LOSS OF TAILROTOR THRUST

• INDICATIONS:

This is a situation involving a break in drivesystem, such as a severed driveshaft, whereintail rotor stops turning and delivers no thrust.A failure of this type in powered flight willresult in nose of helicopter swinging to right(left side slip) and usually a roll of fuselage.Nose down attitude may also be present.Severity of initial reaction will be affected byairspeed, HD, GW, CG, and power being used.

3-5-B. LOSS OF TAIL ROTOR THRUSTAT HOVER

• PROCEDURE:

Close throttles immediately and make ahovering autorotation landing. Yawing can beexpected on touchdown.

3-5-C. LOSS OF TAIL ROTOR THRUSTIN CLIMB

Degree of right yaw upon failure will begreater than that expected in level flight dueto higher power and anti-torque settings.

• PROCEDURE:

Close throttles and lower collectiveimmediately. Establish a glide speedslightly above normal autorotat ionapproach speed.

If a turn is required to reach a moredesirable place to land or to align intowind, make it to the right if possible. Aturn to r igh t can be more near lystreamlined by use of a little power.

BHT-212VFR-FM-1

Once aligned for landing, yaw can becontrolled In following manner:

• Right Yaw

If nose yaws right with power off, apulse of up collective will producemore friction In mast thrustbearings, creating a left moment.The greater the Input of pulse, themore the response will be.

IWARNING'

DO NOT ALLOW ROTOR RPM TODECAY BELOW MINIMUM LIMITS.

Moving collective upward abruptlyincreases rotor loading. Do nothold collective up as rotor rpm willdecrease lower than desirable. It isessential that collective be returnedto down position for autorotation.This cycle Is one pulse. Pulseshould be rapid (up and down) butshould not be used at low altitudes.

• Left YawIf nose yaws left with power off, aslight addition of power shouldarrest It. Further Increase in powerresults in more right yaw increase.

• LandingDuring final stages of approach, amild flare should be executed andall power to rotor should be off.Maintain helicopter in a slight flareand use collective smoothly toexecute a soft, slightly nose highlanding. Landing on aft portion ofskids will tend to correct side drift.If helicopter starts to turn, movecyclic as necessary to follow turnuntil helicopter comes to a completestop. This technique will, in mostcases, result in a run on typelanding.

FOR ZERO GROUND SPEEDLANDING, FLARE AND ABRUPT

FAA APPROVED

USE OF COLLECTIVE MAY CAUSENOSE TO YAW LEFT. DO NOTCORRECT WITH THROTTLE.ALTHOUGH APPLICATION OFTHROTTLE WILL RESULT INYAWING TO RIGHT, ADDITION OFPOWER IS A VERY STRONGRESPONSE MEASURE AND ISTOO SENSITIVE FOR PILOT TOMANAGE PROPERLY. DO NOTADD POWER AT THIS TIME.SLIGHT YAWING UPONTOUCHDOWN AT ZERO GROUNDSPEED MAY BE EXPECTED.

3-5-0. LOSS OF TAIL ROTORTHRUST IN LEVEL FLIGHT ORDESCENTPROCEDURES:

Close throttles and reduce collectiveimmediately. Attain an airspeed slightlyabove normal autorotative glide speed.

If altitude permits with AIRSPEED above60 KIAS, throttle and collective may begently applied to determine if somedegree of powered flight can beresumed. If unacceptable yawing isexperienced, re-enter autorotation andcontinue descent to a landing.

Landing technique is same asprescribed for climb condition above.

3-5-E. LOSS OF TAIL ROTORCOMPONENTS

Loss of any tail rotor component will resultin a forward CG shift. Other thanadditional nose down pitching, thissituation would be quite similar tocomplete loss of tail rotor thrust asdiscussed above.

3-5-F. TAIL ROTOR FIXED PITCHFAILURES

INDICATIONS:

Tail rotor pitch change control failures arecharacterized either by a lack ofdirectional response when a pedal ispushed or by locked pedals. If pedals cannot be moved with a moderate amount offorce, do not attempt to apply a maximum

•••

•••

I 3-12 Rev. 2

•••

•••

FAA APPROVED

effort since a more serious malfunctioncould result.

3-5-G. FIXED PITCH FAILURE AT AHOVER

PROCEDURES:

Do not close throttles unless a severeright yaw occurs. If pedals lock in anyposition at a hover, landing from a hovercan be accomplished with greater safetyunder power controlled flight rather thanby closing throttles and enteringautorotation.

3-5-H. FIXED PITCH FAILURE INFLIGHT

If tail rotor fixed pitch failure occursduring climb (left pedal applied), cruise(approximately neutral pedals), anddescent (right pedal applied), a descentand landing can be effected safely by useof power and throttle changes.

PROCEDURES:

If helicopter Is In a trimmed conditionwhen malfunction Is discovered, enginepower and airspeed should be noted andhelicopter flown to a suitable landing area.

Combinations of ENG TORQUE, ROTORRPM (N R), and AIRSPEED will correct oraggravate yaw attitude and these shouldbe adjusted as required to control yawduring landing.

• Right Pedal Locked Forward ofNeutral

Power should be reduced and ENGRPM (N2) maintained within green arc.This will help streamline helicopter inflight. Right turns are easier than leftturns. AIRSPEED should bemaintained at or above 60 KIAS.

Execute a normal to steep approachadjusting power as necessary tominimize or prevent right yaw.Maintain ENG RPM (N 2 ) and an

BHT-212VFR-FM-1

AIRSPEED of 60 KIAS during initialpart of approach.

At 60 to 75 feet AGL and when landingarea can be made, start a slowdeceleration to arrive at Intendedlanding point with AIRSPEED at about25 KIAS.

At 2 to 5 feet AGL, slOWly reducethrottle to overcome yaw effect andallow helicopter to settle. Whenaligned with landing area, allowhelicopter to touch down.

After ground contact, use collectiveand throttle as necessary to maintainalignment with landing strip, and tominimize forward speed. If helicopterstarts to turn, move cyclic asnecessary to follow turn untilhelicopter comes to a complete stop.

• Left Pedal Locked Forward ofNeutral

Reduce power and maintain ENG RPM(N2) within green arc. Normal turnscan be safely made under theseconditions, although helicopter nosemay be displaced to left.

On final approach, begin a slowdeceleration so as to arrive at a pointabout four to five feet above intendedtouchdown area as effectivetranslational lift is lost.

Apply collective to stop rate ofdescent and forward speed, and toalign helicopter with intended landingpath. Allow helicopter to touch downat near zero ground speed,maintaining alignment with throttle.

• Pedals Locked in Neutral

Reduce power and maintain ENG RPM(N 2) within green arc. Normal turnscan be safely made under theseconditions.

Execute a normal to shallow approach,holding AIRSPEED at 60 KIAS duringinitial part of approach. Adjust power

Rev. 2 3-13 I

BHT-212VFR-FM-1

as necessary to minimize or preventright yaw.

At 50 to 75 feet AGL and when landingarea can be made, start a decelerationto arrive at intended landing point withAIRSPEED at 25 KIAS.

At 2 to 5 feet AGL, use throttle slowlyas necessary to maintain alignmentwith landing area and to control yaw;do not allow helicopter to settle untilalignment is assured, then touchdown.

After ground contact, use collectiveand throttle as necessary to minimizeforward speed and to maintainalignment. Move cyclic as necessaryto follow turn until helicopter hascome to a complete stop.

3-5-J. LOSS OF PITCH CHANGECONTROL LINKAGE

INDICATIONS:

In this type of failure, pitch changemechanism is broken at some point andtail rotor will assume a blade angledetermined by aerodynamic andcounterbalance forces.

PROCEDURES:

Corrective action procedures aredescribed in FIXED PITCH FAILURESabove. Specific procedure to be useddepends on yaw change experienced.

3-6. HYDRAULIC SYSTEM

The helicopter has two hydraulic poweredflight control systems (1 and 2). Bothsystems supply power to collective andcyclic but tail rotor is powered only bysystem 1.

If system pressure or temperature exceedslimits, affected system should be turnedoff. Continued flight and normalmaneuvers can be accomplished onremaining system. Land as soon aspractical. If system no. 1 fails and is

3-14 Rev. 2

FAA APPROVED

turned off, tail rotor control forces willincrease but no change In limitationsresult.

3-7. ELECTRICAL SYSTEM

3-7-A. DC FAILURE TO PRODUCEPOWER

If either generator has not failed but circuitis open, reset generator by movinggenerator switch to RESET, then ON.

For single generator operation,nonessential busses may be restored bymoving NON ESS BUS switch fromNORMAL to MANUAL. Monitor to ensureloads are within limits.

3-7-B. AC - FAILURE TO PRODUCEPOWER

If any Inverter fails to produce power,check appropriate AC circuit breakers in.

3-8. FUEL SYSTEM

3-B-A. FUEL BOOST PUMPFAILURE

INDICATION:

NO. 1 or NO.2 FUEL BOOST CautionLight illuminates.

PROCEDURE:

IF EITHER BOOST PUMP FAILS,FUEL EXHAUSTION COULDOCCUR AT 60 POUNDSINDICATED ON FUEL QUANTITYGAGE.

If practical, descend below 5000 feet Hp

to prevent possible fuel starvation in theevent remaining boost pump fails.

•••

•

•••

FAA APPROVED

Fuel interconnect switch - OPEN.

NOTE

If fuel crossfeed switch is InNORM position, crossfeed valvewill be automatically openedallowing remaining pump tosupply fuel to both engines.


3-8-B. FUEL FILTER PARTIALLYBLOCKED


3-8-C. FUEL QUANTITYINDICATION MALFUNCTIONS

INDICATION:

BHT-212VFR-FM-1

3-10. COMMUNICATIONSYSTEM

3-10-A. NAVIGATION RADIOFAILURE

NAV AC switch - BUS NO.2.

3-10-B. INTERCOM FAILURE

INDICATION:

Weak or no reception in headsets.

PROCEDURE:

Check headset connection.

Verify volume and ICS controls setproperly.

Cycle ICS circuit breaker out and in.

IFuel quantity Indication freezes in place.(Possible power failure to the fuel quantityindicator system.)

3-11. CABIN HEATER

NOTE

•••

PROCEDURE:

FUEL QTY circuit breaker - Recycle.

Fuel interconnect switch - OPEN.

NOTE

A failure in the fuel quantityindicating system will have noeffect on fuel low caution light,fuel interconect, fuel crossfeed,fuel boost, or fuel valve andindications.

I

3-9. AUTOMATIC FLIGHTCONTROLS SYSTEM

Not applicable to VFR helicopter.

A malfunction In the bleed airheater controls mayor may notcause heater to becomeInoperative.

INDICATION:

HEATER AIR LINE caution lightilluminates.

Heated airflow does not shut off whenthermostat knob is turned to full coldposition.

PROCEDURE:

HEATER switch - OFF immediately.

Rev. 2 3-15

BHT-212VFR-FM-1

CABIN HTR circuit breaker - Check; Ifout, do not reset.

Check prior to next flight.

3-12. LANDING GEAR

Not applicable to skid gear helicopters.

3-13. STATIC PORTOBSTRUCTION

Erratic readings from airspeed indicator,vertical speed indicator, and altimeter mayoccur when operating in rain with STATICSOURCE switch (If Installed) In PRI.

3-16

FAA APPROVED

If this occurs, proceed as follows:

Windows and vents - Close.

Heater SYSTEM SELECTOR switch (ifinstalled) - OFF.

STATIC SOURCE switch (if installed) ALTN.

NOTE

This procedure selects analternate static source (cabin air)for pilot instruments only.

•••

•••

BHT-212VFR-FM-l

CORRECTIVE ACTION

Pull FIRE PULL handle, positionFIRE EXT switch to MAIN, closethrottle, position FIRE EXT switch toRESERVE, if necessary. Land assoon as possible.

Table 3-1. WARNING LIGHTS

FAULT CONDITION

Smoke incompartment.

Fire in engine compartment.

BAGGAGE FIRE

ENG lOUT/ENG 2 Engine GAS PROD RPM (N1) Check engine torque, GAS PRODOUT below 53 ± 2%. (N1) RPM, ENG (N 2) RPM, and ITT.

Adjust power and airspeed. Resetremaining ENG (N2) RPM to 100% ifpossible. Close throttle of affectedengine. Refer to ENGINE FAILUREand ENGINE RESTART. Land assoon as practical.

bag gag e Reduce power to minimum required.Land as soon as possible. Inspecttail boom area for damage.

PANELWORDING

FIRE 1 PULU FIRE 2PULL

FAA APPROVED

••

•

XMSN OIL PRESS Transmission oil pressure Reduce power. Land as soon asbelow limit. possible.

XMSN OIL TEMP Transmission oiltemperature above limit.

Reduce power. Check XMSN OILtemperature. If not within limits,land as soon as possible.

BATTERY TEMP (If Battery temperature aboveinstalled) limit.

Land as soon as

••

C BOX OIL PRESS

C BOX OIL TEMP

Combining gearbox oilpressure below limit.

Combining gearbox oiltemperature above limit.

Reduce power.possible.

Reduce power. Check GEAR BOXtemperature. If not within limits,land as soon as possible.

Position BATTERY switches to OFF.Land as soon as practical. IfBATTERY caution segment does notillumninate, turn GEN 2 OFF. Landas soon as possible.

•3-17

Table 3-1. WARNING LIGHTS (Cont)

BHT-212VFR-FM-1

PANELWORDING FAULT CONDITION

FAA APPROVED

CORRECTIVE ACTION

!WARNING'

BATTERY SHALL NOT BE USEDFOR ENGINE START AFTERILLUMINATION OF BATTERY TEMPLIGHT. BATTERY SHALL BEREMOVED AND SERVICED INACCORDANCE WITH MANUFACTURER'S INSTRUCTIONS PRIORTO RETURN TO SERVICE.

•••

ROT 0 R B K ( i f Rotor brake linings not Check rotor brake handle in detent.installed) retracted. If light remains illuminated, land as

soon as possible.

3-18

•••

ENG 1 DC G E N - Failure of DC generator. Position GEN 1 switch to RESETERATOR then ON. Position to OFF if reset

not possible. SN 30554 and sub.position INV 3 switch to ON DC BUS2.

CORRECTIVE ACTION

BHT-212VFR-FM-1

Table 3-2. CAUTION LIGHTS

FAULT CONDITION

FAA APPROVED

Engine oil pressure below Shut down no. 1 engine. SN 30554limit. and sub.,- Position INV 3 switch to

ON DC BUS 2.

ENG 2 0 IL PRE S- Engine oil pressure below Shut down no. 2 engine. SN 30554SURE limit. and sub. -, Position INV 3 switch to

ON DC BUS 1 and BATTERY BUS 2switch to OFF. Position BATTERYBUS 1 switch to ON.

ENG 1 OIL PRESSURE

PANELWORDING•

••

ENG 2 DC G E N - Failure of DC generator.ERATOR

ENG 1 FUEL BOOST/ Applicable pump pressureENG 2 FUEL BOOST is low or pump has failed.•

••

ENG 1 PART SEPOFF/ENG 2 PARTSEP OFF

Separator bypass doorclosed. Ice and dustprotection systemInoperative.

Position GEN 2 switch to RESETthen ON. Position to OFF if resetnot possible.

SN 30554 and subsequentPosition INV 3 switch to ON DC BUS1 and BATTERY BUS 2 switch toOFF. Position BATTERY BUS 1switch to ON.

Check RPM WARN and PART SEPcircuit breakers in. Position PARTSEP switch to OVRD ON. If PARTSEP OFF light remains illuminated,correct malfunction prior to nextflight.

If practical, descend to 5000 feet Hpor below for remainder of flight dueto possible fuel starvation of engineif remaining boost pump fails. Ifeither fuel boost pump fails,crossfeed valve is opened ,by a flowswitch, allowing remaining pump tofurnish pressure to both engine fuelsystems.

Above sequence Is possible withfuel pump crossfeed switch Innormal position.

3-19

FAA APPROVED

Table 3-2. CAUTION LIGHTS (Cant)

BHT-212VFR-FM-1

PANELWORDING FAULT CONDITION CORRECTIVE ACTION •

•I ENG 1 FUEL FILTER! Filter and/or heater is

ENG 2 FUEL FILTER partially clogged.

ENG 1 FUEL LOW/ Fuel remaining is approx-ENG 2 FUEL LOW imately 140 pounds.

If this automatic function Is notdesired, fuel pump crossfeed switchshould be positioned to override •close position and interconnectswitch to open.

Land as soon as practical. Correctmalfunction prior to next flight

Fuel interconnect switch in normalposition (closed) separates twolower fuel cells. When either FUELLOW light Illuminates, interconnectswitch should be positioned toOPEN. This will allow fuel quantityin lower tanks to equalize.

In event a fuel boost failure hasoccurred, or occurs afterinterconnect switch is positioned toOPEN, fuel in lower tanks will beavailable to both engines, througheither boost pump.

ENG RPM, TORQUE, and ITT mustbe controlled manually by throttleand collective.

ENG 1 G 0 V GOV switch in MANUAL.MANUAUENG 2 GOVMANUAL

ENG 1 CHIP/ENG 2 Metal particles in engineCHIP oil.

ENG 1 FUEL VALVE/ Fuel valve not properlyENG 2 FUEL VALVE seated or circuit breaker( S N 3 0 5 9 7 and open.subsequent)

ENG 1 GEN OVHT/ Generator overheating.ENG 2 GEN OVHT(SN 30597 andsubsequent)

CAUTION PANEL Caution panel inoperative.(SN 30597 andsubsequent)

INVERTER #1 Failure of no. 1 inverter.

3-20 Rev. 2

Reduce power and shut downengine as soon as practical topreclude engine damage. Land assoon as practical.

Check FUEL VALVE circuit breakersin. Land as soon as practical. If onground, position FUEL switch toOFF then ON.

Position GEN switch to OFF.Correct malfunction prior to nextflight.

Check MASTER CAUTION circuitbreaker in. Monitor Instruments.Land as soon as practical.

SN 30504 through 30553 - Check INV1 PWR and (NV 1 CONT circuitbreakers in. Position INV 1 switchto OFF.

•••

Table 3-2. CAUTION LIGHTS (Cont)

INVERTER #3 Failure of no. 3 inverter.(SN 30554 andsubsequent)

•••

FAA APPROVED

PANELWORDING

INVERTER #2

FAULT CONDITION

Failure of no. 2 inverter.

BHT-212VFR-FM-1

CORRECTIVE ACTION

SN 30554 and SUbsequent - Checkno. 1 AC voltmeter to determine thatno. 3 inverter has automaticallyassumed no. 1 inverter load.

SN prior to 30554 - Check INV 2PWR and INV 2 CONT circuitbreakers in. Position INV 2 switchto OFF.

SN 30554 and subsequent - Checkno. 2 AC voltmeter to determine thatno. 3 inverter has automaticallyassumed no. 2 inverter load.

Position INV 3 switch to other DCBUS. If light stays illuminated,position INV 3 switch to OFF.

EXTERNAL POWER

DOOR LOCK

External power connected Disconnect external power if stillto helicopter or external applied, close and latch externalpower door not closed power door.properly.

Cab ina ft door (s) 0 r Check doors closed and latched.baggage compartment doornot locked.

