Manual Operations BELL-212- Helicopter

7/22/2019 Manual Operations BELL-212- Helicopter

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POST OFFICE BOX 482 FORT WORTH, TEXAS 761

BHT-212IFR-FM-1

COPYRIGHT NOTICE

COPYRIGHT 2002

BELL HELICOPTER TEXTRON INC.

AND BELL HELICOPTER TEXTRON

CANADA LTD.

ALL R IGHTS RESER VED

THIS MANUAL SHALL BE IN THE HELICOPTER DURING ALL OPERATIONS

ROTORCRAFTFLIGHT MANUAL

14 AUGUST 1995REVISION 4 02 DECEMBER 2002


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BHT-212IFR-FM-1

NP

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

PROPRIETARY RIGHTS NOTICE

Manufacturers Data portion of this manual is proprietary to Bell Helicopter

Textron Inc. Disclosure, reproduction, or use of these data for any purpose other

than helicopter operation is forbidden without prior written authorization from Bell

Helicopter Textron Inc.

NOTICE PAGE


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BHT-212IFR-FM-

NOTE

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

LOG OF REVISIONS

Original ....................... 0.................... 29 JUN 73

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Revision...................... 1....................29 MAY 96

Revision ......................2 ....................12 SEP 9

Revision ......................3 ................... 01 MAY 9

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BHT-212IFR-FM-

LOG OF FAA APPROVED REVISIONS

Original ....................... 0.................... 29 JUN 73

Reissue....................... 0....................14 AUG 95

Revision ..................... 1....................29 MAY 96

Revision ......................2 ....................12 SEP 9

Revision ......................3 ................... 01 MAY 9

Revision ......................4 ................... 02 DEC 0

02 DEC 2002 Rev. 4 C/

DATE:

MANAGER

ROTORCRAFT CERTIFICATION OFFICEFEDERAL AVIATION ADMINISTRATIONFT. WORTH, TX 76193-0170

APPROVED:


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FAA APPROVED BHT-2121FR-FM-GENERAL INFORMATION

ORGANIZATION TERMINOLOGYThis flight manual is divided into fivesections and an appendix as follows: WARNINGS, CAUTIONS, ANDSection 1 LIMITATIONS NOTESSection 2 NORMAL PROCEDURESSection 3 EMERGENCY AND MAL- Warnings, cautions, and notes are usedFUNCTIONPROCEDURES throughout this manual to emphasizeSection 4 PERFORMANCE DATA important and critical instructions and arSection 5 WEIGHT AND BALANCE used as follows:Appendix A OPTIONAL EQUIPMENTSUPPLEMENTS WARNINGSections 1 through 4 contain FAAapproved data necessary to operate AN OPERATING PROCEDUREhelicopter in a safe and efficient manner. PRACTICE, ETC., WHICH, IF NOTSections 5 contains Weight and Balance CORRECTLY FOLLOWED, COULDdata. RESULT IN PERSONAL INJURYAppendix A contains a list of approved OR LOSS OF LIFE.supplements for optional equipment,which shall be used in conjunction withbasic flight manual when respective CAUTIONoptional equipment kits are installed.Manufacturer's data manual (BHT-212-MD- AN OPERATING PROCEDURE,1) contains additional information to be PRACTICE, ETC., WHICH, IF NOTused in conjunction with flight manual and STRICTLY OBSERVED, COULDoptional equipment supplements, as RESULT IN DAMAGE TO ORapplicable. Manufacturer's data manual is DESTRUCTION OF EQUIPMENTdivided into four sections as follows:Section 1 SYSTEMS NOTEDESCRIPTIONSection 2 HANDLING AND An operating procedure,SERVICING condition, etc., which is essentialSection 3 CONVERSION to highlight.CHARTS ANDTABLESSection 4 EXPANDED USE OF PROCEDURALWORDS

PERFORMANCE Procedural word usage and intendedmeaning which has been adhered to ipreparing this manual is as follows:SHALL has been used only whenapplication of a procedure ismandatory.


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BHT-2121FR-FM-1 FAA APPROVEDSHOULD has been used only when HD Density altitudeapplication of a procedure isrecommended.recommended. HP Pressure altitudeMAY and NEED NOT have been used HSI Horizontal situationonly when application of a procedureindicatoris optional. HTR HeaterWILL has been used only to indicate HV Height-velocityfuturity, never to indicate a mandatoryprocedure. HYDRSYS Hydraulic systemIFR Instrument flight

ABBREVIATIONS AND ACRONYMS rulesIGE In ground effectAbbreviations and acronyms used IMC Instrumentthroughout this manual are defined as Meteorologicalfollows: ConditionsINCR IncreaseAC Alternating current INTCON InterconnectAFCS Automatic flightcontrol system INV Inverter

AGL Above ground level ITT InterturbinetemperatureATTD Attitude KCAS Knots calibratedBLWR Blower airspeedC Celsius KG Kilogram(s)CDP Critical decision KIAS Knots indicatedpoint airspeedCG Center of gravity LB Pound(s)CMD Command LDP Landing decisionDC Direct current pointDECR Decrease M Meter(s)DSENGA Disengage MCP Maximum continuouspowerELT Emergency locatortransmitter MIN Minimum, minute(s)ENG Engine NAV NavigationENGA Engage NON ESS Non essentialENG RPM (N2) Engine power NORMNormalturbine rpm OAT Outside airF Fahrenheit temperatureFT Foot, feet OEI One engineinoperativeGAS PROD (N1) Gas producer rpm Out of ground effectOGE Out of ground effectGEN Generator PART SEP Particle separatorGOV Governor PLT PilotGW Gross weight PRI Primaryii


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FAA APPROVED BHT-2121FR-FMREL Release VMC VisualROTOR (N) Rotor RPM MeteorologicalConditionsRPM Revolutions perminute VMIN Minimum speed forinstrument (IFR)SCAS Stability and control flightaugmentation system VNE Never exceed speeSTA Stationtation VTOCS Takeoff climboutTEMP CONT Temperature control speedVCAL Calibrated airspeed VTOSS Takeoff safety speeVFR Visual flight rules XFEED CrossfeedVG Vertical gyro. VIAS Indicated airspeed