Metal particles in tall rotor Land as soon as practical.gearbox.

Metal particles in trans- Reduce power. Land as soon asmission oil. practical.

Met a I par tic I e sin Land as soon as practical.intermediate gearbox oil.

•••

BATTERY

CHIP C BOX

CHIP XMSN

CHIP 42° BOX(SN 30504 through30596)

CHIP 90° BOX(SN 30504 through30596)

Battery relay open or bothbattery switches in sameposition.

Metal particles in combining gearbox oil.

Position both BATTERY switches toOFF. Position BATTERY switch toON DC BUS 1. If light does notextinguish, position switch to OFF,and position other switch to ON DCBUS 2. If light does not extinguish,position switch to OFF.

Reduce power. Land as soon aspractical.

3-21

CHIP 42°/90° BOX Metal particles in inter(S N 30597 and mediate and/or tail rotorsubsequent) gearbox.

HYDRAULIC Hydraulic pressure low or( S N 3 0 5 5 4 and temperature above limit.subsequent)

FAA APPROVED

Table 3-2. CAUTION LIGHTS (Cant)

•••CORRECTIVE ACTION

Verify fault from gage readings. Ifpressure Is low or temperature ishigh, turn affected system off. Landas soon as practical.

Check FUEL XFEED circuit breakersin. Cycle FUEL XFEED switch.

Land as soon as practical

Fuel crossfeed valve notfUlly open or closed, orFUEL XFEED circuit breakeropen.

He ate r mix i n g val ve Turn heater off Immediately.malfunction.

FAULT CONDITION

HEATER AIR LINE

PANELWORDING

FUEL XFEED(SN 30597 andsubsequent)

BHT-212VFR-FM-1

RPM

FOR SYS FAIL(if installed)

ROTOR (NR) RPM above orbelow operating limits.

Flight data recorderInoperative.

Adjust collective and/or RPM INCRDECR switch as required.

Refer to applicable regulations foroperation with flight data recorderinoperative.

•••

3-22



Section 4PERFORMANCE

4TABLE OF CONTENTS


Introduction ............................................................................................ 4-1 ........... 4-3Power Assurance Check ....................................................................... 4-2 ........... 4-3

Power Assurance Checks — PT6T-3B............................................. 4-2-A ....... 4-3Power Assurance Check — PT6T-3 ................................................. 4-2-B ....... 4-3

Density Altitude...................................................................................... 4-3 ........... 4-3Height-Velocity Envelope...................................................................... 4-4 ........... 4-4Hover Ceiling.......................................................................................... 4-5 ........... 4-4Takeoff Distance .................................................................................... 4-6 ........... 4-4Climb and Descent................................................................................. 4-7 ........... 4-4

Twin Engine Takeoff Climbout Speed.............................................. 4-7-A ....... 4-4Twin Engine Rate of Climb................................................................ 4-7-B ....... 4-4Single Engine Rate of Climb — PT6T-3B......................................... 4-7-C ....... 4-4Single Engine Rate of Climb — PT6T-3 ........................................... 4-7-D ....... 4-4

Airspeed Calibration.............................................................................. 4-8 ........... 4-4Landing Distance ................................................................................... 4-9 ........... 4-5Not Used ................................................................................................. 4-10 ......... 4-5Sample Performance Problem.............................................................. 4-11 ......... 4-5

LIST OF FIGURES

Figure PageSubject Number Number

Power Assurance Check Chart — PT6T-3B ........................................ 4-1 ........... 4-7Power Assurance Check Chart — PT6T-3 ........................................... 4-2 ........... 4-11Density Altitude Chart ........................................................................... 4-3 ........... 4-12Hover Ceiling In Ground Effect............................................................. 4-4 ........... 4-13Hover Ceiling Out of Ground Effect ..................................................... 4-5 ........... 4-16Critical Relative Wind Azimuths for Hover Flight ............................... 4-6 ........... 4-24Takeoff Distance Over a 50 Foot (15.2 Meter) Obstacle ..................... 4-7 ........... 4-25Twin Engine Takeoff Climbout Speed.................................................. 4-8 ........... 4-26Twin Engine Rate of Climb.................................................................... 4-9 ........... 4-27Single Engine Rate of Climb — PT6T-3B............................................. 4-10 ......... 4-57Single Engine Rate of Climb — PT6T-3 ............................................... 4-11 ......... 4-67Pilot Airspeed System Calibration ....................................................... 4-12 ......... 4-77


4-2 Rev. 5 17 OCT 2011 ECCN EAR99

LIST OF FIGURES (CONT)

Figure PageSubject Number NumberCopilot Airspeed System Calibration .................................................. 4-13......... 4-78Single Engine Landing Distance Over a 50 Foot (15.2 Meter)Obstacle.................................................................................................. 4-14......... 4-79

•••

•••

FAA APPROVED

Section 4

4-1. INTRODUCTION

Performance data presented herein arederived from engine manufacturer'sspecification power for engine lessinstallation losses. These data areapplicable to basic helicopter without anyoptional equipment that would appreciablyaffect lift, drag, 0 .. power available.

4-2. POWER ASSURANCECHECK

4-2-A. POWER ASSURANCECHECKS - PT6T-38

Power assurance check charts (figure 4-1)are provided to determine if engines canproduce installed specification power.

A power assurance check should beperformed daily. Additional checks shouldbe made if unusual operating conditions orindications arise. Hover check isperformed prior to takeoff and in-flightcheck is provided for periodic in-flightmonitoring of engine performance. Eitherpower assurance check may be selected atdiscretion of pilot. It is pilot responsibilityto accomplish procedure safely,considering passenger load, terrain beingoverflown, and qualifications of personson board to assist in watching for other airtraffic and to record power check data.

If either engine does not meetrequirements of hover or in-flight powerassurance check, published performancemay not be achievable. Cause of enginepower loss, or excessive ITT or GAS PRODRPM (NI) should be determined as soon aspractical.

BHT-212VFR-FM-1

4-2-8. POWER ASSURANCECHECK - PT6T-3

Power assurance check chart (figure 4-2)is provided to determine if engines canproduce installed specification power.

A power assurance check should beperformed daily. Additional checks shouldbe made if unusual operating conditions orindications arise. Ground check isperformed prior to takeoff.

If either engine does not meetrequirements of ground power assurancecheck, published performance may not beachievable. Cause of engine power loss,or excessive ITT or GAS PROD RPM (NI),

should be determined as soon as practical.

4-3. DENSITY ALTITUDE

A Density Altitude Chart (figure 4-3) isprovided to aid in calculation ofperformance and limitations. Densityaltitude is an expression of the density ofthe air in terms of height above sea level;hence, the less dense the air, the higherthe density altitude. For standardconditions of temperature and pressure,density altitude is the same as pressurealtitude. As temperature increases abovestandard for any altitude, the densityaltitude will also increase to values higherthan pressure altitude. The chartexpresses density altitude as a function ofpressure altitude and temperature.

The chart also includes the inverse of thesquare root of the density ratio (t/-1a),

4-3

BHT-212VFR-FM-l

which is used to calculate KTAS by therelation: KTAS = KCAS x lIvcr

EXAMPLE

If ambient temperature is -15°C and thepressure altitude is 6000 feet, find thedensity altitude, lIvcr, and true airspeed for100 KCAS.

SOLUTION

Enter the bottom of the chart at -15°C.

Move vertically to the 6000 foot pressurealtitude line.

From this point, move horizontally to theleft and read a density altitude of 4000 feetand move horizontally to the right andread lNcr =100 x 1.06 =106 KTAS.

4-4. HEIGHT - VELOCITYENVELOPE

Refer to SECTION 1.

4-5. HOVER CEILING

IGE and OGE hover ceiling charts (figures4-4 and 4-5) present hover performance asallowable GW for conditions of Hp andOAT.

Published IGE hover performance can beachieved with adequate tail rotor controlmargins in relative winds up to 20 knotsfrom any direction. More favorable tailrotor control margins will be realized whenwinds are outside critical relative windazimuth area (figure 4-6).

Downwind takeoffs and landings are notrecommended.

4-6. TAKEOFF DISTANCE

Takeoff distance required to clear a 50 foot(15.2 meter) obstacle is presented in figure4-7 as a function of OAT, Hp , and GW.

4-4

FAA APPROVED

4-7. CLIMB AND DESCENT

4-7-A. TWIN ENGINE TAKEOFFCLiMBOUT SPEED

Twin engine takeoff climbout speed (VTOCS)

is that indicated airspeed which will allowtakeoff distance over a 50 foot (15.2 meter)obstacle to be realized and will complywith HV restrictions to allow a safe landingin case of an engine failure (figure 4-8.)

4-7-B. TWIN ENGINE RATE OFCLIMB

Twin engine rate of climb charts areprovided for takeoff power and maximumcontinuous power for GW ranging from7000 to 11,200 pounds (figure 4-9).

4-7-C. SINGLE ENGINE RATE OFCLIMB - PT6T-3B

Single engine rate of climb charts areprovided for 2'/' minute OEI power and 30minute OEI power for GW ranging from7000 to 11,200 pounds (figure 4-10).

4-7-0. SINGLE ENGINE RATE OFCLIMB - PT6T-3

Single engine rate of climb charts areprovided for 30 minute power andmaximum continuous power for GWranging from 7000 to 11,200 pounds (figure4-11 ).

4-8. AIRSPEEDCALIBRATION

Indicated airspeed (lAS) corrected forposition and instrument error equalscalibrated airspeed (CAS). Determinecorrected airspeed from figures 4-12 and4-13.

•••

•••


ECCN EAR99

4-9. LANDING DISTANCE

Single engine landing distance over a 50-foot(15.2-m) obstacle is shown in Figure 4-14 as afunction of OAT, HP, and GW.

4-10. NOT USED

4-11. SAMPLE PERFORMANCEPROBLEM

Helicopter is chartered to transport cargof rom a i rpor t A (e leva t ion 3000 fee t ,temperature 30°C) to airport B (elevation8500 feet, temperature 19°C). Duration offlight will be 30 minutes and a 30-minute fuelreserve at cruise power is required. Averagefue l consumption is determined f romhelicopter historical records to be 545 pounds(247 kg) per hour at 8000 feet HP, 20°C OAT,and cruise power (approximately 55% torque).Crew consists of one 190-pound (86-kg) pilot.Determine maximum allowable cargo payloadfor flight.

• SOLUTION

Fuel required for 30-minute fl ight plus30-minute reserve is 545 pounds (247 kg).Considering fuel needed for start, run-up, taxi,and takeoff, pilot elects to refuel to 600pounds (272 kg).

According to Weight-altitude-temperaturelimitations for takeoff, landing, and in groundeffect maneuvers chart (Section 1), maximumallowable GW for existing ambient conditionsare as follows:

If pilot takes off at 11,000 pounds (4989 kg), hewill arrive at destination 10,728 pounds(4866 kg) (11,000 - 272 pounds) (4989 -123 kg). This exceeds maximum allowablelanding weight by 1478 pounds (670 kg)(10,728 - 9250 pounds) (4866 - 4196 kg);therefore, maximum allowable payload mustbe based on allowable landing weight for thisparticular flight.

Although it is permissible to take off fromairport A at 11,000 pounds (4989 kg) GW, uponlanding at airport B helicopter would haveexceeded a l lowab le land ing GW by1478 pounds (670 kg) due to higher HD atdestination.

Maximum allowable takeoff GW at airport A (5676 feet HD)

11,000 pounds(4989 kg)

Maximum allowable landing GW at airport B (10,861 feet HD)

9250 pounds(4196 kg)

Estimated fuel burnoff during flight (30 minutes at 545 pounds per hour)

272 pounds(123 kg)

Maximum allowable landing GW


GW at landing: 6482 pounds(2940 kg)

Empty weight 5942 pounds(2695 kg)

Oil 22 pounds(10 kg)

Pilot 190 pounds(86 kg)

Fuel (600 - 272 pounds)(272 - 123 kg)

328 pounds(149 kg)

Maximum allowable cargo payload


17 OCT 2011 Rev. 5 4-5/4-6

17 OCT 2011 Rev. 5 4-7


ECCN EAR99

Figure 4-1. Power Assurance Check Chart — PT6T-3B (Sheet 1 of 4)

212_FM_VFR_04_0001a+

HP — FT

-1000

0(SEA LEVEL)

4-8 Rev. 5 17 OCT 2011


ECCN EAR99


212_FM_VFR_04_0001b+

HP — FT

-1000

0(SEA LEVEL)

– 40 – 50

17 OCT 2011 Rev. 5 4-9


ECCN EAR99


212_FM_VFR_04_0001c+

HP — FT

-1000

0(SEA LEVEL)

4-10 Rev. 5 17 OCT 2011


ECCN EAR99


212_FM_VFR_04_0001d+

HP — FT

-1000

0(SEA LEVEL)

– 40 – 50


17 OCT 2011 Rev. 5 4-11ECCN EAR99

Figure 4-2. Power Assurance Check Chart — PT6T-3

212_FM_IFR_04_0002+

•••

•••

1-{5

-172

-16B 170--166-164--1.62-160--158- 156--1.54- 152--150- 1 4B--146-144--1.42-140--138- 136__ 1.34

- 132--130

-128__ 1.26

- 1.24

--122

- 120--118

-116

--1.14

- 112__ 110

-096

- 1.0B

--106

- 104

--1.02

-1.00

--0.98

FAA APPROVED

·70 ·60 ,50 ·40 ·30 -20 ·10 0 10 20 30 40 50 60

4

V L,;-

~ 180V L \'~ EXAMPLE: IF AMBIENT TEMP. IS ·15·C

k~QI:P/"'"i? 178 AND PRESSURE ALT IS 6.000 FEET. THE

b./0~[....) ....'1/ 176 DENSITY ALT IS 4.000 FEET AND ~ IS 106

V V'\ ........ / 1.74

1/ / V ,o,to~"v- / ........ V ........ V ................I\V~~ 1/ V :.--- ........ L,;- ..... . :..-

/ ./ ~ V V ........ ........ --- ........VV V

V V V V V V I..--" ./L--' V .....V V- I..----" \ I..--" 1/ V V L,;- V L,;-V L,;-V V

./ VE.1.()~),..----

I..--" V L,;- ,..,.- ./

V- V V 1\ k"~~ ./ V- I...--- V V L,;-

"" I...... ./ t· /" V- V ./ V L,;- V/ V V ,/ ,../ ,.-/ V........ V V~~ \«\:1 ........ ........

"" V V- ,.../ \./ / ,../ VVO~';"'-- ........ .....V ,/ ...... ./ ~± ~ ...\.~~/ V- /'V i--'V V V V[\V~)- ~VV-~;...- ........ V l/

"" ...... V ......~. ./V\,V-~ I...--- I___ V V- VV V V V [/ 1\1..--" Vi .vf ./ V V ........

"" 1/ V V V \.1/ ~ ...-k' V V -' V VV ./ ...... -t:"'11.~~ 'v -'

...... V VV V- / ,/ ,/ \.~~/ ,/ ..... V ........6/ V ,../ ,/' / ~....... :7 / ,../ /' V

'/ V V V 7 ;/ V V ,../ L/

---V- L..--

./ V V- ,../ "/ :......- \. V ./ ./ ........L7 ,/ ,/

"" ~~~)-- V ./V ,.-/

2V V V V V V 1\ I..--"~~ __ V V ........

V V V l../ V V ~. l7 V V ........V /"V0l/ V V V I..--" V ./ V V

V I..----" /' ,/ V ./ ,/' '\V- I...--- l/v V V- I...--8~"..()yV V / 1./ V- / --/ V V ,/ / V V 1\V~~ ...... V V

6/ / ,/' ,.../ V V V ~ V V V/' V V ,/

"",/ V :.--- V /

/ r/ V V V I..--" \l..' v / /[7

V"" l../ V 1/ ...... V~\. V V V2

V V V V 1\ V: \.~ V V ./<:,~...

"" V V V V- I..----" I..----" v -;.... 1/ -- V0/

./ ./ -- ,/ V k?

2 ./ V V- ,/ ./ ...-: V- ,/ /' \ ....... /'~ booV ,../ ./ V. ,<' /...... ...... / "" ./ ()~V V V ,/ ,/ v 1\ V .~ )/1./V

4

TEMPERATURE - °C21 2VFR-FM- 4·3

36

Figure 4·3. Density altitude chart

26

3B

34

32

30

28

24

20

22

18

14

(11.0)

(10.01

(9.01

(8.01

8 (7.0)0...X

E(6.0)

~LL

WC

(5.0)~~

i=...J<l:> (4.0)~

iiizwC (3.0)

(2.01

(1.0)

(0.5)

(·0.51

(·1.01

BHT-212VFR-FM-1

4-12

Figure 4-4. Hover ceiling in ground effect (Sheet 1 of 3)

CEILINGSDENSITYS FOR

LANDING.CAN BE

AT THEWEIGHTSTAKEOFF

BHT-212VFR-FM-l

212VFR·FM·4·4·1

SKID HEIGHT 4 FTHEATER ON OR OFF

WINTERIZATION KIT HTR ON OR OFF

8000 9000 10.000 11.000 12.000(3629) (4082) (4536) (49891 54431

GW - LB(KG)

HOVER CEILINGIN GROUND EFFECT

/14.000 FT HD LIMIT

\.i7 1/1\ NOTE: THESE IGE HOVER

ARE BASED ON

IC~I \ \ AL T1TUDE LIMIT(J 1 TAKEOFF AND

~~ ~ THIS HELICOPTER"' 1 1\I HOVERED IGE

Is:t>C) V \ \ INDICATED GROSS1\~ITH LESS THANf-V I 1/~HOT DAY LIMIT POWER.1~.~ f\ 1\

/ '\ \LL li )/ \ MAXIMUM GW L1MIT-" \

~1 V 1\1/ II 1/

V ~ / I

/:~#/

t

/I?X'~

1/I • !

1/ I

~ MAXIMUM OAT HEATER ON (21 ·el I

I

1 11.200I '(i~81)-II

o 10 20 30 40 50

OAT - °C

POWER: SEE NOTE BELOWENG RPM 100% IN2)GENERATOR 150 AMPS EACHO· TO 52·C

FAA APPROVED

•

•

•

•

•

•4-13

Figure 4-4. Hover ceiling in ground effect (Sheet 2 of 3) •

••

••

•EIUNGS

DENSITY5 FOR

LANDING.CAN BE

AT THEWEIGHTSTAKEOFF

FAA APPROVED

212VFR-FM-4-4-2



8000 9000 10.000 11.000 12.000136291 140821 145361 (4989) (5443)

GW - LBIKGI


14.000 FT HD LIMIT \

~.JI V NOTE: THESE IGE HOVER C

- 1/ / \ARE BASED ON

,0/1 AL T1TUDE LIMITTAKEOFF AND

V~#I / 1\ THIS HELICOPTERf-

\ HOVERED IGE,~ I / INDICATED GROSS

17&V V \;-"ITH LESS THANPOWER.

,y 1/ ~

11 ~/ 1/ '\1/ 1,01f / MAXIMUM GW LIMIT U i\

1/ lei / \

1/ ~ /

/ / // ~~ /

I/ /

/ ~ /

1/ 1/1; 1/

1/ / '"/ ~«~ 1/

1/ /~~~

1/ 11.200/

15ifOI-/ /

·60 -50 ·40 -30 ·20 -10 0

OAT - °C

POWER: SEE NOTE BELOWENG RPM 100% (N21GENERATOR 150 AMPS EACHO' TO-54'C

BHT-212VFR-FM-l

4-14

Figure 4-4. Hover ceiling in ground effect (Sheet 3 of 3)

• 14,000 FT HD LIMIT •k1, ./'\ 1\

~ I \ \~)f I /\ R\ M~XI~UM GW LIMIT

~~lV \ \~

I /\ ~ ~l 0

V "V \O-~"""

I~ ~ol<osY'1 / 1-~ HOT DAY LIMIT~h\ ~I

/ 1// \ 1--\l!~,,,#/ / \\

VI V r - - - i---- - ~ \1\I

~ ~/ J/ ~~~ I~/ \' (-.

~\I 1 '\

~ l/1- x-q v I/ ~c:P' I- / l.-MAXIMDM OAT HEATER ON (21 °el

/ I II

I t11.200

I I 'ii8T-

•••

•••

FAA APPROVED

MAXIMUM CONTINUOUS POWERENG RPM 100% fN2)GENERATOR 150 AMPS EACH0° TO 52°C

o 10 20 30 40 50OAT - °C

BHT-212VFR-FM-1




8000 9000 10.000 11 ,000 12.000136291 (4082) (4536) (49891 (5443)

GW - L8(KG)212VFR-FM-4-4-3

4-15

Figure 4-5. Hover ceiling out of ground effect (Sheet 1 of 8)

••

•

•

••212VFR-FM-4-5-1

FAA APPROVED

SKID HEIGHT 60 FTHEATER OFFO· TO 52·C

00(3629) (4082) (4536) (4989) (5443)

GW - LB(KG)

14 000 FT H LIMIT

OAT - °C

.------ ' D ~

Zb T/ \ ~V MAXIMUM ~W LIMIT

,C~ \ 'f\\ OATI

+~J /1/\ I,-HOT DAY~~~l\ V 30jCUMIT

~V OT020·C->---

'OvA'

/ ~1/ 1\ f:\

\ \'\'- "-/1" /

\

~\'b~\

LL W \ , ~\'-j !7 '~

[71 '\,#/ I~J\1/ I [7 /1 '1'\

/ ~"/~~ I ~.

/ h~1 IJ \/ ""c5

Wl7 V

f7 [7 11.~00_(5080)

10 20 30 40 60 8000 9000 10,000 11.000 12.0

HOVER CEILINGOUT OF GROUND EFFECT

TAKEOFF POWERENG RPM 100% (N2)GENERATOR 150 AMPS EACH

BHT-212VFR-FM-1

4-16

212VFR-FM-4-5-2


-60 -50 -40 -30 -20 -10 0 8000 9000 10.000 11.000 12.000OAT - °C (3629) (40821 (45361 (4989) (5443)

GW - LB (KG)

SKID HEIGHT 60 FTHEATER OFF

O· TO-54·C

BHT-212VFR-FM-1

14 000 FT H LIMIT.- ' D ------.~~~I/ J/V '\ \¥ - MAXIMUM GW LIMIT

/ \\1/ -& / \ \ OAT'->-----,,\).':/ I

/'/ ~ 17 \\ k:: - 50·C-<iOTO_

1/ ",,:/ [7 ~ O·C

I/' 1/ \:r\/ ~7 / ~

1/ ~ / \1/ ~/ /

1/ ro; 1/~

fI 1/ 1/ i \

/ ~/ / \/

j / \1/ I&~ /

I I>' / 1/1\

1/ I~~II

/ J; II1/

/ 0/1/ 1/

/ 11.200_7 7 (~08~)



FAA APPROVED

••

••

•

•

4·17

212VFR-FM-4-5-3


o 10 20 30 40 50 8000 9000 10,000 11.000 12.000OAT - °C (3629) (4082) (4536) (4989) (5443)

GW - LB(KG)

•

••

•••

FAA APPROVED

SKID HEIGHT 60 FTHEATER ONO· TO 20·C

M


or- 14, 00 FT HO LI IT-

;/ ~V~MAXIMUIv)GW LIMIT

~/ \ o..h~~

~ /'1-20·C

1 ~v- OTO 10·C

~ ~7 ~

-~/ I'\

~~1\\>"'/

1/ \

W \\

~~I /

~ 1\[7

I-~&!/

11,00_

(~0~01)


BHT-212VFR-FM-1

4-18

212VFR-FM-4-5-4


-60 -50 ·40 ·30 -20 -10 0 SOOO 9000 10.000 11.000 12.000OAT - °C (3629) (4OS2) (4536) (49S9) (5443)

GW - LB(KG)

SKID HEIGHT 60 FTHEATER ON

O· TO-54·C

BHT-212VFR-FM-1

14000FTH LIMITr- . D ~

>-J&I/ II \ .---MAXIMUM GY' L1~.1IT

~:z-~ / / \\IOAt-1--

/ \ \.>- I--- 1).:'/ , 5Q:G_f--":/ f7~ / V-40TOOOC

,~,/

II [7 \'(1/ 1/ 1/ ~

/ ~I 7 ~1/ ~ / \

1/ ~III

/

1/ q,"j 1/ 1\17 7 f7 \

/ ~I / \f7 :;( / \[7~ 17

/

7 17-I."1/ 1'< 1/~/;...~

I ~/ 17r7 / q--j

1/ 11.200 _/ / (5PSOII


TAKEOFF POWERENG RPM 100% IN2)GENERATOR 150 AMPS EACH

FAA APPROVED

••

•

•

•

•

4·19

Figure 4·5. Hover ceiling out of ground effect (Sheet 5 of 8)


•

••

••

•FAA APPROVED

212VFR-FM-4-5-5

SKID HEIGHT 60 FTHEATER OFFO· TO 52·C

8000 9000 10,000 11,00012,000(3629) (4082) (4536) (49~9) (5443)

GW - LB(KG)

14 000 FT H LIMITr-- • D - OAT

~ ~ \\\ \\ I

\ ~ ooe

~ , ,\ \\ ~=:;= 10"e

-/( 20~e

/\ \\ ~r 30°CHOT ,

-~V ~

_ DAY-.l\ \\.\LIMIT

/ \ \\.\/ / \ \~ \ I~"

~~/, \ \ \\/

~/

\ \~o ~- / 0

~~ /', \ [\-

/ / \ \\\

/

~/1 \'l\~ ~

- I ~0\~</ /- ) t\\~ ~v/-A / \"\

/ VV /#

/ \/ \

\\

a 10 20 30 40 50OAT - DC

MAXIMUM CONTINUOUS POWERENG RPM 100% (N2)GENERATOR 150 AMPS EACH

BHT-212VFR-FM-1

4-20


SKID HEIGHT 60 FTHEATER OFF

O· TO-54·C

BHT-212VFR-FM-1

212VFR-FM-4-5-6

14000FTH LMr- . D I IT.O~TLt. )/ / ~

f- '# #;/10·

/ I ~ 20TO-40·C'I· , I

I \( .-- OAND-50·C--/ I~/ /f- f---" MAXIMUM

/ ~V GW \

V ,y V LIMIT \I/I~V \

/ 1/ \OVV Ir /

1/ I~ /

/ V / \/

/~ / \/ / \'/

!/ ] / \/ ~~ /

/ ::;(/ // /~~i/

/ ~ / \/ / ~/ \

/ 1#L \/! / ,tV \

-60 -50 -40 -30 -20 -10 08000 9000 10.000 11.000 12,000OAT - °C (3629) (40821 (45361 (49891 (5443)

GW - LB(KG)



FAA APPROVED

•••

••

•

4-21


•

•

•

••

•

FAA APPROVED

SKID HEIGHT 60 FTHEATER ON0° TO 20°C

212VFR-FM-4-5·7

8000 9000 10.000 11,000 12.000(3629) (4082) (4536) (49891 (5443)

GW - LB(KGI


f 14,000 FT HD LIMIT...

VI 1\ l\ OATI

&0/ \ \\~ O°CJ"-lO°·C

-Yf r\ t>:I---' 200C

~~ 'V\ J'0'"',(

/1 1\\\/ l

-~1

~#7 1\1---1>0-',(

VI \

~\\

x-~ \>---1 /~

[71 1\

I---~ \\

~1//l>o':{ \

. -o 10 20 30 40 50OAT - °C

MAXIMUM CONTINUOUS POWERENG RPM 100% IN2)GENERATOR 150 AMPS EACH

BHT-212VFR-FM-1

4-22


-60-50-40-30-20-10 08000 9000 10.00011.00012.000OAT - °C (4082) (4082) (4536) (4989) (5443)

212VFR-FM-4-5-8

BHT-212VFR-FM-1

SKID HEIGHT 60 FTHEATER ON

O' TO -54'C

OAT

GW -lBIKG)

'4 000 FT H LIMIT~. D -

~#V / / ~ V-f-- f-O°C t-~L~ 1Q°C

/ ~t:=V-f--20 ~ -40°Cf--50'C_,--

~ orS) / ~V- - ....~'

~/ ~/ /

/ ....y / \'/If// \

/ / \....0:'/

/ /f // ~/ /

/ ~ / 1\/1 / \

/ ~ / \A' / \Vk / \

/ lJi /

/ /'<~ / ;\

/ ~/~ / \/

/ ~'v/\

/ Ii ~/ / '\: \


MAXIMUM CONTINUOUS POWERENG RPM 100% IN21GENERATOR 150 AMPS EACH

FAA APPROVED

•••

•••

4-23


CRITICAL RELATIVE90 0 WIND AZIMUTHS

40 0 TO 135 0

212VFR·FM-4-6

•••

••

Figure 4-6. Critical relative wind azimuths for hover flight

4-24

•

REFER TO VTOCS CHART FOR TAKEOFF SP!:ED

FF

INITIATED FROM 4 FT SKID HEIGHTHEATER ON OR OFF


BHT-212VFR-FM-1

14 000 FT H LIMIT

TAKEOFF DISTANCEOVER 50 FT (15.2ml OBSTACLE

1 D

~9~~.x /v /y\ I IHO~ DA~ I /j rMAXIMUM

~y V vllo- TEMPERATURE LIMIT ~~HD

FORTAKEOoCO

~~V/ /,~~V,O~o~/ /\ :~OO// \/ / roO 00/ / \ $11 V

~// ;;.;&/ V

!t(~&/ /' /~ 'V

V /} V~% V ~ Ir.J 0 .$Jco::!:!!? /

[A-y /V~~ I f:l8&0~& 0 ry

/ / / I o 0' -'Q:) - -

HOVER POWER + 15% TOROUEENG RPM 100% IN21GENERATOR 150 AMPS

FAA APPROVED

••

•

•

•-60 -40 -20 0 20 40 60

OAT - °C200(61)

400 600 800 1000(122) (183) (244) (305)

TAKEOFF DISTANCE - FT (M)

1200(366)

•212VFR-FM-4-7

Figure 4-7. Takeoff distance over a 50 foot (15.2 meter) obstacle

4-25


•TWIN ENGINE TAKEOFF CLiMBOUT SPEED - KIAS

GW-LB IKG)

HD - FT* 7000 8000 9000 1q,OOO 10,500 11,000 11,200131751 136291 140821 145361 147631 149891 150801

0 30 30 30 35 38 40 40

1000 30 30 30 35 38 40 40

2000 30 30 30 35 38 40 40

3000 30 30 30 36 38 40 42

4000 30 30 32 36 40 42 42

5000 30 30 32 38 40 42 -6000 30 30 34 38 42 - -7000 30 30 34 40 42 - -8000 30 30 34 40 - - -9000 30 30 36 - - - -

10,000 30 32 36 - - - -11,000 30 32 38 - - - -12,000 30 34 38 - - - -13,000 30 34 - - - - -14,000 30 36 - - - - -

" Refer to Density Altitude Chart.

212VFR-FM-4-8

Figure 4-8. Twin engine takeoff climbout speed

4-26

••

•••

•FAA APPROVED

TAKEOFF POWERENG RPM 100% IN21GENERATOR 150 AMPS

TWIN ENGINE RATE OF CLIMBGW 7000 LB (3175 KG)

BHT-212VFR-FM-1

58KIASHEATER OFF

~"'''~ ,-t-j,..=- -50'C

\ I'\. '" '\ V-=- -4~;g. C

1\ '" ,,\,V,/ -20'C-I\. ~ I

\ i\. ~,,~V ~-10'C

~ '\ \. ~,

\~ '\

*l\.\ ~ '\~ "\1\

OAT'~ \ \\~LIMIT

\ \,f\. K~~1\\\ 1\1\ \

\~...: f\1\"

1\ \ \

\ 1\\r\PQ.j

1\ C'

\ 1\\ \

-~.\ C'

WITH ALL DOORS OPEN OR REMOVED, RATE OFCLIMB WILL DECREASE 200 FT/MIN• 20,000

• 18,000

16,000

14,000

12,000

-'enI 10,000co.

::t:

8.000

6,000

• 4,000

2,000

• 0

•o 400 800 1,200 1.600 2,000 2,400

RATE OF CLIMB - FT/MIN

2,800 3,200

212VFR-FM·4-9-1

Figure "4-9. Twin engine rate of climb (Sheet 1 of 30)

Rev. 2 4·27

~~ " " ~ OAT +-~ -50'C

'\ t'-.. " "'- ~-40'C

r--.. -30'C

F\ " ~. ~-20'C -

OAT V "LIMIT - >---- C'

r\ " V,," '\%.I\.

" ~I'\ '\ \I\."\

~" 1"- '\ '\~\ \ \~- \ \ \ '\

r\ 1\ 1\ 1\\ \ \

\ 1\ \\

1\ \\

1\\

WITH ALL DOORS OPEN OR REMOVED, RATE OFCLIMB WILL DECREASE 200 FT/MIN

BHT·212VFR·FM·1

TAKEOFF POWERENG RPM 100% IN2lGENERATOR 150 AMPS

20,000

18,000

16,000

14,000

12,000

...JenI 10,000Co::c

8,000

6.000

4,000

2,000

0

o 400

TWIN ENGINE RATE OF CLIMBGW 7000 LB 13175 KGl

800 1,200 1,600 2,000 2,400


FAA APPROVED

58KIASHEATER ON

2,800 3,200

212VFR-FM-4-9-2

•••

•••Figure 4-9. Twin engine rate of climb (Sheet 2 of 30)

4-28 Rev. 2

•FAA APPROVED

TAKEOFF POWERENG RPM 100'/, IN21GENERATOR 150 AMPS


BHT-212VFR-FM-1

58KIASHEATER OFF

"~ "" .................. ~~

"\0-- "" r-.........~~I

'\~ .........

"""~~5~!C - -

I',. / ~ ·40·C

'\ "" '" "\~ '/;·30·C -

i'... ~ - -20'C- .IO·C

."'- "- "'0." "<K-

~ "C'

",~~'" ~

\-" i'..."o~ '\~\ "" i\. \. \\~

\ I"" \. \\ \\\ ""0, '\ \ \\

1\'\. '\. \ \'\ " \ \\

OAT V V \ '\"0.\ \LIMIT1-

\ '\ \~ \ \

\' \. v. \

\ o.C'

\ '\\\t"

WITH ALL DOORS OPEN OR REMOVED. RATE OFCLIMB WILL DECREASE 200 FT/MIN• 20,000

• 18,000

16,000

14,000

12,000

....ICIl

I 10,000Co

::I:

8,000

6,000

• 4,000

2,000

• 0

•o 400 800 1,200 1,600 2,000 2,400


2.800 3,200

212VFR-FM·4·9-3

Figure 4-9. Twin engine rate of climb (Sheet 3 of 30)

Rev. 2 4-29

~ '" "" '" ,"""-~ I OATl/-- -SO·C

I'\:: "'- "- ,,~V -40·C

"v-:- -30·C

OAT~ "- "- "'-"'-~ ~lIMIT~

'\. "'- '" 1Zc-"~"'- "" ~c- ~ '"","" ~1J:' r'\. f\- '\.\

"\.1'( "- '\ \ .\"0· I'\. '\ \ \ 1\~

f\- "'- '\ \ 1\''\

\ \ f\\ \ \

1'\ \ \1\ 1\

\

\


BHT-212VFR-FM-1

TAKEOFF POWERENG RPM 100'10 IN21GENERATOR 150 AMPS

20,000

18,000

16,000

14,000

12,000

....Il/l

I 10,000Co

::t:

8,000

6,000

4,000

2,000

0

o 400

TWIN ENGINE RATE OF CLIMBGW 8000 LB (3629 KGI

800 1,200 1,600 2,000 2,400

RA TE OF CLIMB - FT/MIN

FAA APPROVED

58KIASHEATER ON

2,800 3,200

212VFR-FM-4-9-4

•••


4·30 Rev. 2

•FAA APPROVED

TAKEOFF POWERENG RPM 100'}'. (N21GENERATOR 150 AMPS


BHT-212VFR-FM-1

58KIASHEATER OFF

................. ~l'::~ i'..

.................. '" ..........

r--....'"~~I'--, '" ..........

r--.... ~~~"-"- .....""- "'" i'.. ~~~~ OAT

'" '" ~ "'-,~~ ~-50'C

~ ""'- / /"--40'C

" "'" "- ""~~-30'C

~ '"~-20'C...... /--- ·10·C

'\['...... .....~ ","""'\ ""'- "'- ~c:~ ~

'\ '" "" "- "\,"

"0.'\\\-. "i'Z

\

~ ~"\\

OAT -LIMIT~ '" "'\ ~c. \

\ \~ \\'~\\

\ \\M'"


• 18,000

16,000

14,000

12,000

...JenI 10,000Q.:I:

8,000

6,000

• 4,000

2,000

• 0

•o 400 800 1,200 1,600 2,000 2,400


2,800 3,200

212VFR-FM·4·9·5


Rev. 2 4-31

BHT-212VFR-FM-1


TAKEOFF POWERENG RPM 100% (N21GENERATOR 150 AMPS

" "-i'...R::r0

""" '""""~~ "-

I OATr-... -SO'C

I'-,""'"

.......~~

-40'C

"" ~~-30'C

'"..........

""'"....... ".!:.~~i'...