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FAA APPROVED BHT-2121FR-FM-

Section 1TABLE OF CONTENTS PageSubject Paragraph Number

INTRODUCTION ................................................. 1-1........... 1-3BASIS OF CERTIFICATION 1-2 ........... 1-3TYPES OF OPERATION......................................... 1-3 ........... 1-3FLIGHT CREW.................................................. 1-4........... 1-3IFR OPERATION ........................................... 1-4-A ........ 1-3IFR CARGO OPERATION ...................................1-4-B ........ 1-3VFR OPERATION ........................................... 1-4-C ........ 1-3VFR CARGO OPERATION.................................. 1-4-D........ 1-4CONFIGURATION............................... ............. 1-5 .......... 1-4REQUIRED EQUIPMENT .................................... 1-5-A........ 1-4OPTIONAL EQUIPMENT .................................... 1-5-B ........ 1-4DOORS OPEN/REMOVED(VMC ONLY) .............................. 1-5-C ........ 1-4PASSENGERS.............................................. .. 1-5-D ....... 1-4CARGO .................................................. 1-5-E ........ 1-4AWEIGHT AND CENTER OF GRAVITY ........................... 1-6........... 1-5WEIGHT .................................................... 1-6-A ........ 1-5CENTER OF GRAVITY ...................................... 1-6-B ........ 1-5AIRSPEED...................................................... 1-7........... 1-5ALTITUDE....................................................... 1-8........... 1-6MANEUVERING................................................. 1-9........... 1-6PROHIBITED MANEUVERS ............................... 1-9-A ....... 1-6CLIMB AND DESCENT..................................... 1-9-B ........ 1-6HEIGHT-VELOCITY ............................................. 1-10 ......... 1-6AMBIENT TEMPERATURES ................................... 1-11 ......... 1-6ELECTRICAL ................................................... 1-12 ......... 1-6BATTERY ................................................... 1-12-A ....... 1-6GENERATOR ............................................... 1-12-B ....... 1-7STARTER.................................................. 1-12-C....... 1-7GROUND POWER UNIT .................................... 1-12-D....... 1-7

POWER PLANT.................................................. 1-13 ......... 1-7GAS PRODUCER RPM (N) ................................. 1-13-A ....... 1-7POWER TURBINE RPM..................................... 1-13-B ...... 1-8INTERTURBINE TEMPERATURE ........................... 1-13-C ...... 1-8ENGINE TORQUE ........................................... 1-13-D ....... 1-8FUEL RESSURE..................................... .....-13-E ... 1-9ENGINE OIL PRESSURE ................................... 1-13-F ...... 1-9ENGINE OIL TEMPERATURE .............................. 1-13-G....... 1-9COMBINING GEARBOX OIL PRESSURE .................. 1-13-H ....... 1-9COMBINING GEARBOX OIL TEMPERATURE.............. 1-13-J ....... 1-9Rev. 2 1-


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BHT-2121FR-FM-1 FAA APPROVEDTABLE OF CONTENTS (Cont) PageSubject Paragraph Number

TRANSMISSION ................................................. 1-14 ......... 1-9TRANSMISSION OIL PRESSURE........................... 1-14-A ....... 1-9TRANSMISSION OIL TEMPERATURE ...................... 1-14-B ....... 1-9TRANSMISSION TORQUE .................................. 1-14-C ....... 1-9ROTOR .......................................................... 1-15 ......... 1-10ROTOR RPM - POWER ON ................................ 1-15-A ....... 1-10ROTOR RPM - POWER OFF ............................... 1-15-B ....... 1-10HYDRAULIC ..................................................... 1-16 ......... 1-10HYDRAULIC PRESSURE ................................... 1-16-A ....... 1-10HYDRAULIC TEMPERATURE .............................. 1-16-B ....... 1-10FUEL AND OIL .................................................. 1-17 ......... 1-10FUEL ........................................................ 1-17-A ....... 1-10OIL ENGINE AND COMBINING GEARBOX................ 1-17-B ....... 1-10OIL TRANSMISSION, INTERMEDIATE AND TAIL ROTORGEARBOX .................................................. 1-17-C ....... 1-10

ROTOR BRAKE.................................................. 1-18 ......... 1-11LANDING GEAR ................................................. 1-19 ......... 1-11INSTRUMENT MARKINGS AND PLACARDS ................... 1-20 ......... 1-11HEATER ......................................................... 1-21 ......... 1-11LIST OF FIGURES Figure PageTitle Number Number

Instrument markings ............................................ 1-1........... 1-13Placards and decals ............................................ 1-2........... 1-19Gross weight center of gravity chart .......................... 1-3........... 1-21Weight-altitude temperature limitations for takeoff, landingand in ground effect maneuvers chart......................... 1-4........... 1-22Single engine height velocity chart............................ 1-5........... 1-23

1-2 Rev. 2


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FAA APPROVED BHT-212IFR-FM-

02 DEC 2002 Rev. 4 1-

Section 1LIMITATIONS

1-1. INTRODUCTION

NOTE

Compliance with limitations in this

section is required by appropriate

operating rules.

Minimum and maximum limits, and normal and

cautionary operating ranges for helicopter and

subsystems are indicated by instrument

markings and placards. Instrument markings

and placards represent aerodynamic

calculations that are substantiated by flight

test data.

Anytime an operating limit is exceeded, an

appropriate entry shall be made in helicopter

log book. Entry shall state which limit was

exceeded, duration of time, extreme value

attained, and any additional information

essential in determining maintenance actionrequired.

1-2. BASIS OFCERTIFICATION

This helicopter is certified under FAR Part 29,

Category B.

1-3. TYPES OF OPERATIONThis helicopter is certified for VFR and

Category 1 IFR operations under IFR day and

night, non-icing conditions.

1-4. FLIGHT CREW

1-4-A. IFR OPERATION

Minimum flight crew for IFR operation, excep

as noted below, shall consist of two pilots

each of which must hold a helicopte

instrument rating.

1-4-B. IFR CARGO OPERATION

Refer to applicable operating rules

for internal cargo operations.

1-4-C. VFR OPERATION

Minimum cockpit (FS 47.0) weight is 17

pounds (77.1 kilograms). Refer to Section 5.

Minimum flight crew consists of one pilot wh

shall operate helicopter from right crew seat.