I'.. '".........,R~~~

.......... ""C'

~~~"'- I

"'- ~" i'...... I" '\~~o.""- ~ "\\\~

'" "~ '\. \\ .\

'" "' \ S'" \

~ '\ \ \'"\ \ '\

\ \\

\

•••

•••

212VFR-FM-4-9-&

58 KIASHEATER ON

FAA APPROVED

800 1,200 1.600 2,000 2,400


400

WITH ALL DOORS OPEN OR REMOVED. RATE OFCLIMB WILL DECREASE 200 FT/MIN

o

20,000

18.000

16,000

14,000

12,000

-'Ul

I 10,000Co:z:

8,000

6,000

4.000

2,000

0


4-32 Rev. 2

•.'

FAA APPROVED


TWIN ENGINE RATE OF CLIMBGW 10,000 LB 14536 KG)

BHT-212VFR-FM-1

58KIASHEATER OFF


I"-: .......... I, ..........~ I I......... ""-~

OAT

......... "- ~f--- -SO'C

........... ""-~="~f--- .40·Cf--- ·30·C

......... v:::f--- ·20·C

"'-.... ""- .......

"Q~ f--- ·IO·C

....... "i'-.. "" '<Y'........~~t'---. ", ..........

....... ............. '"~~........ ........~~ ~."""" 1"-"~"-

"- "" "'-CO

"- \'\. ,-"O~

" "- CO

'" \~

'\~ ~ '" \\~~I "- "'- ,\\"'0.\" \.

OAT~

" \LIMIT

"- \\~. "-\/,$.

\c>

\\.


18,000

• 16,000

14,000

12,000

..JenI 10,000...

::t:

8,000

6,000

• 4,000

2,000

• 0

•o 400 800 1,200 1,600 2,000 2,400


2,800 3,200

212VFR-FM-4·Q-7

Rev. 2 4-33

Figure 4·9. Twin engine rate of climb (Sheet 8 of 30)

~ I'.....

""l":~ IOAT

f'-... .......~~t--.

·SO·C

I'.... / ~.4O"C

"" ~t': ~.30·C

I'-... ~ I'v"-., ""

......... "~~.......

"'"........

r--... -...... ·..,o.~~........ I C'

"'"-......

r-..... "'" ~""~~

""'" "'" ~C' '" '"~"" ~;t-....... "\.'\~"'..1 "',,- '" \r\

~ I\. '\.~ \ \1\

1"'- \1\1\ 1\

r\

1\

WITH All DOORS OPEN OR REMOVED, RATE OFCLIMB Will DECREASE 200 FT/MIN

BHT·212VFR·FM·1


20,000

18,000

16,000

14,000

12,000

....enI 10,000Co

::r::

8,000

6,000

4,000

2,000

0

o 400

TWIN ENGINE RATE OF CLIMBGW 10,000 lB (4536 KGI

800 1,200 1,600 2,000 2,400


FAA APPROVED

58 KIASHEATER ON

2,800 3,200

212YFR-FM-4-9-8

•••

•••

4·34 Rev. 2

•FAA APPROVED


BHT-212VFR-FM-1

TWIN ENGINE RATE OF CLIMBGW 11,200 LB (5080 KGI

58KIASHEATER OFF

WITH ALL DOORS OPEN OR REMOVED, RATE OFCLIMB WILL DEC REASE 200 FT/MIN

I"'--I--I"'--

I----.-.I--I----.--.r--r--r- I--...--I-- --. r-. r----. r- r- r-r--I-- -.r- r-. .............. r-°"r- r-. r- .......... 1'.:....:50·

CI-- --...r- -..............

....................... .......... .~-- r--. ....... r-....~'-I-- --r-. ...........

.............. ............... ~.........-- r-.......... I C

r- ........I-- r-- ............... ~r- r- .............. r-.......

:::::::-...........r- --r-.

.......... ............... 'Rto- r-...............

........::r-- r-- ..................... ~t--.. ..............

.........r--........

.......r-... ............... ~........ ........................ ..........

...............-......... ,I

I"...... ~·c

~ :::-. r--....... I ..........Jo'

......................... r-.....- ~~ ~~.cy "- '"OAT'~

'\ILIMIT

~

• 18,000

• 16,000

14,000

12,000

.....en 10,000IQ.

::E:

8,000

6.000

• 4,000

2,000

• 0

•o 200 400 600 800 1,000 1,200 1,400


212VFR·FM·4·&·&


Rev. 2 4-35

f---..

t- o;;;;;;I'"--I-..- I-..-

~~ t- r--.r--. ----I'"-- .............r--. ......................

r-......Ioo-I--. .............r--.t'-- ..........r--. ............. r-:::r--.~100- ...... I-.... -S'o·c-r-- ............r-.. ............. r.......

-...;;;:~~r--. ..... -Jo· r---.....

l"- I'"-- .............~ ..........r-- ...... t-.... t-.... ~j'... r-.....

I"- .......... I'"--......

r-..............~

r--.....r-- t........ f-..... r---.....r--.I'"-- ............

r-....... ~~I t'-....I--. r-.....r-;;:::

r-....... ~..........

r--.....~c ............ .......

....... "'-.r--....... t--...

........

r-.......


BHT-212VFR-FM-1


18,000

16.000

14,000

12,000

-' 10,000(/)

I...::I:

8,000

6,000

4,000

2,000

0

o 200

FAA APPROVED

TWIN ENGINE RATE OF CLIMBGW 11,200 LB 15080 KGI

58KIASHEATER ON

400 600 800 1,000 1,200 1,400


212VFR-FM-4-9-10

•••


4-36 Rev. 2

•FAA APPROVED

TWIN ENGINE RATE OF CLIMBGW 7000 LB 13175 KGI

MAXIMUM CONTINUOUS POWERENG RPM 100% IN21GENERATOR 150 AMPS

BHT-212VFR·FM·1

58 KIASHEATER OFF

~ '" " "- r'\.~~ I I ~5~!C-r-...

\"" '" " "- 1'\.~/I.40·C

r-...

\ '\. I"\. '\. "- ~:{\

r\. I\- '\ '\ .,~'\'\o.

\- "- ~ '" "\'\I\.\ l'" '\ \. ~'"1\ f'\ '\ '\~" I\.

\ " ~ \ "/' \ ~c. '\OAT /

LIMIT \,. ~ \

\ '\~ \I'\c.

\ I\. \

\ '\

~\

\1\ '\1\ \ \

"0.

\ '\\ \\ \KO"

WITH ALL DOORS OPEN OR REMOVED. RATE OFCLIMB WILL DECREASE 200 FT/MIN• 20,000

• 18,000

16.000

14,000

12,000

-'Ul

I 10,000Co

::E:

8,000

6,000

• 4.000

2,000

• 0

•o 400 800 1,200 1.600 2,000 2,400


2,800

212VFR-FM-4-9-11


Rev. 2 4-37

BHT-212VFR-FM-1


MAXIMUM CONTINUOUS POWERENG RPM 100% (N21GENERATOR 150 AMPS

f'.:.: '-.", .......r-:::::-i'-.... i'-.. "'-

r--....... '-.", ....... i'-.. "::::~........~

......., .......~ "'" '"~~.......

........

"".......... .........

....... ~ ~~k·....... oro.~ ""

,"" ................. "-~

~ .................

""........

......... "'" ~~~ "-........ o.

""""............. ............. r.......... "";0;\ \

""........

"" "'".........

r-.... ~.~ \1'...

r"-. ~ 1'r-.... ~I::Z1\~ ............ 0 K 1"\

~1'... '" ~" f'-~

OAT l\." "'- I"~~"o.

LIMIT~ ~ K\ "'~o. ~~ K\ ",I '"\ '\"'0.

N'1\ \

\~~

•••

•••

212VFR·FM·4-9-12

B3 KIASHEATER OFF

FAA APPROVED

2,800800 1,200 1,600 2,000 2,400


400


o

20,000

18,000

16,000

14,000

12,000

...JenI 10,000Cl.•

8,000

6,000

4,000

2,000

0


4-38 Rev. 2

I--I----~~----l____J.____J.--+__+__+__+_\~>l +\-+++~~ \.

•••

FAA APPROVED

TWIN ENGINE RATE OF CLIMBGW 7000 LB 13175 KG)

MAXIMUM CONTINUOUS POWERENG RPM 100% IN2)GENERATOR 150 AMPS


20,000

18,000

16,000

14,000

12,000

..J1Il

I 10,000Co::r::

8,000

BHT-212VFR-FM-1

58 KIASHEATER ON

•\.

\6.000

4,000

2,000


••

oo 400 800 1,200 1,600 2,000 2,400


2,800

212VFR·FM-4·9·13

Rev. 2 4-39


f".. ..................~ r--...I-... .....

r-........ ............ ""I'-.......I'.:~'" ....... i'..... ....... '-... """~~I'..... r-..... I-...

r"': I-...............

I-..............

I-... ~ "- I'::~.~.i'-.- '" "'- i'.-. .......

t'..... ~~....... '-... ........... ...........

"" "'~'\"r--.. t--.. I-...

~ ~ ~ "",- ~:\1"-r"-.. "- ~ ~.['\, r\

"'" "'" '" Kr\'I'.- 'i'.. "{o r\

'" ,,-1'\

~ K '\

"'~o. f\.K

t'\.


BHT-212VFR-FM-1

•••

••

•

212VFR-FM-4·Q·14

2,800

FAA APPROVED

83 KIASHEATER OR WINTERIZATION KIT ON

800 1,200 1,600 2,000 2,400


TWIN ENGINE RATE OF CLIMBGW 7000 LB 13175 KG}

400o

20,000

18,000

16,000

14,000

12,000

...Ul

I 10,000...:z:

8,000

6,000

4,000

2,000

0


4-40 Rev. 2

•FAA APPROVED


MAXIMUM CONTINUOUS POWERENG RPM 100% (N21GENERATOR 150 AMPS

BHT-212VFR-FM-1

58 K1ASHEATER OFF

~ I"-. '"~.........

1'-...........~ 1 OAT-50·C

0 ......i'... 1""- "- ",.'~/I.40·C

'\ "- ~ '" " ~~I'-.. '"\ ...... f", " "~o~ f\.l'.. '"I~ " "- " " 1\.\l"\. ,,"of,.

to l"\. " ~"'\,

o.

\ "- I\. '\ '\ '\

~1~rT ----../1'>- '\. ~f'\1'\

\

'" \

I~ fZe. '\ '\\l'\ r-... \1\ ul \ \

'e"\ \ i\

\ \

~\ "0. \\ '\1 r-..

\1\'&(,


• 18,000

16,000

14,000

12,000

-'Ul

I 10,000a.:r

8,000

6,000

• 4,000

2,000

• 0

•o 400 800 1,200 1,600 2,000 2,400

RATE OF CLIMB - FT/MIN 212VFR·FM-4·9·15


Rev. 2 4-41

BHT-212VFR-FM-1



-........~ r'::"-

"'"""'I'-...

"""-......"I'-..

"'"""' """.......

i'-... I'"~~

""- """.......

i'.. ~ "'" ~°of,.......... ......... "'- .......r--...'

.~."""

....... ~ "'-..;"'- ~

.......

~..........

""'I~f'............ .......... ......... '"

........ '01.1:).

i'.. ~ ...... "'- " \."'- ~ ~

................. .......... ~~i'........... .........

""" '" ~o'\ \"'- f'..

'~ ~..........

i'.. "R.~'\~ '" ,,~> '\

'\ " " K'\ "'- ~", I"'-

i\ ........"'- I ' r--...

~ 'Ro)-:1'\..1 r"\

OAT~ "0.LIMIT 1\ i\"

\ \1\

~$o ••

•

••

•

212VFR-FM-4-9-16

83 KIASHEATER OFF

FAA APPROVED

800 1,200 1,600 2,000 2,400


400


o

20,000

18,000

16.000

14,000

12,000

-'CIl

I 10,000Q.

::J:

8.000

6.000

4,000

2,000

0


4-42 Rev. 2


FAA APPROVED



212VFR-FM-4-9-17

58 KIASHEATER ON

BHT-212VFR-FM-1

800 1,200 1,600 2,000 2,400


400


~ l'--. "'- ......I'.... '"1"'- '"~"\'" "1'... !'.. '" "'-.~

1\~ "- '" ""C' '.to.

C':-....~7 ·"o.~f'" ......

"'>-.. I'.. C' C' ~

OAr. =:!:7' "- I'"......

I"Z~." '\ \LIMIT !'.. I'..." I'" ~J:' '" .\J',.

~ "" 1Z I\- \1\ I \"- 'b. r-.. \

'\ C' '\ \~

"0" "- \

'" '\ \1\ \

\\\

o

20,000

18,000

16,000

14,000

12,000

.....CIl

I 10,000Q.

:J:

8,000

6.000

4,000

2,000

0

•

••

•

••

Rev. 2 4-43


BHT·212VFR-FM·1



••

•

••

•

212VFR·FM·4·9·18

83 KIASHEATER OR

WINTERIZATION KIT ON

FAA APPROVED

800 1,200 1,600 2,000 2,400


400

I'-.. ""-~ ........I"-- r-... I'-.. ......... :'---I'-.. """- .........

........ -.........: ""I'-........

"""-.........

"'"""" ~O"'1'0.........

i'r-... ......... "" I'-- .........................

.~

........ ........ C'

'" """-......... .......... "' "'o~I'-.. "- " I C'

......... ......... "" '"....... '~...'\ "r......... ........ r'\. C'

"" :-................

i'... '" ~'\

I............ '" '" ~"'.'\\

........i'..

.......... I'........~~C'

i'..........~ 1"'- "

'" 1{ '\

"'~o. "-"-"

o

20,000

18,000

16.000

14,000

12,000

-'III

I 10,000...•8,000

6,000

4,000

2,000

0


4·44 Rev. 2

•FAA APPROVED



BHT-212VFR-FM-1

58KIASHEATER OFF

r'--.. " I'... "f"~r'--.. "'"I'... '" "'" ~.~~ "" "- "" C'~ "4>.

I'\. "........

'" '" '" ~"tZ"I~ "'- 1'.. 1""- ~ 0\ [\

\ ~ '" ~ ""ob.' '\~1'..

'\"-, ",,, '\ f\I'\.

1\ 1""- " ~~ \'"-\

",

'obK \'1\,""'f \'

\" "Jo.\\ '\ K- 1\

f>\ ~I \OAT ~.LIMIT \ i\ \

~ \

\\~. \\ 1'\, '\

[\~c.


• 18,000

16,000

14,000

12,000

-'CIl

I 10,000co.:z:

8,000

6,000

• 4,000

2,000

• 0

•o 400 800 1,200 1,600 2,000 2,400

RATE OF CLIMB - FT/MIN 212VFR·FM·4·8·18


Rev. 2 4-45

BHT-212VFR-FM-1




••

••

•

•212VFR-FM-4-9-20

83 KIASHEATER OFF

FAA APPROVED

800 1,200 1,600 2.000 2,400

RATE OF CLIMB - FTIMIN

400

WITH ALL DOORS OPEN OR REMOVED, RATE OFCLIMB WILL DECREASE 200 FTIMIN

r-...r---.....t'r-.....r--.... r-.... '"""-i'-- '"

...................'" r-..... 0",)-I-.....

r--.... '" '".......... "'Kol'o..........

........... '" ",~:.,"r-...... ..........

r--...... ~o.

r-.... ....... "'~~ " \......., 1:) •

I'-- ~ r-..... ~~ '\

"" "" ............1:).

r-....... r-....... "" I "to-... .~. \.

" ""- I'-- "-I"\.o·I~ '"

............i'... ............" " \.

'"r'....... "" K '\.

'''''" ~c ~

1\ "'" I ............"'~ ~

\' "- "i\.J ~b.

OAT 'f'LIMIT 1\ \

\ 1\~CSo

o

20,000

18,000

16,000

14,000

12,000

....III)

I 10,000Q.

•8,000

6,000

4,000

2,000

0

4-46 Rev. 2

•FAA APPROVED


MAXIMUM CONTINUOUS POWERENG RPM 100% (N21GENERATOR 150 AMPS EACH

BHT-212VFR-FM-1

58 KIASHEATER ON

i"-- ......~r-....... r-....

'" I": ........

'" ~f\.i'...

~ ..........~ f"'.I~~......

........... " !"-. I~' .,~1'.. t'... C' 'dO.

I........... ~........

'" r-.... '" l"y~

'" ~ "' f\.. ~IC' ~t'... '.=!o.

" ~ "- C' 1\\f\. f\. r\.,,,

"' I\. "\ ~~ \

"' '" ~,,'\I\.."\ ~J'\'\'\.

'\ ~- '\'\"0.\

1'\-1\1\


• 18,000

16,000

14,000

12,000

.....til

I 10,000Q.::t:

8,000

6,000

• 4,000

2,000

• 0

•o 400 800 1,200 1,600 2,000 2,400

RATE OF CLIMB - FT/MIN 212VFR-FM-4-9-21


Rev. 2 4-47


BHT-212VFR-FM-1



•••

••

•

212VFR·FM-4·9·22

83KIASHEATER OR

WINTERIZATION KIT ON

FAA APPROVED

800 1.200 1,600 2,000 2,400


400

.....

.......... ..........~

I'-. .......I'-...~

I'-. .......~~ """..........

.........r--.....~ "- ,"-~.~.

r-...............

r--.... ~ """" ,.:.i'-- "- "'- ....... ""-.1 C' f\.

.......~ .......~ " "i'..~ i\.

"""1"'- "'- "r--.~ \.

"- "- ".~.

" " " I C' \.

"'- ~ 'N:" \..

"'- N"-b. '\."'-

r--. I'",,"0.~

"\

o

20,000

18,000

16,000

14,000

12,000

-'III

I 10,000c.:x:

8,000

6.000

4.000

2.000

0


4·48 Rev. 2

•"FAA APPROVED



BHT-212VFR·FM·1

58 KIASHEATER OFF

I--- "'""""-r--- r-- '---r-- --r- -...r-..-- l- I---. .........I--r-- r--...

r---...............

............ ............~,.- I--..

I"""---. .........,so'

I--r-- r---...... i'-..~-. I--.. I--..... I'--...·~o.

r-- ....,;,.,r- r--...... i'-..r---.-K ""--- r-. 1'--...:.10' i'-..r- -.;;;

r--..... 'N"S ........ "---. t'-- I--.. r--... ,~r- '"r---...... i'-.. I"~ '\.'-- f.....- f.....- 1--.....·,0. I'-..-r---...... -...t--.. ........... K f" ,\r--..... I---. t--.. "-

........... ......... t--.. r-..... ~ "l'-. I'('I'-..... t-.....

~~ r-..... ~ ......1'.-. i'-..t-.....

"r--....... r---.- J ~ ~~<o'

"'" ~ ~I'... r--...

....... " I

'"I'-.. No.

~~ ~i'..

~I:;T~ ~o. i'...

\1" ~

f\ "\\ '\\ ['\~c.


• 18,000

16,000

14,000

12,000

...enI 10,000Co:I:

8,000

6,000

• 4,000

2,000

• 0

•o 200 400 600 800 1.000 1,200


1,400 1,600

212YFR-FM-4-9-23


Rev. 2 4·49


WITH ALL DOORS OPEN OR REMOVED, RATE OFCLIMB WILL DECREASE 200 FT /MIN

TWIN ENGINE RATE OF CLIMBGW 10,000 LB (4536 KG)

••

•83 KIASHEATER OFF

FAA APPROVED

-_ -r-..r-... ........ r...........

--.....le.oOO

16,000

20,000

BHT·212VFR·FM-1

OAT LIMIT l\..'" "" I......:o~.-1--4-+---1

I\. t'Z

I----+_+---+--+---+_+---+------+----+I\.~d'~ f'...~"

14,000

12,000

....ICIl

I 10,000Co:I:

8,000

6,000

4,000

2,000

oo 200 400 600 800 1,000 1,200

RATE OF CLIMB - FT /MIN

1,400

212VFR·FM-4-9-24


4-50 Rev. 2

•FAA APPROVED



BHT-212VFR-FM-1

58KIASHEATER ON


r--..r--.. --I--.

r--..r-- --...::r-......~~ -SO.Ir--t-- -r--- --~t-- f'-...;.40·c

r--.r--- ........... I~ r--....r-- No·c t-....r--r--- r----..No·cI'--.. ""~r--... f.....-r--. ...........-- I .......r--.... ~ -....... :--.."'-r- -10·

r-...... ..... r-... iZ .....

"" ""'" 1'\.'\r--. ........... I'--..... ......-- ........... r--- r-... ~ ['....r....... ""'" "I\.

r-... ........

~ r--........f..... "" " "\r--....... "\.

..........r--....... 1 I'--..

""" """\

<0·-..;;~

'" "" "-i'..... "'".......

"""" ...........

""...........

"-

WITH ALL DOORS OPEN OR. REMOVED, RATE OFCLIMB WILL DEC REASE 200 FT/MIN• 20,000

• 18,000

16,000

14,000

12,000

....Il/l

I 10,000Co:x:

8,000

6,000

• 4,000

2,000

• 0

•o 200 400 600 800 1,000 1,200


1,400 1,600

212VFR-FM-4-Q-25

Rev. 2 4-51

•••

•••

212YFR-FM-4-Q-28

FAA APPROVED

1.400400 800 800 1,000 1,200


TWIN ENGINE RATE OF CLIMBGW 10,000 LB 14536 KG)

200

83 KIASHEATER OR

WINTERIZATlON KIT ON


r-- -r-r-- '-- r-...-r-- ---r-.. ----- --r-. -.......: .........:---....- -- 0..,-- ...;:::: "";;;:-- r-. ........... I'-.. ~c

-..... -..... -- "";;;:............

........~.~..... ..........-r- f' ............. .......... ~.1~:'-r-... r-. I'-...

r-- - cr- r-.. t--.. r-........ .........

i'x..f,'t--..r-. r- r-r-.. .........

r-........ ............. I'-.:.~r-. r-........

c-- ........... r-........,f.'r.......... ..........

r-........ ~r-.............-- ~t-...

N°'.z

o


20,000

18,000

16,000

14,000

12,000

....enI 10,000co.::I:

8,000

6.000

4,000

2,000

0


BHT·212VFR·FM-1

4·52 Rev. 2

•FAA APPROVED


MAXIMUM CONTINUOUS POWERENG RPM 100';' IN21GENERATOR 150 AMPS EACH

BHT·212VFR·FM·1

58 KIASHEATER OFF

.........

......................

............... ..........

.....r--....-- ~ .................. .......... °-4r

........... r--. .........~

...... .....1'-.....t-.. .............. ~I""".........

I'-..... .......... ~'C~ "....--r-- ......... ~'A "- \---- ......... .........~.~ '" \r-- ...............

............. ..........r-!!:.AI'\. \\-- r--- ..............

~"'" '" \\f.-.

~.............r-- .............

~o,l', '\. \\I~ .............r-. I~ '\. \\

.....~-- ~ '\. \\

".......... r-..... "- \\~ ~ \'

OAT~

'" "'"LIMIT

\ "~" '\


• 18,000

14,000

12,000

-' 10,000l/)

Ia.

::c8,000

6.000

• 4,000

2,000

• 0

•o 200 400 600 800 1,000 1,200 1,400


212VFR·FM-4·9·27


Rev. 2 4-53

BHT-212VFR-FM-1




18,000

16.000

r-.......r-....... r-... .........

14,000r--...... ~I--.. , -,fo-

.........r--...... ~ K

f-.. .....12,000

.............. ,,~ "-I--.. i"-. f\.........

r-............"'-~ "-I--.. ~

..... 10,000 .........~~ ""1Il

I""-. r-........ f....I .........

"'-~ r'::::Q. r-......:%: f....8,000 r--. ",-R'"............. f.... '0----- r--.....~ ""'-6.000 f.... -'0-

-- r-...... r--.... K "-........

".............. ~........."4,000

" "'- I "'"2,000 "" ~

- _ OAT ~~

.......... ,0

LI~IT I I

0 200 400 600 800 1,000 1,200



4-54 Rev. 2

FAA APPROVED

83 KIASHEATER OFF

212YFR-FM-4-9-28

•••

•••

•FAA APPROVED



BHT·212VFR-FM·1

58 KIASHEATER ON

-r-- """-r-..

.............. r-...... r-....r-- ............. I'-- ............

r--.....o..)"t--..

r- ........... r-...... t--.............. r-.... ~-I--

...........I'-- .......... ~C\t--..- """-r-...... ............ ~'\1\r-- r--....

r-......r- ............ ~~'\1\\- t--..--r-- ................."t~'\ 1\\

~ r--....I---- """- ..........

~"1\'-r-.. r-...... 't~'\1\\

I'--~!~1\'

'"1\\I\'

WITH ALL DOORS OPEN OR REMOVED, RATE OFCLIMB WILL DECREASE 200 FT/MIN•

le.oOO

• 16,000

14,000

12,000

.....enI 10,000...

::I:

8,000

6,000

• 4,000

2,000

• 0

•o 200 400 600 800 1,000 1,200 1,400


212VFR-FM-4-9-29


Rev. 2 4-55

BHT-212VFR-FM-1




FAA APPROVED

83KIASHEATER OR

WINTERIZATION KIT ON ••

-- .................- "-

....................... r----...

.......... ........0..,.............

............. I'...... ~............ r--..... r--...... ~,'"'c r-..r-- r---.....

.........I'...... '"~~c

f'-.. r-- .......I'--.., ""'"~~:"

r--- ....... C'

r--~ r--...... I'-..J,~

r-- .........................

~- .....r-- ...... ICr--.... N·

r-........ I'No.

"

18,000

16,000

14,000

12,000

....I 10,0000

I...:I;

8,000

6,000

4,000

2,000

0

o 200 400 600 800 1,000 1,200


212VFR-FM-4-9-30

•

•••

4·56 Rev. 2


SINGLE ENGINE RATE OF CLIMB - PT6T·3BGW 7000 LB (3175 KGI•

•

"FAA APPROVED

21/2 MINUTE OEI POWERENG RPM 97% (N2)GENERATOR 150 AMPS EACH

BHT-212VFR-FM-1

5BKIAS IHEATER OFF

INOPERATIVE ENGINE SECURED

WITH ALL DOORS OPEN OR REMOVED, RATEOF CLIMB WILL DECREASE 200 FT/MIN

Figure 4-10. Single engine rate of climb - PT6T-3B (Sheet 1 of 10)

\[\" " '\ '\~ OAT NOTE

\ '\ " '\ ~I\~- sqoc OPERATION ABOVE 71.B%I---+--+\J-:>.--J.-------I>.-'--->l-'\1---::..-'\1\,o-~+-40°C TORQUE REQUIRES THE

~~ ~I\ l.:L -30'OC 212·070·160·101 OR ·103, '\1" '\ 1 '\ ~ TORQUEMETER

1-----I--+-+-+--+--+--J\>-+I\~I\'bJ \ \ \ ,OAT L1MIT-~ \ \'I \ \ 1\ itS

o -400 0 400 800 1200 1600 2000

RATE OF CLIMB - FT/MIN 212VFR-FM·4-10·1

20.000

18.000

16.000

14.000

12.000

l-ll.

I 10.000a.

:l:

8000

6000

4000

2000

•

•••

Rev. 2 4-57

58KIASHEATER OFF


21/2 MINUTE OEI POWERENG RPM 97% (N21GENERATOR 150 AMPS EACH

.-BHT-212VFR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3BGW 8000 L8 (3629 KGI

WITH ALL DOORS OPEN OR REMOVED. RATEOF CLlM8 WILL DECREASE 200 FT/MIN

FAA APPROVED

-

Figure 4·10. Single engine rate of climb· PT6T·3B (Sheet 2 of 10)

\ '\ '\ ""-I\: ~ OAT NOTE"-\" '" ""

",,' f"\'~50°C OPERATION ABOVE 71.8%

--4d°c TORQUE REQUIRES THE

,,,,,- ""- 1"\ n -30°C 212-070-160-101 OR -103

l'\ TORQUEMETER.

\""

f'\ [\. '\ '\f\ f\

,'\ \'1'\ \

~ '\ " \ '\ \\1\

1\'\ \ \ 1\ [\\ .\ TORQUE

\1\ 1\ 1\ ~~~LIMITS-I

~71t% I------

1\ f\ ~\ \ C'(n'

\ \ \ \~ .\ 79.4%hI~ f\ l\ t:,,\ \ 1\\ ,\\ \ \'O~ \ 1\ ~"' rr\

\ \ I~ 1\ \!\ tb\ \ \1\ ° ... .

\ '\[,\ \ 1\to \1\ C' 1\

OAT LIMIT~ r\\ 1\ \ \\f(; 1\ 1\ ,

\1.\ \ \1>(; 1\ 1\

20.000

18.000

16.000

14.000

12.000

t1 10.000CL

::t:

8000

6000

4000

2000

o

4·58 Rev. 2

-800 -400 0 400 800 1200 1600


-

---

58KIASHEATER OFF


2 1/2 MINUTE OEI POWERENG RPM 97% (N21GENERATOR 150 AMPS EACH•

•

FAA APPROVED

SINGLE ENGINE RATE OF CLIMB - PT6T-3BGW 9000 LB (4OB2 KGI


BHT-212VFR-FM-1

I


,""~~ OAT NOTE

,'" "" """~'\

5~oC- OPERATION ABOVE 71.8%-40°C TORQUE REQUIRES THE

'" '" '" ~ <" 212-070-160-101 OR -103

,\ 1\ TORQUEMETER.

~

'" ~ '\. \\ "::J \w

~ [\ "\.\ 1\ ,\1\uw --I- '\ ,"\. \ \ 1\'::> [\.--'0 I\"\. \ \ 1\[\\ ,\ TORQUEenCD ' ',-~ \\ \ 1\ \\ ,~~ LIM'TFII:w

\ \ 1\\ ~\\ 7~.401=~ \0ll. \

1\ \ \ ~~\1\en ~::>0 \\ \ \ 'f~\l\\ 71.8% ,7::>z \1\ [\ 1\-0\ \ 1\\ \ /i=z0 1\ \ \ "\[\\ \~u::!: \ \ l\b~\ f\\At2::>::!: S\ \x

~~

::!:~ ~,,\ 1\ SfIw \(·i-¥.(:

z HI ..l \ ~Il:a OAT L1MIT-zw \,,, \ \ 1=z~ I\~'t 1\I-

\\"\ \

4000

2000

8000

6000

o-1200 -800 -400 0 400 800 1200 1600

RATE OF CLIMB - FT/MIN 212VFR·FM-4·10·3

14,000

16,000

18,000

20,000

12,000

t;:I 10,0000..

::I:

•

•••

Rev. 2 4-59

FAA APPROVEDBHT-212VFR-FM-1

2 1/2 MINUTE OEI POWERENG RPM 97% (N2)GENERATOR 150 AMPS

SINGLE ENGINE RATE OF CLIMB - PT6T-3BGW 10.000 LB (4536 KG)

58 K1ASHEATER OFF



•••

lLL.

IDo

J:

1200

212VFR·FM-4·10-4


4-60 Rev. 2

•

•••

Figure 4-10. Single engine rate of climb· PT6T-3B (Sheet 5 of 10)


WITH All DOORS OPEN OR REMOVED, RATE OFCLIMB Will DECREASE 200 FT/MIN

SINGLE ENGINE RATE OF CLIMB - PT6T-3BGW 11,200 lB (50BO KG)

212VFR-FM-4-10-5

800

BHT-212VFR-FM-1

58 KIAS IHEATER OFF


400o

NOTE

OPERATION ABOVE 71 B%TORQUE REQUIRES THE212-070-160-101 OR -103

OAT TORQUEMETER

~'\>--,--50°C

~ f--40°C'I'

~~30°C

",,"~\I\

=±~ ""1\\l\0 TORQUE

U~ITS -1\~d;~(J)z 1\

1 -6;! '\ \>'5: I\~ 71_8%,7------L _::> ~ "0! 'Zw \ \"f \\,\ /--L_f=~1 z----'

I~ I~ I\r1\ \ \' /IWOO_ zU(J)? \ \C3~c:l 1\ 1\ rf~ 79.4o/~7z::>«

-w~1J:

1\ \ '\ '"b\ \ 1\z-w_x~

-I~«O \ \ ~1\ 1\\ ~~:il-~CL

~<?

\f------

Ifo i\\' "'\ \ \

r--

0 I---OAT LIMIT r-\ \f \ \ ,

:::

\.:.

\-,

\

~~\ \ :=:

to-1200 -800 -400

2000

6000

4000

8000

16,000

20,000

18,000

14,000

12,000

I...I 10,000ll..

J:

2 1/2 MINUTE OEI POWERENG RPM 97% (N2)GENERATOR 150 AMPS

FAA APPROVED

•••

•••

Rev. 2 4-61


30 MINUTE OEI POWERENG RPM 97% (N21GENERATOR 150 AMPS

SINGLE ENGINE RATE OF CLIMB - PT6T·3BGW 7000 LB (3175 KG)

58 K1ASHEATER OFF



I.•

Figure 4-10. Single engine rate of climb· PT6T-3B (Sheet 6 of 10) •••

•

212VFR·FM-4-10-6RATE OF CLIMB - FT/MIN

~

"" "","" \. ~ OAT NOTE

~~1\ \\ io- -50°C e-

"\OPERAnON ABOVE 71.B%

~--40°C TORQUE REQUIRES THE

\ 1\ \ 1\\ 212·070·160·101 OR .103

1\ 1\ TORQUEMETER

\ \ \ ~~\

\ \ '\'\ I\~~l\ 1\ \ r\.~\~1\\ \ \ ~0\ r\~ TORQUE

~ - LIMITS-\ \ \ \r 1\\~ S71.8~·+°0 \ 1\"1\ 1\ 1\ Y: \\ \ '\00\ \ 1\ \ .~ 79.4%-

OAT UMIT \ f\ 1\ 1\ \ \ ~1\

\ \'be \ \ \ 1\ I\~

'\ 1\1\ i\ 1\\ \l ,~1\ .~. ",

'\ \'b\ '\ \ \ 0:":';

":..':";~;:::

\ t 1\ 1\ 1\:::.

1\ :l~~-

\\~ \ \ \ \ :...."'0,;...:,"

1\ \0(; 1\ 1\ 1\\ 1\ \ \ \ ":'::~::.~;;: :'~:;

I---

\ \ 1\ .~i.1\

~(; 1\ \ ...;:;

-400 0 400 800 1200 1600

2000

4000

o

6000

8000

14.000

20.000

12.000

16.000

18.000

t:I 10.000a.

::E:

4·62 Rev. 2

•

••

FAA APPROVED

30 MINUTE OEI POWERENG RPM 97% (N2)GENERATOR 150 AMPS

BHT-212VFR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3BGW 8000 L8 (3629 KG)

58 KIAS IHEATER OFF




212VFR-FM-4-10-7

400 800 1200 1600oRATE OF CLIMB - FT/MIN

-800 -400

~ '\ ."""",'"""~ OAT NOTE

~~ '\"" ~""~ -sdOc OPERATION ABOVE 71.B%

TORQUE REQUIRES THE

\ f\ 1\'" \~ -4d°c212-070-160-101 OR -103

'\ 1\ TORQUEMETER.

\ ,,'" '" '\ \ 1\\'\ \ \ '\ \ I\~~

1\\ '\ 1'\ \ I\~~'\ f\ f\ !\ \ ,°0\ ~ TORQUE

'\ \ \ ~~ I\~UMrrS-

1\ I

\ \ \ 1\ 0 \ \ 1\\1 7'j8% e---

°0~-e---

" '{\ \ I\~~ 7~.4%...,1\ 1\ ...1\\ \ ~(,\ 1\ f\\ '\

OAT lIMIT- f-\ 1\ 1\~1\ f\\ \ 1\~~\ \0\ \ r\ 1\\

1\ [\1\ \ \!\ 1\ ,

'\ ~0\ \ '\ \ , "tt.\1\ 1\ 1\ 1\ 1\ ~~[~~j~:;;

\~\ \ '\ \ I!;:;:::::;:

1\ \ 1\ 1\ 1\ ~!ti+'

\~ \ \ '\ \ j~~~!t:.~~~..$&:

0~0 \ 1\ 1\ III

2000

6000

8000

4000

10.000

12,000

18.000

20,000

14.000

16,000

lLL

III..

J:

•

•••

Rev. 2 4-63

BHT-212VFR-FM-l

30 MINUTE OEI POWERENG RPM 97% (N2)GENERATOR 150 AMPS

FAA APPROVED

SINGLE ENGINE RATE OF CLIMB - PT6T-3BGW 9000 LB (40B2 KG)

58 KIASHEATER OFF



•••

Figure 4·10. Single engine rate of climb - PT6T-3B (Sheet 8 of 10) •••

•

21 2VFR·FM-4· 10-8

800 1200 1600400oRATE OF CLIMB - FT/MIN

'"""~" ,,"" NOTE

'\ 1'\ 1'\ ,,'\2\ OAT OPERATION ABOVE 71 8%

r- TORQUE REQUIRES THE

~ '"~ '\ '\ '\ 212·070-160-101 OR -103

'\ ~-50~C TORQUEMETER.

z 1\ '\ '\\ \ ~ -400C:::;LLJ \ '\ \ \ \ 1\ r\uLLJ

\\ \ \ 1\ \ Rb~f\I-::J--'0 \\ \ \ \~1\\en \ '"borc« \ \ \ /~[\\~ TORQUEa: \ \LLJ

\ \ [\ \ \0\\ ~ L/MITS-:5:0a..

\ \ \ f o \ \ ~ 71.8%7en::J0 \\ \ \ ....\ \ \ , /::JZ

\ \ \r \ \ \ \\~~z0 OAT L1MIT-~ \bo \ \ \\ . -79.4%u~ \ \ '\ \ \ \::J~

~ \ \x ~ \°0 \ \«~ \\ '\ \ \ \LLJZ \ 'b<.9 \'"0 \ \ \z \ '\ \ \ \ rmLLJ

Z

~ \ \ \ 'ij,,:I- .~

1\0 \ \ \.....":::::"

~1200 -800 -400

2000

4000

6000

8000

12,000

10,000

18,000

14,000

16.000

20,000

I...IQ.

:I:

4-64 Rev.2

•

••

FAA APPROVED


BHT-212VFR-FM-l

SINGLE ENGINE RATE OF CLIMB - PT6T-3BGW 10,000 LB (4536 KG)

58 KIAS IHEATER OFF



Figure 4·10. Single engine rate of climb - PT6T-3B (Sheet 9 of 10)

212VFR-FM-4-10-9

800 1200400oRATE OF CLIMB - FT/MIN

I~~ I I NOTE

r~" ,""--OAT-

OPERATION ABOVE 718%I I-50°C_ TOROUE REQUIRES THE

J r--..~ " '\: I\-212-070-160-'01 OR -103

I I ITORQUEMETERI\- -40°CI--- z

" '" "::::;"\.I"\. 30°C

I--- W

~~

""'\ ",,\ !

'UUJ

I--- I-

~['\ '\1\ r\ i=> '\...JI--- 0

1\ 1\-\/$f)

~ ~ \"lDI--- <l:

" '\ '.J~f\\ex: ~ 1\ /\ TORQUEI--- UJ

~IMITS-I---:5: '\ '\ '\ '\ \ 0:\\f\0 ,-"SI-- Cl.(f) ~ \ \ \ ;\C;\ \ ,\\ 71_8%-=>I--- 0 1\ r\O 1\ \ \ I=> 1\ 1\ ~I--- ZI- \ 1\ \ ",\ \ 1\\,,\ IIz 1\I-- 0 \ \ \ \01\ 1\\ \U ~\794% t7

I-- ~

t-\ ~o \ \ 1\ ,\~OAT L1MIT- r\ /I--

\ \ .\ \ \ \'l1/X1\<l:

I-- ~

~\<A

\ \ 1\ \UJ rf01\I--- zC) 1\ \ ~\ \ \ 1\ 1\ \I---ZUJ

\ 1\0 \z 1\ 1\I--- ~$~ \ \ \ r\I-

°0 1\ 1\ \1\0o -1200 -800 -400

2000

4000

12,000

6000

14,000

8000

16,000

20,000

18,000

lLL

I 10,000~

:I:

•

•••

Rev. 2 4·65

FAA APPROVEDBHT-212VFR-FM-1


SINGLE ENGINE RATE OF CLIMB - PT6T-3BGW 11,200 LB (5080 KG)

58KIASHEATER OFF



•••

Figure 4-10. Single engine rate of climb - PT6T-3B (Sheet 10 of 10) •••

•

212VFR·FM·4·10·10

800

NOTE

OPERATION ABOVE 71.8%TORQUE REQUIRES THE212-070-160-101 OR -103

OAT TORQUEMETER.

'\~/

i--5'O°C......

40°CI~CIl :--30°C

f----- ::J '\Y\t\0f-----

::J [\.z \ "\

.'\1\~- z

'\ "\ \ 1\\Bel-

:2~ \ \ ~ '\~::J:::! 00 TORQUE- :2 UJ 0 L1rm!;-_U

\ \ ~ '\ :\XUJ 00- <{I-0'\; '\ '\\71.8%7:23 \ '\- UJO

\ \ \0\ '\\~ TZC/l-aJ

~~<{

\ \ ,\o~ 1\ i\\1UJ ffi < 79.4%7f----- ~ ~

r\0

\ II~O \ I\'"b 1\f----- I- c.. '--\ \ \f\ \ \ '--

1'\\ \b"-\ 1\ 1\ :~i,

l--

k 1\ '1\ '\ '\ .::OAT LIMIT

1\

to\ '\'\.:.

ii~l--

1\ .1\ '\1\ 1\ l--

~O\ \ \ :::.:~

o -1200 -800 -400 0 400


2000

6000

12,000

4000

8000

20,000

16,000

18,000

14,000

Iu..

1 10,000ll.

J:

4-66 Rev. 2

SINGLE ENGINE RATE OF CLIMB - PT6T-3GW 7000 LB 13175 KGI

••

FAA APPROVED

30 MINUTE POWERENG RPM 97% INZ)GENERATOR 150 AMPS EACH

BHT-212VFR-FM-1

58 KIAS ' IHEATER OFF


WITH ALL DOORS OPEN OR REMOVED. RATE'OF CLIMB WILL DECREASE ZOO FT/MIN

~ t'-... "-t--.. r--.. -....::~ OATI

"""- " "- '" r--..~SOOC

;

40°C

'" """ '" r--.. "'-~ -30°C

"'-.: I'.... ~"'- ~~ -20°C

~ "'-, "- ">o~I"" """-

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• 20.000

18.000

16.000

14.000

12.000

I-u. 10.000I~

I8000

6000

• 4000

2000

200 400 600 800 1000 1200 1400 IGOC 1800 2000•o-600 -400 -200 o


• Figure 4-11. Single engine rate of climb - PT6T-3 (Sheet 1 of 10)

Rev. 2 4-67

58 KIASHEATER OFF


30 MINUTE POWERENG RPM 97% (N21GENERATOR 150 AMPS EACH

BHT-212VFR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3GW 8000 LB (3629 KGI

WITH ALL DOORS OPEN OR REMOVED. RATEOF CLIMB WILL DECREASE 200 FT/MIN

FAA APPROVED

•I.•

Figure 4-11. Single engine rate of climb - PT6T-3 (Sheet 2 of 10) •••

~ r-... " '"I":~, I I I". t--... " '"

......., ~~ I i ! 1"'- '" t--... "" '" """~ , I O~T ! I~ t--... ......... '"

.......i'-.. ~ I, -50°C

~ f' t--... I"': ~~40°C

~-300C

"t'-.... .......t-.... ~ t--... ""~ ~-200C I

"......... t'-.... " I"'-. "I:'~ , !

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2000

4000

6000

8000

12,000

18,000

14,000

20,000

a-1000 -800 -600 -400 -200 a 200 400 600 800 1000 1200 1400 1600

RATE OF CLIMB - FT/MIN 212VFR.FM.4.11.2

16,000

~

LL

I 10,000<>.

J:

4-68 Rev. 2

.. ..

58 KIAS •HEATER OFF


30 MINUTE POWERENG RPM 97% (N2)GENERATOR 150 AMPS EACH

•••

FAA APPROVED

SINGLE ENGINE RATE OF CLIMB - PT6T-3GW 9000 LB I40B2 KG)

WITH ALL DOORS OPEN OR REMOVED. RATEOF CLIMB WILL DECREASE 200 FT/MIN

BHT-212VFR-FM-1

200 400 600 800 1000 1200o

r-... ""'-~t'~ I~ ""'- ........, r'::~ Ir......., ""'- "-." ~ """~ r--....

,i, I

/""- .......~ "-." '" .......1'-.~~

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""" ""- /' .-!.-40oC

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i """ I"-... ""-. "-." ""-. ~~-300Ci

/ r--.... ......... "" "- "-20°C

~ I

Lb=- rlvvlN ENblNJ I\. "" ""-. ......... ":/~ i

MAXIMUM CONTINUOUS "':-.. ......... '" ~"~- r-POWER ABSOLUTE C~ILI~G '\ t'-,. '" ~'\ '",

~

'\'" i'-. ~o I\. '" '"'" i

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\ "'-VO '\. , '\.)f "- '\ '\.. "-

0\ J "- '\.. "- '\\.~~ '\. '\ "-0

-1200 -1000 -800 -600 -400 -200

200

4000

6000

8000

12,000

14,000

16,000

18,000

20,000

f-...I 10,0000

I

•••

RATE OF CLIMB - FT IMIN212VFR·FM·4·'1-3

Figure 4-11. Single engine rate of climb - PT6T-3 (Sheet 3 of 10)

Rev. 2 4·69

BHT-212VFR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3GW 10,000 LB (4536 KGI

FAA APPROVED

•30 MINUTE POWERENG RPM 97% (N21GENERATOR 150 AMPS EACH

58 KIAS IHEATER OFF


WITH ALL DOORS OPEN OR REMOVED, RATEOF CLIMB WILL DECREASE 200 FT/MIN •

•••

•\ l"':

r--...:'"~ I

'" .........~~

t'-, r---.....I"t": t'--.t'-- t'--.. 1"- .......

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.......... "- ...... t'--. """~~-400C

~ "- )<'"/!,--30uC

\. '" ......... ......... "".......i'...~'"'" "" "- "'" "~~~"- , ........ I'-- ......~o~~"'-0

~ ~ ........ Oo~- '"~~1\.-

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" "- ~' ~"r\. t\.. i'\. ~'- TWIN ENGINE \ "- r(ool,,- r\. ~MAXIMUM CONTINUOUS0'--

POWER ABSOLU~E CEIILlN~ , r'\. '" ~ "'\ ~I\.OAT LIMIT-r..' ~if-';;; I\. '\ """\

~"0

''\ .. 1\ " ""r\.

1\ I~""T, """"\ r\:",0

\ 1\ \ I\. \ 1\~if \ I\. 1\ I\.

0

400

200

600

800

12,000

14,000

16,000

-1000 -800 -600 -400 -200 0 200 400 600 800 1000



20,000

18,000

...u..

I 10,0011.

:I:

4-70 Rev. 2

.. ..

Figure 4·11. Single engine rate of climb - PT6T-3 (Sheet 5 of 10)

30 MINUTE POWERENG RPM 97% IN21GENERATOR 150 AMPS EACH

212VFR·FM-4-11-5

BHT-212VFR-FM-1

400200

58 KIAS IHEATER OFF


·400 -200 0


-600·800

SINGLE ENGINE RATE OF CLIMB - PT6T-3GW 11,200 LB 15080 KGI

~, I I


.~I- T~N E~GINE I IMAXIMUM CONTINUOUSPOWER ABSOLUTE CEILING

1---,- OAT ~ '\. ....

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o.1,000

6.000

4,000

2,000

16,000

12,000

14,000

18,000

I- 10,000...ICl.

::c 8,000

FAA APPROVED

•••

•

••

Rev. 2 4-71

BHT-212VFR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T-3GW 7000 LB 13175 KGI

FAA APPROVED

•58 KIAS IHEATER OFF



WITH ALL DOORS OPEN OR REMOVED. RATEOF CLIMB WILL DECREASE 200 FTIMIN •

18000

16000

14000

12000

-1000 -800 -600 -400 -2.00 a 200 400 600

RATE OF CLIMB - FT /MIN

800 1000 1200 1400 1600

212VFR·FM-4-11-6

•

••


4-72 Rev. 2

•


••


SINGLE ENGINE RATE OF CLIMB - PT6T-3GW 8000 L8 (3629 KG)