Left crew seat may be used for an additiona

pilot for VFR day and night operations whe

approved dual controls and copilot instrumen

kits are installed.

NOTE


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BHT-212IFR-FM-1 FAA APPROVED

1-4 Rev. 4 02 DEC 2002

1-4-D. VFR CARGO OPERATION

Refer to applicable operating rules

for internal cargo operations.

1-5. CONFIGURATION

1-5-A. REQUIRED EQUIPMENT

(*) Designates required equipment for VFR

flight.

(*)Operable force trim system.

(*)Heated pitot-static system.

(*)Pilot windshield wiper.

Operational AFCS.

Two VHF communication radios

Two navigation receivers with auxiliary

equipment appropriate for intended route of

flight.

DME equipment.

ATC transponder.

Marker beacon receiver.

Standby attitude indicator or gyro rate of turn

indicator.

Pilot IVSI.

Roof window blackout curtains

Dual controls.

Copilot instruments.

Copilot clock.

1-5-B. OPTIONAL EQUIPMENT

Refer to appropr ia te F l ight Manual

Supplement(s) for additional limitations,

procedures, and performance data with

optional equipment installed. See Appendix A.

1-5-C. DOORS OPEN/REMOVED(VMC ONLY)

Helicopter may be flown with doors open or

removed only with Bell Standard interior

installed. Flight operation is approved for the

following alternative configurations during

VMC only:

Both crew doors removed.

Both sliding doors locked open or removed

with both hinged panels installed or removed.

NOTE

Opening or removing doors shifts

helicopter center of gravity and

reduces VNE. Refer to Section 5 and

to Airspeed Limitations.

In all cases, door configuration shall be

symmetrical.

1-5-D. PASSENGERS

NOTE

Refer to Section 5 for loading

tables to be used in weight/CG

computations.

With the passenger seat kit installed, the

helicopter is certified for operations as afifteen place aircraft.

The above loading does not apply if cargo

or a combination of cargo and passengers

are being transported. It shall be the

responsibi l i ty of the p i lot to ensure

NOTE


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FAA APPROVED BHT-2121FR-FM-1helicopter is properly loaded so entire 1-5-E. CARGOflight is conducted within the limits ofgross weight center of gravity charts 1-5-E-1. INTERNAL CARGO(Figure 1-3). CONFIGURATION

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 1250

Rev. 2 1-4A/1-4B


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FAA APPROVED BHT-2121FR-FM-pounds (567.0 kilograms) vertical and 500 NOTEpounds (226.8 kilograms) horizontal perfitting. Provisions for installation of cargo Station 0 (datum) is located 20tiedown fittings are incorporated in aft inches (508.0 millimeters) aft ofcabin bulkhead and transmission support most forward point of cabin nose.structure and have an airframe structuralcapacity of 1250pounds (567.0kilograms) 1-6-B-2. LATERAL CENTER OF

at 90 degrees to bulkhead and 500 pounds GRAVITY(226.8 kilograms) In any direction parallelto bulkhead. Cargo shall be secured by an Lateral CG limits are 3.5 inches (88.9approved restraint method that will not millimeters) from fuselage centerline foimpede access to cargo in an emergency. IFR.All cargo and equipment must be securelytied down when operating with aft cabin Lateral CG limits are 4.7 inches (119.4doors open or removed. millimeters) left and 6.5 inches (165.1millimeters) right of fuselage centerline foI 1-5-E-2. BAGGAGE VFR.

The baggage compartment maximum 1-7. AIRSPEEDallowable loading is 400 pounds (181.4kilograms), not to exceed 100 pounds per VMIN (IFR) - 40 KIAS.square foot (4.9 kilograms/100 squarecentimeters). NOTE

Due to control authorities1-6. WEIGHT AND CENTER OF required for flight at airspeedsGRAVITY below 40 KIAS, AFCS ATTD modeshould not be utilized except forground checks.1-6-A. WEIGHT VNE (IFR or VFR) - 120 KIAS from seaMaximum GW is 11,200 pounds (5080.3 level up to and including 3000 feet HD akilograms). 8800 pounds (3991.6 kilograms) or lessGW decreasing linearly to VNE of 100 KIASRefer to Weight-altitude-temperature at 11,200 pounds (5080.3 kilograms) GWCG of 132.0 to 142.5. Refer to OPERATINlimitations for takeoff, landing and in LIMITATIONS decal figure 1-2 Vground effect maneuvers chart (figure 1-4). decreases 3 KIAS per 1000 feet above 3000

feet HD.1-6-B. CENTER OF GRAVITY VNE (VFR only)(CG 142.5 to 144.0) - 110KIAS from sea level up to and Including1-6-B-1. LONGITUDINAL CENTER 3000 feet HD at 10,000 pounds (4536OF GRAVITY kilograms) or less GW decreasing linearlyto VNE of 100 KIAS at 11,200 pounds

(5080.3 kilograms) GW, CG of 142.5 toLongitudinal CG operational range Is 144.0. Refer to OPERATING LIMITATIONSvariable (figure 1-3), depending upon GW, decal, igure 1-2. VNE decreases 3 KIASand shall be computed from weight and per 1000 feet above 3000 feet Hbalance data.VNE (VFR only) doors open or removed -Longitudinal CG limits are from station 100 KIAS for any GW. Refer to Type o132.0 to 142.5 for IFR. Operation.

Longitudinal CG limits are from station Maximum airspeed when above maximum132.0 to 144.0 for VFR. continuous torque (87.5%) is 80 KIAS.Rev.2 1-5


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BHT-2121FR-FM-1 FAA APPROVED1-8. ALTITUDE which a safe power off landing can bemade.Maximum operating- 20,000 feet Hp. When takeoffs are made in accordanceRefer to applicable operating rules for high with HV charts, proceed as follows:altitude oxygen requirements. Determine hover torque at a four foot

skid height.Perform takeoff with no more than15% torque above hover power whileaccelerating to Takeoff ClimboutMONITOR ITT WHEN STARTING Speed (VTOCs). Refer to Section 4 forENGINE IN MANUAL FUEL VTOCS.CONTROL MODEAbove 15,000 feet Hp, restart shall be NOTEaccomplished in manual fuel control mode Downwind takeoffs are notonly. (No airspeed restrictions.) recommended since publishedtakeoff distance performance willBelow 15,000 Hp, restart may be attempted not be achieved. When near zeroin either manual or automatic fuel control wind conditions prevail, determinemode. true direction of wind.1-9. MANEUVERING 1-11. AMBIENT TEMPERA-