58 KIAS IHEATER OFF


•WITH ALL DOORS OPEN OR REMOVED. RATE

OF CLlM8 WILL DECREASE 200 FT/MIN

Figure 4-11. Single engine rate of climb - PT6T-3(Sheet 7 of 10)

212VFR·FM·4-11-7

800, 1000 1200

~ 0; ~~ "" ~""" i I i I

i ~~ ""'-~ ""'- ~ ~ ..... IOAT

~-500C

, 1"- '" I"" I'--. '" ~ '"~y, r--4OoC I

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a I : ~~-1400-1200 -1000-800 -600 -400 -200 a 200 400 600


200

400

6000

8000

\8,000

10.000

12.000

14,000

16.000

20,000

I...I0.

:I:

•

••

Rev. 2 4-73

BHT-212VFR-FM-1

SINGLE ENGINE RATE OF CLIMB - PT6T·3GW 9000 LB 14OB2 KG)

FAA APPROVED

•MAXIMUM CONTINUOUS POWERENG RPM 97% (N21GENERATOR 150 AMPS EACH

58 KIAS IHEATER OFF •



•

212VFR-FM-4-11-8RATE OF CLIMB - FT/MIN •

•

"" ~ "'" F..: r":::OAT

I~ -....... I'---

~t::J ~-~ooC

r~ " I'--- i'-. ~-400Cfl' ~ r':::: i'-. r-.....<c~

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1\ 1"\ 1"'-i\\ 1\ ~

i I I \1'\00 \ 1\ '\

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-1800-1600-1400-1200-1000 -800 -600 -400 -200 0 200 400 600 800 1000

20,000

18,000

16,000

14.000

12.000I-u..

I 10.000l>.

:I:

8000

6000

4000

2000

Figure 4·11. Single engine rate of climb - PT6T-3 (Sheet 8 of 10) •4-74 Rev. 2

.. .

WITH AU DOORS OPEN OR REMOVED, RATEOF CLIMB WILL DECREASE 200 FT/MIN

MAXIMUM CONTINUOUS POWERENG RPM 97% (N2)GENERATOR 150 AMPS EACH•

•



58 K1AS IHEATER OFF



400 600

212VFR-FM-4-11-9

200

f'.-.2' I'...

f'.-. ""!'--, IOAT

i'-... ""........~~

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t'-- ......1'--. ........J'.... f"" C'--

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-1200 -1000 -800 -600 -400 -200 0


2000

6000

8000

16000

14000

12000

18000

20000

I 10000"-

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I...

•

•••

Rev. 2 4-75

Figure 4-11. Single engine rate of climb - PT6T-3 (Sheet 10 of 10) •••

•••

212VFR-FM-4-11-10

FAA APPROVED

400

58 KIASHEATER OFF




TWIN ENGINE\ M.C.P. ABSOLUTE CEILING

\""" r--....

......""'" 0",,,.......I'-... """- '''O'c

.........r--.... 1"""- ......~i'...

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\o-1,000 -800 ·600 -400 -200 0 200

RATE OF CLIMB - FTIMIN

18,000

16,000

14,000

I-LIJLIJu.

12,000ILIJC:::Il-i: 10,000-'4(

LIJa::::IUl 8,000UlLIJa:a.

6,000

4,000

2,000

MAXIMUM CONTINUOUS POWERENG RPM 97% (N21GENERATOR 150 AMPS EACH

BHT-212VFR-FM-1

I

4-76 Rev. 2

••

•FAA APPROVED

PILOT AIRSPEED SYSTEM CALIBRATION

CLIMBlEVEL FLIGHT

AUTOROTATIONSKID GEAR

lAS - ERROR : VCAl

BHT-212VFR-FM-1

V/

0- LEVEL FLIGHT

/d"

;{f "--AUTO

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l/II-0Z~

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60

• 40

20

• 0

•o 20 40 60 80 100 120

INDICATED AIRSPEED - KNOTS

140

212VFR-FM·4-12

Figure 4-12. Pilot airspeed system calibration

Rev. 2 4-77

BHT-212VFR-FM-1

COPILOT AIRSPEED SYSTEM CALIBRAnON

CLIMBlEVEL FLIGHT

AUTOROTATIONSKID GEAR

lAS - ERROR. yCAl

FAA APPROVED

••

LEVEL FLIGHT ------.. /

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0o 20 40 60 80 100 120

INDICATED AIRSPEED - KNOTS

140

212VFR·FM-4-13

•

•••

4-78 Rev. 2

Figure 4"13. Copilot airspeed system calibration

". .

••

FAA APPROVED

SINGLE ENGINE LANDING DISTANCEOVER 50 FT (15.2 Ml OBSTACLE

POWER AS REQUIREDENG RPM 97% (N21GENERATOR 150 AMPS


BHT-212VFR-FM-1

40KIAS •RATE OF DESCENT SOO FPMHARD SURFACED RUNWAY

Figure 4-14. Single engine landing distance over a 50 foot (15.2 meter) obstacle

200 400 600 800 1000(61) (122) (183) (244) (305)

LANDING DISTANCE - FT (M)212VFR-FM-4-14

14000 FT H LIMIT\. ' D

\ I;l\ /\ / If V HOT DAY L1M11 ",/ /

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/ / /1/; V-60 ·40 -20 0 20 40 60

OAT - °C

•

•

••

Rev. 2 4-79/4-80

••

MANUFACTURER'S DATA

Section 5

TABLE OF CONTENTS

BHT-212VFR-FM-l

•Subject

INTRODUCTION .EMPTY WEIGHT CENTER OF GRAViTy .GROSS WEIGHT CENTER OF GRAViTy .DOORS OPEN OR REMOVED ..COCKPIT AND CABIN LOADING .

CABIN DECK LOADING .INTERNAL CARGO LOADING TABLE .

BAGGAGE COMPARTMENT LOADING .BAGGAGE LOADING .BAGGAGE LOADING TABLE .

FUEL LOADING .COMPUTATION OF CG .SAMPLE LOADING PROBLEM .

Paragraph

5-1 .5-2 .5-3 .5-4 .5-5 .5-5-A .5·5·B .5-6 ..5-6-A .5-6-B .5·7 .5-7-A ..5-7-B ..

PageNumber

5-35·35-35-35-35-35-35-45-45-45-45-45·4

•••

LIST OF FIGURES

Title

Helicopter station diagram .

LIST OF TABLES

Title

Door weights and moments .Crew and passenger table of moments .Internal cargo loading .Baggage loading .Fuel loading .Fuel loading .

Figure PageNumber Number

5·1..... ...... 5-7

Table PageNumber Number

5·1........... 5-85-2........... 5-95-3 5·115-4........... 5-135·5........... 5-145-6........... 5-16

5-1/5-2

•••

•••

MANUFACTURER'S DATA

Section 5·

5-1. INTRODUCTIONThis section provides informationregarding helicopter center of gravity andcockpit and cabin loading. Loading tablefor pilot and passengers, cargo, and fuelare provided. A sample loading problem isprovided to aid in flight planning.

5-2. EMPTY WEIGHT CENTEROF GRAVITYWeight empty consists of basic helicopterwith required equipment, optionalequipment kits, transmission and gearboxoils, hydraulic fluid, unusable fuel,undrainable engine oil, and fixed ball~st.

Weigh empty CG shall be adjusted withinlimits of applicable Weight empty center ofgravity chart in BHT-212-MM.

5-3. GROSS WEIGHT CENTEROF GRAVITYIt shall be pilot responsibility to ensurehelicopter is properly loaded so entireflight is conducted within limits of GrossWeight Center of Gravity Chart In Section1. GW CG may be calculated fromhelicopter Actual Weight Record (historicalrecords) and loading tables In this sectionor in appropriate Flight ManualSupplements to assure safe loading.Locatlco,·,s of crew and passenger seats,baggage compartment, and fuel tanks areshown in helicopter station diagram (figure5-1).

5-4. DOORS OPEN ORREMOVEDOpening or removing doors results in CG::hanges. Door configuration shall besymmetrical for both sides of fuselage.

BHT-212VFR-FM-1

Door weights and moments table (table 51) lists weight and moment adjustmentswhich should be made in determining GWand CG when doors are opened orremoved.

5-5. COCKPIT AND CABINLOADINGA minimum crew weight of 170 pounds(77.1 kilograms) in cockpit is required.Except for two aft passenger seats, crewand passengers may be loaded in anysequence without exceeding GW CG limitsapproved for flight.

NOTE

Outboard facing seats should notbe occupied unless at least fourpassengers are seated in forwardand/or aft facing seats.

5-5-A. CABIN DECK LOADINGCabin deck cargo loading limit is 100pounds per square foot (0.048 kilogramsper square centimeter).

]WARNING ~

Helicopter CG shall be computedfor all cargo/baggageconfigurations before flight.

Refer to table 5-2 for personnel weightsand moments in English and Metric units.

5-5-B. INTERNAL CARGO LOADINGTABLEWeights at various arms and theirmoments are listed in 50 pound

5-3

BHT-212VFR-FM-1

5-4 Rev. 5 17 OCT 2011 ECCN EAR99

increments from 50 through 2000 pounds andin 25-kilogram increments from 25 through900 kilograms (Table 5-3).

5-6. BAGGAGE COMPARTMENTLOADING

Baggage compartment is accessible fromr igh t s ide o f ta i lboom and conta insapproximately 28 cubic feet o f space.Baggage compartment has a load limit of400 pounds (181 .4 kg) not to exceed100 pounds per square foot (0.048 kg/cm2).These are structural limitations only and donot infer that CG will remain within approvedlimits. When weight is loaded into baggagecompartment, indiscriminate crew, passenger,and fuel loading can no longer be assumed,and pilot must compute GW CG to ensureloading is within approved limits.

5-6-A. BAGGAGE LOADING

Loading of baggage compartment should befrom front to rear. Load shall be secured totie-down fittings if shifting of load in flightcould result in structural damage to baggagecompartment or in GW CG limits beingexceeded. If baggage is not secured, CG shallbe computed with load in most adverseposition.

5-6-B. BAGGAGE LOADING TABLE

Weights at various arms and their momentsare listed in 20-pound increments, from 20through 400 pounds, and in 10-kilogramincrements, from 10 through 181.4 kilograms(Table 5-4).

5-7. FUEL LOADING

At the beginning of any flight with full fuel onboard, helicopter CG will move forward due tothe fact that the CG of fuel on board movesforward as it is consumed. This occursbecause fuel is consumed from rear (upper)fue l ce l ls f i rs t . Max imum forward CGcondition of fuel on board occurs when72.6 U.S . gal lons (274.8 L ) remain for

helicopters S/N prior to 35049 and at 78.5 U.S.gallons (297.1 L) for helicopters S/N 35049and subsequent. CG then begins to moverearward as fuel is consumed from forward(lower) fuel cells. With normal crew andpassenger loading, GW CG should remainwithin limits at any fuel quantity.

Fuel quantities are listed with moments in10-gallon increments, from 10 through216.8 gallons, and in 40-liter increments, from40 through 820.7 l i ters for hel icoptersS/N prior to 35049 (Table 5-5).

Fuel quantities are listed with moments in10-gallon increments, from 10 through218.6 gallons, and in 40-liter increments, from40 through 827.4 l i ters for hel icoptersS/N 35049 and subsequent (Table 5-6).

5-7-A. COMPUTATION OF CG

A sample problem is presented showingcalculation of takeoff and landing weights andCG locat ions for two typ ica l load ingconditions.

5-7-B. SAMPLE LOADING PROBLEM

CG of helicopter will move forward as fuel isburned off in flight. This occurs because fuelis burned from upper rear fuel cells first. Amaximum forward CG condition occurs when72.6 gallons (274.8 L) of fuel is on board forhelicopters S/N prior to 35049. CG thenbegins to move rearward as fuel is burned outof lower fuel cells.

Helicopter is chartered to transport ninepassengers and 180 pounds (82 kg) ofbaggage for a t r ip that w i l l requi reapproximately 155 gallons (586.8 L) of fuel.Pilot, weighing 180 pounds (82 kg), will returnalone. Determine extreme CG conditions forboth trips.

From GW CG charts in Section 1, it can bedetermined that CG is within limits for first legof flight and that loading of passengers in fiveman and four man seats will be satisfactoryfor first leg.

BHT-212VFR-FM-1

ECCN EAR99

From GW CG char ts , i t can a lso bedetermined that CG is within limits for secondleg of flight, thus, entire operation can becompleted.

17 OCT 2011 Rev. 5 5-5/5-6

MANUFACTURER'S DATA BHT-212VFR-FM-1

BAGGAGECOMPARTMENT

-- 84IN-_

243

;~~, ~,: =:fuJ-:~I ll1J L

I --,.. •• FS138.0C

~@]H-.r------- - ----;===JI iJ9l1 --,- -9I ~,~,@ I

I f----'----JI ~,L __ J

8747

23

IHEFDATUM

FUSELAGESTATIONS•

••

FUSELAGESTATIONS

REFDATUM

102 166

I 177

155

Figure 5-1. Helicopter station diagram

~-- - _. Seats

o lateral location (Inches From ell of Helicopter

D Longitudinal location (Inches Aft of Ref Datum) 01 Personnel

~ External Cargo

•••

(i) Pilot Seat

CD C.opilot or Passenger Seat

~ Fuel Cells

212VFR-FM·5·1

5-7

WEIGHT MOMENTCHANGE ARM C~ANGE

DOOR CONFIGURATION (POUNDS) (INCHES) (IN-LB)

Both crew doors removed -39.0 46.2 -1802Both hinged panels removed -20.4 85.0 1734Both sliding doors removed -90.4 130.0 -11,752Both sliding doors full open 0 202.0 +6509

BHT-212VFR-FM-1 MANUFACTURER'S DATA

Table 5·1. Door weights and moments

ENGLISH

METRIC

•••

DOOR CONFIGURATION

Both crew doors removedBoth hinged panels removedBoth sliding doors removedBoth sliding doors full open

5·8

WEIGHTCHANGE

(KILOGRAMS)

-17.7- 9.3-41.0

o

ARM(MILLIMETERS)

1173215933')25131

MOMENTCHANGE

(KG· MM/100)

-207.6200.8

-1353.8+749.9

(TABLE I.D. 911208)

•••

• • • • • •

encD

Table 5-2. Crew and passenger table of moments

CREW AND PASSENGER TABLE OF MOMENTS (ENGLISH)

Passenger Passenger Passenger Litter PatientPilot and (4 - Man Seat (5 - Man Seat Facina Outboard Lateral Longitudinal

Weight Copilot" Facing Aft) Facing Fwd) Fwd Seat Aft Seat Loaded Loaded(Pounds) FS 47 FS 87 FS 117 FS 139 FS 156 FS 117 FS 120

100 4700 8700 11700 13900 15600 11700 12000110 5170 9570 12870 15290 17160 12870 13200120 5640 10440 14040 16680 18720 14040 14400130 6110 11310 15210 18070 20280 15210 15600140 6580 12180 16380 19460 21840 16380 16800150 7050 13050 17550 20850 23400 17550 18000160 7520 13920 18720 22240 24960 18720 19200170 7990 14790 19890 23630 26520 19890 20400180 8460 15660 21060 25020 28080 21060 21600190 8930 16530 22230 26410 29640 22230 22800200 9400 17400 23400 27800 31200 23400 24000210 9870 18270 24570 29190 32760 24570 25200220 10340 19140 25740 30580 34320 25740 26400

"Left Forward Seat

(TABLE I.D. 911209)

==>zc:.">o~c::zlm~enc>~

CREW AND PASSENGER TABLE OF MOMENTS (METRIC)(KG • MM/100)

Passenger Passenger Passenger Litter PatientPilot and (4 - Man Seat (5 - Man Seat Facing Outboard Lateral Longitudinal

Weight Copilot" Facing Aft) Facing Fwd) Fwd Seat Aft Seat Loaded Loaded(Kilograms) 1194 MM 2210 MM 2972 MM 3531 MM 3962 MM 2972 MM 3048 MM

45 537.3 994.5 1337.4 1589.0 1782.9 1337.4 1371.650 597.0 1105.0 1486.0 1765.5 1981.0 1486.0 1524.055 656.7 1215.5 1634.6 1942.1 2179.1 1634.6 1676.460 716.4 1326.0 1783.2 2118.6 2377.2 1783.2 1828.865 776.1 1436.5 1931.8 2295.2 2575.3 1931.8 1981.270 835.8 1547.0 2080.4 2471.7 2773.4 2080.4 2133.675 895.5 1657.5 2229.0 2648.3 2971.5 2229.0 2286.080 955.2 1768.0 2377.6 2824.8 3169.6 2377.6 2438.485 1014.9 1878.5 2526.2 3001.4 3367.7 2526.2 2590.890 1074.6 1989.0 2674.8 3177.9 3565.8 2674.8 2743.295 1134.3 2099.5 2823.4 3354.5 3763.9 2823.4 2895.6

"Left Forward Seat

Table 5-2. Crew and passenger table of moments (Cont)

(TABLE 1.0. 911210)

!CI

• • •II"I

• • •

til:::t~~N<."::D;..~...

s:::1>0Zc:.":1>0o-4c:::Dm::Denc:1>0-4:1>0

INTERNAL CARGO LOADING TABLE (ENGLISH)

CARGOWEIGHT CARGO CENTER OF GRAVITY (FS)

(POUNDS) 75 90 105 120 135 150

CARGO MOMENT (IN-LB)

50 3750 4500 5250 6000 6750 7500100 7500 9000 10500 12000 13500 15000150 11250 13500 15750 18000 20250 22500200 15000 18000 21000 24000 27000 30000250 18750 22500 26250 30000 33750 37500

300 22500 27000 31500 36000 40500 45000350 26250 31500 36750 42000 47250 52500400 30000 36000 42000 48000 54000 60000450 33750 40500 47250 54000 60750 67500500 37500 45000 52500 60000 67500 75000

550 41250 49500 57750 66000 74250 82500600 45000 54000 63000 72000 81000 90000650 48750 58500 68250 78000 87750 97500700 52500 63000 73500 84000 94500 105000750 56250 67500 78750 90000 101250 112500

800 60000 72000 84000 96000 108000 120000850 63750 76500 89250 102000 114750 127500900 67500 81000 94500 108000 121500 135000950 71250 85500 99750 114000 128250 142500

1000 75000 90000 105000 120000 135000 150000

1050 78750 94500 110250 126000 141750 1575001100 82500 99000 115500 132000 148500 1650001150 86250 103500 120750 138000 155250 1725001200 90000 108000 126000 144000 162000 1800001250 93750 112500 131250 150000 168750 187500

1300 97500 117000 136500 156000 175500 1950001350 101250 121500 151750 162000 182250 2025001400 105000 126000 147000 168000 189000 2100001450 108750 130500 152250 174000 195750 2175001500 112500 135000 157500 180000 202500 225000

1550 116250 139500 162750 186000 209250 2325001600 120000 144000 168000 192000 216000 2400001650 123750 148500 173250 198000 222750 2475001700 127500 153000 178500 204000 229500 2550001750 131250 157500 193750 210000 236250 262500