TURES1-9-A. PROHIBITED MANEUVERS Maximum sea level ambient airAerobatic maneuvers are prohibited. temperature for operation is +52 C (+125F) and decreases with altitude at standardlapse rate (2 C per 1000 feet Hp).1-9-B. CLIMBAND DESCENT Minimum ambient air temperature at allaltitudes is -54 C (-65 F). Refer toRefer to Section 4, PERFORMANCE. Weight-altitude-temperature limitations fortakeoff, landing and in ground effectmaneuvers chart (figure 1-4).1-10. HEIGHT-VELOCITYThe height-velocity limitations are critical 1-12. ELECTRICALin the event of a single engine failureduring takeoff, landing, or other operationnear the surface (figure 1-5). The AVOID 1-12-A. BATTERYarea of the Height-Velocity chart definesthe combinations of airspeed and heightabove the ground from which safe singleNGengine landing on a smooth, level, firmsurface cannot be assured. BATTERY SHALL NOT BE USEDThe H-V chart is valid only when the FOR ENGINE START AFTERWeight-Altitude-Temperature limitations ILLUMINATION OF BATTERYare not exceeded (figure 1-4). The diagram TEMP LIGHT(IF INSTALLED).does not define the conditions which BATTERY SHALL BE REMOVEDassure continued flight following an AND SERVICED IN ACCORDANCEengine failure nor the conditions from WITH MANUFACTURER1-6


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FAA APPROVED BHT-2121FR-FM-1INSTRUCTIONS PRIOR TORETURNING BATTERY TO 28 vdc ground power units for startingSERVICE. shall be rated at a minimum of 400 ampsand limited to a maximum of 1000 amps.Maximum batterycase temperature 54.5 C (130 F)Maximum battery 1-13. POWER PLANTinternalinternal 62.7 C (145 F) PRATT AND WHITNEY CANADA PT6T) 3B and PT6T-3.

1-12-B. GENERATOR NOTEOperation in 2 1/2 minute or 30Maximum - 150 amps per ammeter. minute OEI range is intended foremergency use only, when oneNOTE engine becomes inoperative dueto actual malfunction. OEI rangesTo attain published single engine shall not be used for training.performance, generator loadsshould not exceed 75 amps eachduring twin engine operation. 1-13-A. GAS PRODUCER RPM (N1)

Ammeter needle may deflect full 1-13-A-1. TWIN ENGINEscale momentarily during OPERATIONgenerator assisted start of secondengine. PT6T-3B (Gage P/N 212-075-037-101)Continuous operation 61 to 100.8%1-12-C. STARTER Maximum continuous 100.8%Maximum for takeoff 100.8%Limit starter energizing time to: Maximum transient(not to exceed 3030 seconds - ON. seconds) 102.4%60 seconds - OFF.30 seconds - ON.5 minutes - OFF. NOTE30 seconds - ON. Either gage shall be installed in15 minutes - OFF. pairs.

Above energizing cycle may then be PT6T-3B (Gage P/N 212-075-037-113)repeated. Continuous operation 61 to 101.8%Maximum continuous 101.8%Above 15,000 Hp, restart shall be Maximum 101.8%accomplished in manual fuel control mode MaximumMaximum transient(not to exceed 30Below 15,000 Hp, restart may be attempted seconds) 103.4%in either manual or automatic fuel controlmode. PT6T-3Maximum continuous 100%Maximum transient(not to exceed 10seconds) 101.5%1-12-D. GROUND POWER UNIT

Rev.2 1-7


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BHT-2121FR-FM-1 FAA APPROVED1-13-A-2. ONE ENGINE PT6T-3B (SINGLE ENGINE OPERATION)INOPERATIVE (OEI) 30 Minute OEIrange 765 to 822 C2'/2 Minute OEI range 822 to 850 CPT6T-3B(Gage P/N 212-075-037-101) Maximum OEI 850 C21/2Minute range 100.8 to 102.4%Maximum 102.4%

PT6T-35 Minute range (twinPT6T-3B(Gage P/N 212-075-037-113) engine operation) 765 to 810 C21/2 Minute range 101.8 to 103.4% 30 Minute rangeMaximum 103.4% (OEI) 765 to 810 CMaximum continuouslimit (Single or twin1-13-B. POWER TURBINE RPM engine operation 765transient limit

PT6T-3B or PT6T-3 (Max 5 secondTakeoff 100% above 810 C) 850 C IMinimum 97% Starting transient limitContinuous Operation 97 to 100% (Not to exceed 2Maximum continuous seconds above 810C). 1090 C.operation 100Transient (not toexceed 10 seconds) 101.5% 1-13-D. ENGINE TORQUE

1-13-C. INTERTURBINE NOTETEMPERATURE For normal twin engine operation,maximum permissible torqueneedle split is 4 totalPT6T-3B (TWIN ENGINE OPERATION) needle split is 4% totalContinuous operation 300 to 765 CMaximumcontinuous 765 C 1-13-D-1. ONE ENGINE5 Minute takeoff range 765 to 810 C INOPERATIVE (OEI)Maximumfor takeoff 810 C (ENGINE SCALE)Maximumtransient(Not to exceed 5seconds) 850 C PT6T-3B - TORQUEMETERS MARKEDMaximum for starting 71.8%(Not to exceed 2 Maximumseconds above 960 C 1090 C continuous 63.9%30 Minute power 63.9% to 71.8%Maximum 71.8%

NOTEIf ITT remains above 810 C longer PT6T-3B - TORQUEMETERS MARKEDthan 15 seconds or exceeds other 79.4%limits, ITT and duration shall be Maximumrecorded in helicopter logbook. continuous 63.9%Refer to Pratt and Whitney 30 Minute power 63.9%to 79.4%Maintenance Manual for Maximum 79.4%inspection requirements.