1800 135000 162000 189000 216000 243000 2700001850 138750 166500 194250 222000 249750 2775001900 142500 171000 199500 228000 256500 2850001950 146250 175500 204750 234000 263250 2925002000 150000 180000 210000 240000 270000 300000

•••

•••

MANUFACTURER'S DATA

Table 5-3. Internal cargo loading

BHT-212VFR-FM-1

(TABLE 1.0. 911214)

5-11

INTERNAL CARGO LOADING TABLE (METRIC)

CARGOWEIGHT CARGO CENTER OF GRAVITY (MM)

(KG) 1905 2286 2667 3048 3429 3810

CARGO MOMENT (KG· MM/l00)

25 476.3 571.5 666.8 762.0 857.3 952.550 952.5 1143.0 1333.5 1524.0 1714.5 1905.075 1428.8 1714.5 2000.3 2286.0 2571.8 2857.5

100 1905.0 2286.0 2667.0 3048.0 3429.0 3810.0125 2381.3 2857.5 3333.8 3810.0 4286.3 4762.5150 2857.5 3429.0 4000.5 4572.0 5143.5 5715.0175 3333.8 4000.5 4667.3 5334.0 6000.8 6667.5200 3810.0 4572.0 5334.0 6096.0 6858.0 7620.0225 4286.3 5143.5 6000.8 6858.0 7715.3 8572.5250 4762.5 5715.0 6667.5 7620.0 8572.5 9525.0275 5238.8 6286.5 7334.3 8382.0 9429.8 10477.5300 5715.0 6858.0 8001.0 9144.0 10287.0 11430.0325 6191.3 7429.5 8667.8 9906.0 11144.3 12382.5350 6667.5 8001.0 9334.5 10668.0 12001.5 13335.0375 7143.8 8572.5 10001.3 11430.0 12858.8 14287.5400 7620.0 9144.0 10668.0 12192.8 13716.0 15240.0425 8096.3 9715.5 11334.8 12954.0 14573.3 16192.5450 8572.5 10287.0 12001.5 13716.0 15430.5 17145.0475 9048.8 10858.5 12668.3 14478.0 16287.8 18097.5500 9525.0 11430.0 13335.0 15240.0 17145.0 19050.0525 10001.3 12001.5 14001.8 16002.0 18002.3 20002.5550 10477.5 12573.0 14668.5 16764.0 18859.5 20955.0575 10953.8 13144.5 15335.3 17526.0 19716.8 21907.5600 11430.0 13716.0 16002.0 18288.0 20574.0 22860.0625 11906.3 14287.5 16668.8 19050.0 21431.3 23812.5650 12382.5 14859.0 17335.5 19812.0 22288.5 24765.0675 12858.8 15430.5 18002.3 20574.0 23145.8 25717.5700 13335.0 16002.0 18669.0 21336.0 24003.0 26670.0725 13811.3 16573.5 19335.8 22098.0 24860.3 27622.5750 14287.5 17145.0 20002.5 22860.0 25717.5 28575.0775 14763.8 17716.5 20669.3 23622.0 26574.8 29527.5800 15240.0 18288.0 21336.0 24384.0 27432.0 30480.0825 15716.3 18859.5 22002.8 25146.0 28289.3 31432.5850 16192.5 19431.0 22669.5 25908.0 29146.5 32385.0875 16668.8 20002.5 23336.3 26670.0 30003.8 33337.5900 17145.0 20574.0 24003.0 27432.0 30861.0 34290.0

BHT-212VFR-FM-1

5·12

MANUFACTURER'S DATA

Table 5-3. Internal cargo loading (Cant)

(TABLE I.D. 911215)

•••

•••

BAGGAGE LOADING TABLE (ENGLISH)LOAD BAGGAGE FROM FORWARD END OF COMPARTMENT

400 POUND MAXIMUM

WEIGHT APPROX.CG WEIGHT APPROX.CG(LB) (FS) MOMENT (LB) (FS) MOMENT

20 245 4900 220 265 5830040 247 9880 240 267 6408060 249 14940 260 269 6994080 251 20080 280 271 75880

100 253 25300 300 273 81900120 255 30600 320 275 88000140 257 35980 340 277 94180160 259 41440 360 279 100440180 261 46980 380 281 106780200 263 52600 400 283 113200

•••

MANUFACTURER'S DATA

Table 5-4. Baggage loading

BHT-212VFR-FM-1

•••

BAGGAGE LOADING TABLE (METRIC)LOAD BAGGAGE FROM FORWARD END OF COMPARTMENT

181.4 KILOGRAMS MAXIMUM

WEIGHT APPROX. CG MOMENT WEIGHT APPROX. CG MOMENT(KG) (MM) (KG· MM/100) (KG) (MM) (KG· MM/100)

10 6228 622.8 110 6789 7467.920 6284 1256.8 120 6845 8214.030 6340 1902.0 130 6901 8971.340 6396 2558.4 140 6957 9739.850 6452 3226.0 150 7013 10519.560 6507 3904.2 160 7069 11310.470 6563 4594.1 170 7125 12112.580 6619 5295.2 180 7181 12925.890 6675 6007.5 181.4 7188 13039.0

100 6734 6734.0(TABLE 1.0. 911213)

5·13

BHT-212VFR-FM-1

5-14 Rev. 5 17 OCT 2011 ECCN EAR99

Table 5-5. Fuel Loading Helicopters S/N Prior to 35049

ENGLISH

ASTM D-1655 JET A, A-1, JP-5, AND JP-8(6.8 LB/GAL)

ASTM D-6615 JET B AND JP-4(6.5 LB/GAL)

QUANTITY(U.S. GAL)

WEIGHT(LB)

CG(IN)

MOMENT(IN•LB)

QUANTITY(U.S. GAL)

WEIGHT(LB)

CG(IN)

MOMENT(IN•LB)

10 68 143.3 9765 10 65 143.6 9334

20 136 143.6 19530 20 130 143.6 18668

30 204 140.2 28601 30 195 140.2 27339

40 272 134.8 36666 40 260 134.8 35048

50 340 131.6 44744 50 325 131.6 42770

60 408 129.4 52795 60 390 129.4 50466

70 476 127.9 60880 70 455 127.9 58195

72.6* 494 127.6 63034 72.6* 472 127.6 60227

80 544 128.3 69795 80 520 128.3 66716

90 612 130.6 79927 90 585 130.6 76401

100 680 134.6 91528 100 650 134.6 87490

110 748 137.8 103074 110 715 137.8 98527

120 816 140.4 114566 120 780 140.4 109512

130 884 142.6 126058 130 845 142.6 120497

140 952 144.6 137659 140 910 144.6 131586

150 1020 146.1 149022 150 975 146.1 142448

160 1088 147.6 160589 160 1040 147.6 153504

170 1156 148.8 172013 170 1105 148.8 164424

180 1224 149.9 183478 180 1170 149.9 175383

190 1292 150.9 194963 190 1235 150.9 186362

200 1360 151.9 206584 200 1300 151.9 197470

210 1428 152.7 218056 210 1365 152.7 208436

216.8** 1474 153.3 225964 216.8** 1409 153.3 216000

* Most critical fuel amount for most forward flight condition.

** Most critical fuel amount for most aft flight condition.

NOTE: All data above represents usable fuel based on nominal density at 15°C (59°F).

BHT-212VFR-FM-1

17 OCT 2011 Rev. 5 5-15ECCN EAR99

Table 5-5. Fuel Loading Helicopters S/N Prior to 35049 (Cont)

METRIC

ASTM D-1655 JET A, A-1, JP-5, AND JP-8(0.815 KG/L)

ASTM D-6615 JET B AND JP-4(0.779 KG/L)

LITERS WEIGHT(KG)

CG(MM)

MOMENTKG•MM

100

LITERS WEIGHT(KG)

CG(MM)

MOMENTKG•MM

100

40 32.6 3647 1188.9 40 31.2 3647 1137.9

80 65.2 3647 2377.8 80 62.3 3647 2272.1

120 97.8 3541 3463.1 120 93.5 3541 3310.8

160 130.4 3399 4432.3 160 124.6 3399 4235.2

200 163.0 3322 5414.9 200 155.8 3322 5175.7

240 195.6 3272 6400.0 240 187.0 3272 6118.6

274.8* 224.0 3241 7259.8 274.8* 214.1 3241 6939.0

280 228.2 3246 7407.4 280 218.1 3246 7079.5

320 260.8 3277 8546.4 320 249.3 3277 8169.6

360 293.4 3368 9881.7 360 280.4 3368 9443.9

400 326.0 3470 11312.2 400 311.6 3470 10812.5

440 358.6 3541 12698.0 440 342.8 3541 12138.5

480 391.2 3609 14118.4 480 373.9 3609 13494.1

520 423.8 3665 15532.3 520 405.1 3665 14846.9

560 456.4 3708 16923.3 560 436.2 3708 16174.3

600 489.0 3744 18308.2 600 467.4 3744 17499.5

640 521.6 3777 19700.8 640 498.6 3777 18832.1

680 554.2 3805 21087.3 680 529.7 3805 20155.1

720 586.8 3833 22492.0 720 560.9 3833 21499.3

760 619.4 3858 23896.5 760 592.0 3858 22839.4

800 652.0 3884 25323.7 800 623.2 3884 24205.1

820.7** 668.9 3894 26047.0 820.7** 639.3 3894 24894.3


** Most critical fuel amount for most aft flight condition.


BHT-212VFR-FM-1

5-16 Rev. 5 17 OCT 2011 ECCN EAR99

Table 5-6. Fuel Loading Helicopters S/N 35049 and Subsequent

ENGLISH

ASTM D-1655 JET A, A-1, JP-5, AND JP-8(6.8 LB/GAL)

ASTM D-6615 JET B AND JP-4(6.5 LB/GAL)

QUANTITY(U.S. GAL)

WEIGHT(LB)

CG(IN)

MOMENT(IN•LB)

QUANTITY(U.S. GAL)

WEIGHT(LB)

CG(IN)

MOMENT(IN•LB)

10 68 143.9 9785 10 65 143.9 9354

20 136 144.0 19584 20 130 144.0 18720

30 204 141.6 28886 30 195 141.6 27612

40 272 135.7 36910 40 260 135.7 35282

50 340 132.2 44948 50 325 132.2 42965

60 408 129.9 52999 60 390 129.9 50661

70 476 128.2 61023 70 455 128.2 58331

78.5* 534 127.3 67953 78.5* 510 127.3 64955

80 544 127.4 69306 80 520 127.4 66248

90 612 129.5 79254 90 585 129.5 75758

100 680 133.4 90712 100 650 133.4 86710

110 748 136.7 102252 110 715 136.7 97741

120 816 139.3 113669 120 780 139.3 108654

130 884 141.7 125263 130 845 141.7 119737

140 952 143.6 136707 140 910 143.6 130676

150 1020 145.2 148104 150 975 145.2 141570

160 1088 146.8 159718 160 1040 146.8 152672

170 1156 148.1 171204 170 1105 148.1 163651

180 1224 149.3 182743 180 1170 149.3 174681

190 1292 150.3 194188 190 1235 150.3 185621

200 1360 151.3 205768 200 1300 151.3 196690

210 1428 152.1 217199 210 1365 152.1 207617

218.6 1486 152.6 226837 218.6 1421 152.6 216829



BHT-212VFR-FM-1

17 OCT 2011 Rev. 5 5-17ECCN EAR99

Table 5-6. Fuel Loading Helicopters S/N 35049 and Subsequent (Cont)

METRIC

ASTM D-1655 JET A, A-1, JP-5, AND JP-8(0.815 KG/L)

ASTM D-6615 JET B AND JP-4(0.779 KG/L)

LITERS WEIGHT(KG)

CG(MM)

MOMENTKG•MM

100

LITERS WEIGHT(KG)

CG(MM)

MOMENTKG•MM

100

40 32.6 3655 1191.5 40 31.2 3655 1140.4

80 65.2 3658 2385.0 80 62.3 3658 2278.9

120 97.8 3561 3482.7 120 93.5 3561 3329.5

160 130.4 3421 4461.0 160 124.6 3421 4262.6

200 163.0 3340 5444.2 200 155.8 3340 5203.7

240 195.6 3284 6423.5 240 187.0 3284 6141.1

280 228.2 3246 7407.4 280 218.1 3246 7079.5

297.1* 242.1 3233 7827.1 297.1* 231.4 3233 7481.2

320 260.8 3249 8473.4 320 249.3 3249 8099.8

360 293.4 3343 9808.4 360 280.4 3343 9373.8

400 326.0 3434 11194.8 400 311.6 3434 10700.3

440 358.6 3515 12604.8 440 342.8 3515 12049.4

480 391.2 3579 14001.1 480 373.9 3579 13381.9

520 423.8 3635 15405.1 520 405.1 3635 14725.4

560 456.4 3683 16809.2 560 436.2 3683 16065.3

600 489.0 3721 18195.7 600 467.4 3721 17392.0

640 521.6 3757 19596.5 640 498.6 3757 18732.4

680 554.2 3790 21004.2 680 529.7 3790 20075.6

720 586.8 3818 22404.0 720 560.9 3818 21415.2

760 619.4 3843 23803.5 760 592.0 3843 22750.6

800 652.0 3866 25206.3 800 623.3 3866 24092.9

827.4 674.3 3876 26135.9 827.4 644.5 3876 24980.8




SAMPLE LOADING PROBLEM (ENGLISH UNITS)HELICOPTER SERIAL NUMBERS PRIOR TO 35049

FIRST LEG •WEIGHT CG MOMENT

'" (LBS) (INCHES) (IN-LBS)cu;:i:

{Licensed Empty Weight 6529.4 939996 •.;~......

lDO~ +Oil 24.5 4146'tI +Pilot *170.0 7990•0{ +Passengers (5 man seat) *850.0 99450>.• +Passengers (4 man seat) *680.0 591600.

+Baggage *180.0 46980 •Basic Operating Weight + Payload 8433.9 1157722..c Basic Operating Weight + Payload 8433.9 1157722

=~ {0-.. 't1 +Takeoff Fuel (216.8 gallons Type B) *1409.0 216000... c.0I-U

Takeoff Weight, CG & Moment 9842.9 139.6 1373722..c Basic Operating Weight + Payload 8433.9 1157722.d:lE {_:!::c'O +Crltlcal Fuel (72.6 gallons Type B) *472.0 60227~~~ S::IULLU

Critical Weight, CG & Moment 8905.9 136.8 1217949..Basic Operating Weight + Payloadc

{8433.9 115772201.2c-:s:S +Landing Fuel (60 gallons Type B) *390.0 50466cc

.0.... u Landing Weight, CG & Moment 8823.9 136.9 1208188

(* Information obtained from loading charts)

(TABLE 1.0. 911217) •••

5-18

SAMPLE LOADING PROBLEM (ENGLISH UNITS)HELICOPTER SERIAL NUMBERS PRIOR TO 35049•


••

SECOND LEG

Licensed Empty Weight

+Oil+PilotBasic Operating Weight (No Payload)

+Takeoff Fuel (216.8 gallons Type B)

Takeoff Weight, CG & Moment

Basic Operating Weight (No Payload)

+Critical Fuel (72.6 gallonsType B)

Critical Weight, CG & Moment

Basic Operating Weight (No Payload)

+Landing Fuel (60 gallons Type B)

Landing Weight, CG & Moment

WEIGHT(LBS)

6529.4

24.5*170.06723.9

*1409.0

8132.9

6723.9

*472.0

7195.9

6723.9

*390.0

7113.9

CG(INCHES)

143.6

140.7

140.9

MOMENT(IN-LBS)

939996

41467990

952132

216000

1168132

952132

60227

1012359

952132

50466

1002598

•••

(TABLE I.D. 911218)

5-19


SAMPLE LOADING PROBLEM (METRIC UNITS)HELICOPTER SERIAL NUMBERS PRIOR TO 35049

FIRST LEG •MOMENTWEIGHT CG (KGeMM

= (KG) (foIIM) 100) •cu:;~"i.~......

{ Licensed Empty Weight 2961.7 108298.71II0~

'0 +011 11.1 477.7• +Pllot *90.0 1074.60>.

+Passengers (5 man seat) •• {*375.0 11145.00-

+Passengers (4 man seat) *300.0 6630.0+Baggage *80.0 5295.2

OJ Basic Operating Weight + Payload 3817.8 132921.2c

=~ {Basic Operating Weight + Payload 3817.8 132921.2

0-.. '0... C +Takeoff Fuel (820.7 liters Type B) *639.3 24894.3.0..... u

OJTakeoff Weight, CG & Moment 4457.1 3541 157815.5

c1'0

{ Basic Operating Weight + Payload 3817.8 132921.2'iiuE_~Q"tI

3~~ ~ +Critlcal Fuel (274.8 liters Type B) *214.1 6939.0:IOu u

Critical Weight, CG & Moment 4031.9 3469 139860.2OJc

{Basic Operating Weight + Payload=0 3817.8 132921.2c:O:

:a=g+Landlng Fuel (227.1 liters Type B) *176.9 5814.5;0

....IU

Landing Weight, CG & Moment 3994.7 3473 138735.7


(TABLE I.D. 911219) •••

5-20

SECOND LEG

SAMPLE LOADING PROBLEM (METRIC UNITS)HELICOPTER SERIAL NUMBERS PRIOR TO 35049•


MOMENT

0> WEIGHT CG (KG-MM

• I: (KG) (MM) 100)u;:E_~O>.... -.. Q."

{Licensed Empty Weight 2961.7 108298.7lllO~

.. +Oil 11.1 477.7I: +Pllot *90.0 1074.6:t:.g• 2ii

{Basic Operating Weight (No Payload) 3062.8 109851.0

... 1:.. 0I-U +Takeoff Fuel (820.7 liters Type B) *639.3 24894.3

.. Takeoff Weight, CG & Moment 3702.1 3640 134745.3I:

.8E

{Basic Operating Weight (No Payload) 3062.8 109851.0.~c-g

0;: ~ 0::::EUlI.U +Critical Fuel (274.8 liters Type B) *214.1 6939.0

.. Critical Weight, CG & Moment 3276.9 3564 116790.0I:

0>0

.5~


~~ju +Landlng Fuel (227.1 liters Type B) *176.9 5814.5


(TABLE I.D. 911220)

•••

5·21


SAMPLE LOADING PROBLEM (ENGLISH UNITS)HELICOPTER SERIAL NUMBERS 35049 AND SUBSEQUENT •FIRST LEG

WEIGHT CG MOMENTca (LBS) (INCHES) (IN-LBS)c •ul.E

{ Licensed Empty Weight 6529.4 939996-= i-f1II0~ +011 24.5 4146

"CI +Pllot *170.0 7990•

{0 +Passengers (5 man seat) *850.0 99450>.• +Passengers (4 man seat) *680.0 59160 •A.

+Baggage *180.0 46980

Basic Operating Weight + Payload 8433.9 1157722•c Basic Operating Weight + Payload 8433.9 1157722=,g {2'ii +Takeoff Fuel (218.6 gallons Type B) *1421.0 216829... c

.0I-U

Takeoff Weight, CG & Moment 13745519854.9 139.5•c Basic Operating Weight + Payload 8433.9 1157722_C1,2

{-~~~ +Crltlcal Fuel (78.5 gallons Type B) *510.0 64955B~if g:::Eu U

Critical Weight, CG & Moment 8943.9 136.7 1222677

• Basic Operating Weight + Payload 8433.9 1157722c

{ca,2

~~ +Landlng Fuel (60 gallons Type B) *390.0 50661cC~8 Landing Weight, CG & Moment 8823.9 136.9 1208383


(TABLE I.D. 811328) •••

5·22


• SAMPLE LOADING PfiOBLEM (ENGLISH UNITS)HELICOPTER SERIAL NUMBERS 35049 AND SUBSEQUENT

SECOND LEG

WEIGHT CG MOMENT'" (LBS) (INCHES) (IN-LBS)• c

u i:c

iH { Licensed Empty Weight 6529.4 939996IDO:=

.. +Oil 24.5 4146c +Pllot *170.0 7990

• d{ Basic Operating Weight (No Payload) 6723.9 9521320-.,'1:1-",c110 +Takeoff Fuel (218.6 gallons Type B) *1421.0 216829..... u

.. Takeoff Weight, CG & Moment 8144.9 143.5 1168961c

.B~{ Basic Operating Weight (No Payload) 6723.9 952132_=0'1:1

~~ff~ +Crltlcal Fuel (78.5 gallonsType B) *510.0 64955::lEu u

.. Critical Weight, CG & Moment 7233.9 140.6 1017087c..{ Basic Operating Weight (No Payload) 6723.9 952132c_

:a:aCc110 +Landlng Fuel (60 gallons Type B) *390.0 50661-,u

Landing Weight, CG & Moment 7113.9 141.0 1002793

(TABLE I.D. 911327)

•••

5-23

BHT·212VFR·FM-1 MANUFACTURER'S DATA

SAMPLE LOADING PROBLEM (METRIC UNITS)HELICOPTER SERIAL NUMBERS 35049 AND SUBSEQUENT •FIRST LEG

MOMENTWEIGHT CG (KG-MM •ao (KG) (MM) 100)C

:;:;-ull,c"i~gII Doll

{ Licensed Empty Weight 2961.7 108298.71Il0~

'0 +011 11.1 477.7II +Pilot *90.0 1074.60>. •II

{ +Passengers (5 man seat) *375.0 11145.0lL+Passengers (4 man seat) *300.0 6630.0+Baggage *80.0 5295.2

II Basic Operating Weight + Payload 3817.8 132921.2C

=~ {Basic Operating Weight + Payload 3817.8 132921.2

0-11'0... c +Takeoff Fuel (827.4 liters Type B) *644.5 24980.811 0I-U

IITakeoff Weight, CG & Moment 4462.3 3539 157902.0

C

'iS~ { Basic Operating Weight + Payload 3817.8 132921.2_~Qii

3~~ a +Crltlcal Fuel (297.1 liters Type B) *231.4 7481.2~U U

Critical Weight, CG & Moment 4049.2 3467 140402.4coC

{ Basic Operating Weight + Payloadao.2 3817.8 132921.2c-'6~ +Landing Fuel (227.1 liters Type B) *176.9 5838.8Coju



(TABLE I.D. 911326) •••

5-24


SAMPLE LOADING PROBLEM (METRIC UNITS)

• HELICOPTER SERIAL NUMBERS 35049 AND SUBSEQUENT

SECOND LEG

MOMENT

lJl WEIGHT CG (KG-MM

• I: (KG) (MM) 100)(,):;:E"it~., a."mO~

{Licensed Empty Weight 2961.7 108298.7

.. +011 11.1 477.7I: +Pllot *90.0 1074.6• =.g

{0- Basic Operating Weight (No Payload) 3062.8 109851.0.,'0.><1:.,0I-U +Takeoff Fuel (827.4 liters Type B) *644.5 24980.8.. Takeoff Weight, CG & Moment 3707.3 3637 134831.8I:

"i8~

{Basic Operating Weight (No Payload) 3062.8 109851.0"=0"