1-8 Rev.2


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FAA APPROVED BHT-2121FR-FMNOTE 1-20. INSTRUMENT

DOD-L-85734AS or MIL-L-23699 is MARKINGS AND PLACARDSrecommended. Refer to Figure 1-1 and 1-2 for Instrumen1-18. ROTOR BRAKE range markings, placards, and decals.Engine starts with rotor brake engaged are 1-21. HEATERprohibited. Rotor brake application islimited to ground operation and shall not Heater shall not be operated when OATbe applied until engines have been shut above 21 C.down and ROTOR RPM (NR) has decreasedto 40% or less. Refer to Appendix A for listing of FligManual Supplements (FMS) coverin1-19. LANDINGGEAR optional equipment kits available.No Flight Manual Limitations

1-11/1


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FAA APPROVED BHT-2121FR-F

(TYPICAL)

PANEL AFT ENDOF OVERHEADCONSOLE

(if installed) 2121FR-FM-1-2-1

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


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BHT-2121FR-FM-1 FAA APPROVED

NOTES:USEDWITHGASPRODUCERAGEP/N 212-075-037-101USEDWITH GASPRODUCERAGEP/N 212-075-037-113

2121FR-FM-1-22

LOCATION: 212-IFR-FM-1-4-2

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

1-20 Rev.1


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11,000

8.000

6,000

5,000132 134 136 138 140 142 144

LONGITUDINALCG STATION INCHES

2121FR-FM-1-3

Figure 1-3. Gross weight center of gravity chart

Rev. 1 1


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BHT-2121FR-FM-1 FAA APPROVED

NOTE: ALLOWABLE GROSS WEIGHTS OBTAINED FROM THIS CHART MAY EXCEEDCONTINUOUS HOVER CAPABILITY UNDER CERTAIN AMBIENTCONDITIONS.REFER TO HOVER CEILINGCHARTS IN SECTION 4

14,000 FT. DEN.ALT. UNIT 14,000

/ -6000

2000

-40 -20 0 20 40 60 8 9 10 11 12 LB X 1000OAT - C 138 42 46 50 54 KG X 100GROSSWEIGHT

2121FR-FM- -4

Figure1-4. Weight-altitude temperature limitations for takeoff, landing and in groundeffect maneuvers chart1-22 Rev. 1


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450NOTE: THEHELICOPTERCONFIGURATIONSHALLCOMPLYWITHTHEWEIGHT-400 ALTITUDE-TEMPERATURECHARTFOR HEIGHT-VELOCITY DIAGRAM

TO BE VALID

350

250250 1000 LBLESS THAN

02

150

50

0 10 20 30 40 50 60 70INDICATEDAIRSPEED - KNOTS

Figure 1-5. Single engine height velocity chart

Rev. 1 1-23/


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FAA APPROVED BHT-2121FR-FM-1

Section 22-1. INTRODUCTION Consult applicable weight and balanceinstructions provided in Section 5.This section contains instructions andThis sectionontains instructions and Determine weight of fuel, oil, load, etc.,procedures for operating helicopter fromplanning stage, through actual flight takeoffand anticipatatedandinconditions, to securing helicopter after GW, and check helicopterCG locations.landing. Ensure weight and balance limitations inSection 1 are not exceeded.Normal and standard conditions areassumed in these procedures. Pertinentdata in other sections is referenced when 2-3. PREFLIGHT CHECKapplicable. Pilot is responsible for determiningInstructions and procedures contained whether helicopter is in condition for safeherein are written for purpose of flight.standardization and are not applicable toall situations.

NOTE2-2. FLIGHT PLANNING Preflight check is not intended tobe a detailed mechanicalPlanning of mission to be accomplished Inspection, but a guide to checkwill provide pilot with data to be used condition of helicopter. Thisduring flight. Information to be used can check may be made asbe compiled as follows: comprehensive as conditionswarrant.

Check type of mission to be performedand destination. All areas checked shall include avisual check for evidence ofSelect appropriate performance charts corrosion, particularly whento be used from Section 4. helicopter is flown near or oversalt water or in areas of highindustrial emissions.2-2-A. TAKEOFF AND LANDINGRefer to Section 1 for takeoff and landing 2-3-A. BEFORE EXTERIORweight limits and to Section 4 for takeoff CHECKand landing data. Flight planning - Completed.2-2-B. WEIGHT AND BALANCE Publications- Check.Determine proper weight and balance of Ensure helicopter has been serviced ashelicopter as follows: required.

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BHT-2121FR-FM-1 FAA APPROVED2-3-B. EXTERIORCHECK Fuel sump drain buttons (left andright) - Press.

Fuel filters - Drain before first flightof day as follows:ENGINE 1 BOOST PUMP andIF HELICOPTER HAS BEEN ENGINE2 BOOSTPUMPswitches -EXPOSED TO SNOW OR ICING ON.CONDITIONS, SNOW AND ICESHALL BE REMOVED PRIOR TO ENGINE 1 FUEL and ENGINE2 FUELFLIGHT. switches - ON.

1. FUSELAGE- FRONT Fuel filters (left and right) - Drainsamples.Rotor blade - Condition andcleanliness. ENGINE 1 FUEL and ENGINE 2 FUELswitches - OFF.Cabin area - Condition, all glassclean. ENGINE 1 BOOST PUMP andENGINE 2 BOOST PUMP switches -Pitot tubes - Covers removed, OFF.unobstructed. BATTERY BUS 1 switch - OFF.Static ports (left and right) -Unobstructed. 2. FUSELAGE - CABIN LEFT SIDERemote hydraulic filter bypass Copilot and passenger doors -Indicator - Check green. Condition and operation, glass clean.Security of emergency releaseCabin nose ventilators - handles.Unobstructed. Position lights - Condition.Nose compartment - Condition anddoors secured. Landing gear - Condition, groundhandling wheels removed.Battery vent and drain tubes -Battery vent and drain tubes Engine air intake - Cover removed,Unobstructed. unobstructed.Searchlight and landing light - 3. FUSELAGE AFT LEFT SIDEAntenna - Condition, security. Drain lines - Clean,unobstructed.

Engine compartment - Check.Fuel sumps - Drain samples asfollows: Engine oil level - Verify presence ofoil in sight gage and proper oil level.ENGINE 1 BOOST PUMP andENGINE2 BOOSTPUMPswitches - Engine governor spring - Condition.OFF. Engine fire extinguisher - BottleENGINE 1 FUEL and ENGINE 2 FUEL pressure gage and temperature range.switches - OFF.BATTERY BUS 1 switch - ON.

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FAA APPROVED BHT-2121FR-FM-Combining gearbox filter - Bypass Engine compartment - Check.indicator retracted. Engine oil level - Verify presence oAccess doors and engine cowling - oil and proper level in sight gage.Secured. Access doors and engine cowling -Engine exhaust ejector tubes - Secured.Covers removed, unobstructed. Fuel filler - Check fuel quantity4. FUSELAGE -AFT secure cap.Tailboom - Condition. 6. FUSELAGE - CABIN RIGHT SIDETail rotor driveshaft covers - removeSecured. Engine air intake - Cover removed*secured. unobstructed.Synchronized elevator - Condition,security z Transmission oil - Verify presence ooil and proper level in sight gage.Main rotor blade - Condition,cleanliness.Removeiedown. Pilot and passenger doors-Condition and operation, glass cleanTail rotor gearbox - Verify presence Security of emergency releaseof oil and proper level in sight gage, handles.filler cap and chip detector plugsecurity. Position lights - Condition.Tail rotor - Condition, free movement Landing gear - Condition, groundon flapping axis. handling wheels removed.Tail rotor yoke - Evidence of static 7. CABIN TOPstop contact damage (deformed staticstop yield indicator).Intermediate gearbox - Verify CAUTIONpresence of oil and proper level insight gage. Filler cap and chip SNOW AND ICE SHALL BEdetector plug security. REMOVED PRIOR TO FLIGHTTail skid - Condition, security. WHEN HELICOPTER HAS BEENEXPOSED TO SNOW OR ICINGSynchronized elevator - Condition, CONDITIONS.security. Main rotor and controls - ConditionTailboom - Condition. fluid levels in all reservoirs.Baggage compartment - Check Transmission oil filler cap - Securedsmoke detector - Condition andsecurity. Cargo and door secured. Hydraulicoil reservoirs - Check sighglasses for proper fluid levels. Cap5. FUSELAGE - AFT RIGHT SIDE secured.Engine fire extinguisher - Bottle Antenna(s)- Condition and securitypressure gage and temperature range. Combining gearbox oil filler cap -Combining gearbox oil level - Verify Securedpresence of oil and proper level Insight gage. Close access door.

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BHT-2121FR-FM-1 FAA APPROVEDAnticolllsion light - Condition and Shoulder harness inertia reel and lock-security. Check.

Flight controls - Freedom of movement,CAUTION position for start.Cyclic - Centered,.friction as desired.

IF ANY TEMP-PLATE IS MISSINGOR HAS BLACK DOTS, Collective - Full down.MAINTENANCE PERSONNELSHALL ASSIST IN DETERMINING Transmission chip detector indicators (ifAIRWORTHINESS. installed) - Check.Main driveshaft and coupling - Lower pedestal circuit breakers- In.Condition, security, and greaseleakage. Check Temp-Plates (four Collective control head switches - OFF.places each coupling) for evidence ofelevated temperature indicated by dot COMPASS CONTROL slaving swltch(es)changing color to black. - MAG (slave position).Engine air intakes - Unobstructed, Radio equipment - OFF.particle separator doors closed. Fuel INTCON switch - NORM.Engine and transmission cowling -Secured. ENGINE 1 BOOST PUMP and ENGINE 2BOOST PUMP switches - OFF.Fresh air inlet screen - Unobstructed. FUEL XFEED switch - NORM.

2-4. INTERIOR AND ENGINE 1 FUEL and ENGINE 2 FUELPRESTART CHECK switches - OFF.Cabin interior - Cleanliness, security of ENGINE NO. 1 PART SEP and ENGINEequipment. NO. 2 PART SEP switches - NORM.Portable fire extinguishers - Proper ENGINE NO. 1 GOV and ENGINE NO. 2charge, secured. GOV switches - AUTO.Passenger seats - Secured, each HYDR SYS NO. 1 and HYDR SYS NO. 2occupied seat equipped with seat belt. switches - ON.Crew and passengerdoors - Secured. STEPswitch (if Installed) - As desired.Cargo load - Secured. FORCE TRIM switch - ON, cover down.Protective breathing equipment (if Instruments Staticcheck.required) - Condition and properlyserviced. STATIC SOURCEswitch (if installed) -PRI.Seat and pedals - Adjust. Altimeter(s) - Set.Seat belt and shoulder harness -Fasten and adjust. Clock - Set and running.

FIRE EXT switch - OFF.2-6


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FIRE PULL handles In (forward).

AFT DOME 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 (if installed)

As desired.

NAV AC switch 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 2

switches ON, check BATTERY caution

light illuminates.

NOTETest all lights when night flights are

planned or anticipated. Accomplish

light tests with external power

connected or during engine runup.

MASTER CAUTION switch (overhead)

TEST, check all caution panel lights

ext inguish except CAUTION PANE

segment and MASTER CAUTION light. (Bot

ENG OUT lights and RPM light will dim

during test.)

CAUTION

ROTOR BRAKE HANDLE SHALL

BE IN DETENT POSITION (OFF) AT

ALL TIMES WHEN ENGINES ARE

RUNNING.

ROTOR BRAKE lights Test. Pull brak

lever and check that both lights illuminate

return to off and check lights extinguish.

FIRE PRESS TO TEST switch Press an

release. FIRE PULL 1 and FIRE PULL warning lights illuminate when switch i

pressed and extinguish when switch i

released.

BAGGAGE FIRE warning light TEST butto

Press to test (verify light flashes).

CARGO RELEASE ARMED light (if installed

TEST.

Caution panel lights TEST and RESET.

INV 1 switch ON, check no. 1 AC voltmete

for 104 to 122 volts.

INV 2 switch ON, check no. 2 AC voltmete

for 104 to 122 volts.

FUEL QTY SEL switch LEFT, then RIGHT

check fuel quantity gauge indicates lowe

fuel cell quantity of 270 to 300 pound

(each).

2-5. ENGINE START

NOTE

If helicopter has been cold soaked

in ambient temperature of -18 C

....

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FAA APPROVED BHT-2121FR-FM-1GAS PROD RPM (N,) - Check 61 1% Engine 2 throttle - Open to Idle at 12%when throttle is on idle stop. GAS PROD RPM (N1) minimum.