~~~ g~u U +Crltlcal Fuel (297.1 liters Type B) *231.4 7481.2

.. Critical Weight, CG & Moment 3294.2 3562 117332.2I:lJlO1:':


:a~

~S +Landing Fuel (227.1 liters Type B) *176.9 5838.8


(TABLE I.D. 911325)

•••

5-25/5-26

BHT-212VFR-FM-1

ECCN EAR99

Appendix AOPTIONAL EQUIPMENT SUPPLEMENTS

ATABLE OF CONTENTS


Optional Equipment............................................................................... A-1 .......... A-3

LIST OF TABLES

Table PageSubject Number Number

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

17 OCT 2011 Rev. 5 A-1/A-2

BHT-212VFR-FM-1

17 OCT 2011 Rev. 5 A-3ECCN EAR99

Appendix AOPTIONAL EQUIPMENT SUPPLEMENTS

AA-1. OPTIONAL EQUIPMENT

Bell Helicopter Textron’s policy is one ofcontinuous product improvement. Bellreserves the right to incorporate designchanges, make additions to, and improve itsproduct without imposing any obligation

upon the company to furnish for or installsuch changes, additions, improvements, etc.,products previously manufactured.

Flight Manual Supplement for each kit listedin Table A-1 must be carried in helicopter atall times if subject kit is installed.

Table A-1. Flight Manual Supplements for Optional Equipment

NAME OF EQUIPMENT KIT NUMBERCERTIFIED

DATEREVISIONCURRENT

BHT-212-FMS-1Litters

205-706-047 1 MAR 72 Reissue14 AUG 95

BHT-212-FMS-2Winterization Heater

212-706-008 29 OCT 70 Reissue14 AUG 95

BHT-212-FMS-3Cargo Hook

212-706-103 29 OCT 70 Rev. 112 SEP 97

BHT-212-FMS-4Auxiliary Fuel Tanks

205-706-044205-706-045

29 OCT 70 Reissue12 SEP 97

BHT-212-FMS-5Internal Rescue Hoist (Breeze)

205-706-030 1 MAR 71 Reissue14 AUG 95

BHT-212-FMS-6Fixed Floats

205-706-050 1 APR 71 Reissue14 AUG 95

BHT-212-FMS-7Category A Operations

18 AUG 72 Rev. 112 SEP 97

BHT-212-FMS-8Emergency Flotation

212-706-021 28 AUG 72 Reissue14 AUG 95

BHT-212-FMS-9Emergency Flotation

212-706-042 9 AUG 73 Reissue14 AUG 95

BHT-212-FMS-10.1Battery Temperature Sensor

Incorporated Into Basic Flight Manual

BHT-212-FMS-10.2Battery Temperature Sensor


BHT-212VFR-FM-1

A-4 Rev. 5 17 OCT 2011 ECCN EAR99

BHT-212-FMS-11VLF-1000 Navigation System

212-899-118 21 MAY 74 Reissue14 AUG 95

BHT-212-FMS-12Heated Windshield

212-899-244 3 JUN 74 Reissue14 AUG 95

BHT-212-FMS-13Environmental Control Unit(Air Conditioning)

212-706-025 17 JUN 74 Reissue14 AUG 95

BHT-212-FMS-1420/90 Auxiliary Fuel Tanks

212-899-243 3 MAR 75 Reissue14 AUG 95

BHT-212-FMS-15KNC 610 Area Nav System

212-899-131 4 APR 75 Reissue14 AUG 95

BHT-212-FMS-16Heated Windshield

212-706-053 1 NOV 75 Reissue14 AUG 95

BHT-212-FMS-17Internal Rescue Hoist(Western Gear)

214-706-003 20 NOV 75 Reissue14 AUG 95

BHT-212-FMS-18Automatic Flight Control System/Autopilot

212-961-620(For VFR operations)

15 DEC 76 Reissue14 AUG 95

BHT-212-FMS-19Automatic Flight Control System/Autopilot

212-706-111(For VFR operations)

14 JUN 77 Reissue14 AUG 95

BHT-212-FMS-20Altitude Hold System

212-899-143 12 DEC 77 Reissue14 AUG 95

BHT-212-FMS-21Crash Position Indicator

212-899-375 1 JUN 78 Reissue24 MAR 95

BHT-212-FMS-22Transmission


BHT-212-FMS-23PT6T-3B Engine


BHT-212-FMS-24Seat Cushion

412-706-019 24 JUL 87 Reissue14 AUG 95

BHT-212-FMS-25Fixed Step

212-706-057 27 SEP 89 Reissue14 AUG 95

BHT-212-FMS-CAN-26Internal Rescue Hoist and Cargo Hook

9 NOV 89 Reissue14 AUG 95

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


DATEREVISIONCURRENT

BHT-212VFR-FM-1

ECCN EAR99

BHT-212-FMS-27Alternate Static Air Valve


BHT-212-FMS-28Two-speed Internal Hoist

214-706-003 7 May 92 Reissue14 AUG 95

BHT-212-FMS-29Increased Takeoff Horsepower

212-704-153 16 DEC 91 Rev. 120 JUL 09

BHT-212-FMS-30Airline Passenger Seating

412-706-028 18 JUN 93 Reissue14 AUG 95

BHT-212-FMS-31Cold Weather Operation with Kerosene Fuels

24 JAN 05 Original

BHT-212-FMS-32Engine No. 2 Governor Trim Actuator

TB 212-93-145 28 JUL 94 Rev. 13 MAY 06

BHT-212-FMS-33Bendix/King RDS 81 Weather Radar

212-899-234 7 OCT 94 Original

BHT-212-FMS-34TRIMPACK GPS Navigator

212-899-835 7 OCT 94 Reissue24 FEB 95

BHT-212-FMS-35Increased Weight Altitude Temperature Limit

212-704-129212-704-153

22 MAR 96 Original

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


DATEREVISIONCURRENT

17 OCT 2011 Rev. 5 A-5/A-6

Documents

BHT-212VFR-FM-1