Engine 2 ITT - Monitor. Observe ITTIf battery start: limitations.GAS PROD RPM (N1) - 71%. START switch - Off at 55% GAS PRODRPM (N1)GEN 1 switch - ON.

GAS PROD RPM (N1) - Check 61 + 1%AMPS 1 - Check at or below 150 amps. when engine 2 throttle is on Idle stop.NOTE CAUTIONDuring extremely cold ambienttemperatures, idle rpm will behigh and ENGINE OIL, XMSN OIL, ENSURE SECOND ENGINEand GEAR BOX OIL pressures ENGAGES AS THROTTLE ISmay exceed maximum limits for INCREASED. A NON-ENGAGEDup to 2 minutes after starting. ENGINE IS INDICATED BY 10 TO15% ENG RPM (N2) HIGHER THANDo not increase ROTOR RPM (NR) ENGAGED ENGINE AND NEARabove 80% until XMSN OIL ZERO TORQUE. IF A NON-temperature is above 15 C. ENGAGEMENT OCCURS, CLOSETHROTTLE OF NON-ENGAGED

ENGINE OIL, XMSN OIL, AND GEAR BOX ENGINE. WHEN NON-ENGAGEDOIL pressures - Check. ENGINE HAS STOPPED, SHUTDOWN ENGAGED ENGINE.ENG 1 PART SEP OFF caution light -Extinguished. IF S U D D E N ( H A R D)ENGAGEMENT OCCURS, SHUTEngine 1 throttle - Increase to 85% ENG DOWN BOTH ENGINES.RPM (N2). Friction as desired. MAINTENANCE ACTION ISREQUIRED.

2-5-B. ENGINE 2 START Engine 2 throttle - Increase slowly to85% ENG RPM (N2). Monitor tachometerENGINE 2 BOOST PUMP switch - ON, and torquemeter to verify engagement ofcheck ENG 2 FUEL BOOST caution light second engine.extinguished (FUEL XFEEDcaution lightwill illuminate momentarily). Engine 2 ENGINE OIL pressure - Check.ENGINE 2 FUEL switch - ON. (ENG 2 ENG 2 PART SEP OFF light -FUELVALVE caution light will illuminate Extinguished.momentarily.)Engine 2 FUEL PRESS - Check. 2-5-C. POST STARTSTART switch - ENG 2 position. External power - Disconnect if used,Observe starter limitations. GEN 1 switch - ON.Engine 2 ENGINE OIL pressure - GEN 2 switch - ON (BATTERY BUS 1Indicating. will switch OFF automatically).

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BHT-2121FR-FM-1 FAA APPROVED2-5-E. DRY MOTORING RUNCAUTIONFollowing procedure is used to clear an

IF OPERATING ON BATTERY BUS engine whenever it Is deemed necessary to1, POSITION INV 3 SWITCH TO ON remove internally trapped fuel and vapor:DC BUS 1. Throttle - Fully closed.ONLY ONE BATTERY SWITCHSHALL BE ON DURING FLIGHT. ENGINE (1 or 2) BOOST PUMP switch -ON.Caution lights - Check all extinguished. ENGINE (1 or 2) FUEL switch - ON.

ENGINE OIL, XMSN OIL, and GEAR BOXOIL temperatures and pressures - ENGIGN SYScircuit breaker-Pull out.Within limits. STARTswitch - Engagefor 15 seconds,AMPS 1 and AMPS 2 - Within limits, then disengage.ENGINE (1 or 2) FUEL switch - OFF.NOTE

AMPS 2 will indicate a higher load ENGINE (1 or 2) BOOST PUMP switch -than AMPS 1 until battery is fully OFF.charged. ENG IGN SYS circuit breaker - In.Radios- ON as required. Allow required cooling period for starterELT (if installed) - Check for before proceeding. Follow normal startinadvertent transmission. sequence as described on precedingpages. Refer to SECTION 1, STARTERLIMITATIONS.2-5-D. ENGINE FAILS TO STARTWhen engine fails to light off within 15 2-6. SYSTEMS CHECKseconds after throttle has been openedto idle, following action isrecommended: 2-6-A. FORCE TRIM CHECK

IDLESTOP REL switch - Actuate. Flight controls - Friction off; collectivelock removed.Throttle - Fully closed. Cyclic and pedals - Move slightly eachSTARTswitch - OFF. direction to check force gradients.ENGINE (1 or 2) BOOST PUMP switch Cyclic FORCE TRIM release button -- OFF. Press; check trim releases with buttonpressed, reengages with buttonENGINE (1 or 2) FUEL switch - OFF. released.

After GAS PROD RPM (N 1) has FORCETRIM switch - OFF; check trimdecreased to zero, allow 30 seconds for disengages and FT OFF caution lightfuel to drain from engine. Conduct a illuminates.DRY MOTORING RUN before attemptinganother start. FORCE TRIM switch - ON.2-10 Rev. 2


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FAA APPROVED BHT-2121FR-FM2-6-B. PRELIMINARY HYDRAULIC RPM INCR DECR switch - INCR to 100CHECK (N2).

Throttles - Set to idle. 2-6-E. FUEL CROSSFEED VALVECHECKNOTE NOTE FUEL XFEED test switch - TEST BUSUncommanded control movement and hold.or motoring with either hydraulicsystem off may indicate hydraulicsystem malfunction. NOTE

If, after turning either boost pumpHYDR SYS NO. 1 switch - OFF, then off, fuel pressure remains 4 to 6psi below normal (10 4 psi),appropriate check valve is notHYDR SYS NO. 2 switch - OFF, then functioning properly.ON.ENGINE 1 BOOST PUMP switch - OFCheck no. 1 FUEL PRESS decreases2-6-C. ENGINE FUEL CONTROL then returns to normal. (This indicateCHECK that crossfeed valve has opened by buno. 1 power and check valve Throttles - Idle. functioning properly.) ENGINE 1 BOOSPUMP switch - ON.

NOTE FUEL XFEED test switch - TEST BUSand hold.Do not allow GAS PROD RPM (N1)to decrease below 50%. ENGINE 2 BOOST PUMP switch - OFCheck no. 2 FUEL PRESS decreasesAround 8000 feet Hp, GAS PROD then returns to normal. ENGINERPM (N 1) may not change BOOSTPUMPswitch - ON.significantly when manual fuelcontrol is selected. FUEL XFEED test switch - NORM.GOV switch (ENGINE NO. 1 or 2) - FUEL XFEED switch - OVRD CLOSE.MANUAL, observe change in GAS PRODRPM (N1 ). Open respective throttle ENGINE 1 (or ENGINE 2) BOOST PUMcarefully to assure GAS PROD RPM (N1) switch - OFF. Check fuel pressureresponds upward, then return throttle to drops to zero on selected systemidle. Return GOV switch to AUTO. ENGINE 1 (or ENGINE 2) BOOST PUMCheck for return to original GAS PROD switch - ON.RPM (N1 ). Check other governor in samemanner. FUEL XFEED switch - NORM.

2-6-D. GOVERNOR CHECK 2-6-F. ELECTRICAL SYSTEMSCHECKNo. 1 throttle - Full open. Check ENGRPM (N2 ) stabilizes at 95 1%. DC voltmeters - Check 27 1 vdc.No. 2 throttle - Full open. Check no. 1 AC voltmeters - Check 104 to 122 vacengine ENG RPM (N2 ) increases 2% andboth engines stabilize at 97 1% N2 . Ammeters - Check within limits.

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BHT-2121FR-FM-1 FAA APPROVEDAC system - Check as follows: light illuminates, then extinguishes afterseveral seconds.INV 3 switch - ON DC BUS 2, checkINVERTER 3 caution light Cyclic - Move laterally and hold. Checkextinguishes. that roll NO GO light Illuminates, thenextinguishes after several seconds.INV 2 switch - OFF, INVERTER 2 Return to neutral.

caution light illuminates. Check no. 2AC voltmeter for indication that Pedals - Move and hold. Check thatinverter no. 3 has assumed load. INV yaw NO GO light illuminates, then2 switch - ON. INVERTER2 caution extinguishes after several seconds.light extinguishes. Return pedals to neutral.INV 3 switch - OFF, then ON DC BUS SCAS switch - ENGA, SCAS lights1, check INVERTER 3 caution light illuminate.extinguishes. SCAS switch - DSENGA, SCAS lightsINV 1 switch - OFF, INVERTER 1 extinguish.caution light illuminates. Check no. 1AC voltmeter for indication that SCAS switch - ENGA, SCAS lightsinverter no. 3 has assumed load. INV illuminate.1 switch - ON. INVERTER 1 cautionlight extinguishes. INV 1 switch - OFF, SCAS disengages.INV 3 switch - OFF, INVERTER 3 INV 1 switch - ON, check no. 1 ACcaution light illuminates. INV3 switch voltmeter for 104 o 122volts.- ON DC BUS 2, INVERTER 3 cautionlight extinguishes. SCAS switch - ENGA, SCAS lightsilluminate.

2-6-G. AFCS CHECK Pilot AFCS RELEASE - Press, SCASdisengages.NOTE NOTE SCAS switch - ENGA, SCAS lightsAFCS mode operation is illuminate.annunciated on instrument panelby a three segment light (PITCH, Copilot AFCS RELEASE - Press, SCASROLL, YAW). AFCS functions In disengages.two modes - automatic with turnand trim functions, and pilot SCAS switch - ENGA, SCAS lightscyclic steering. AFCS illuminate.annunciation is applicable to bothmodes. FORCE TRIM - ON, cover down.

AFCS power - ON. ATTD switch - ENGA, AFCS lightsilluminate, SCAS ights extinguish.Channel arm switches - ATTD. ATTD switch - DSENGA, AFCS lightsSCAS NO GO lights - Illuminated, extinguish, SCAS ights Illuminate.should extinguish within severalseconds to Indicate system null. Wait ATTD switch - ENGA, AFCS lightsfor lights to extinguish. illuminate, SCAS ights extinguish.

Cyclic - Move forward and hold, then Pilot AFCS RELEASE - Press, AFCSaft and hold. Check that pitch NO GO lights extinguish, SCAS disengages.2-12


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FAA APPROVED BHT-2121FR-FM-1SCAS switch - ENGA, SCAS lights laterally. Cyclic should follow andilluminate. AFCS ROLL light remain illuminated.Center cyclic using cyclic FORCEATTD switch - ENGA, AFCS lights TRIM switch.illuminate, SCAS lights extinguish. Turn - Actuate turn knob throughCopilot AFCS RELEASE - Press, AFCS cycle. Cyclic should follow and AFCSCopilot AFCS RELEASE - Press, AFCS PITCH and ROLL remainPITCH and ROLL lights remainlights extinguish, SCASdisengages. illuminated, AFCS YAW lightextinguishes. Center cyclic usingcyclic FORCE TRIM switch.CAUTION AFCS pilot cyclic steering mode -Check as follows:MONITOR ALL CONTROLS TOE N S U R E CONTROL Pitch - Displace cyclic slightlyDEFLECTIONS ARE NOT forward and release. AFCS PITCHEXCESSIVE DURING AFCS light extinguishes and SCAS PITCHCHECK. light illuminates. Displace cyclicslightly aft and release. AFCS PITCHSCAS switch - ENGA. light extinguishes and SCAS PITCHCAS switch- ENGA. light illuminates.ATTD switch - ENGA. Roll - Displacecyclic slightly left andrelease. AFCS ROLL light

NOTE extinguishes and SCAS ROLL lightilluminates. Displacecyclic slightlyright and release. AFCS ROLL ightCyclic friction must be properly right and release. AFCS ROLL lightset for proper AFCS operation, extinguishes and SCAS ROLL lightFriction adjust ring must neitherbe tightly compressed against Yaw - Displace left pedal slightlyminimum friction bracket nor be forward and release. AFCSYAW lightexcessively tight. extinguishes and SCAS YAW lightilluminates. Displace right pedalCyclic friction - Adjust. slightly forward and release. AFCSYAW light extinguishes and SCASAFCS automatic mode - Check as YAW light illuminates.follows:

Pitch - Actuate pitch trim wheel CAUTIONthrough cycle. Cyclic should followand AFCS PITCH light remainilluminated. Center cyclic using cyclic CYCLIC CONTROLS MAY MOTORFORCE TRIM switch. Actuate AFCS TO STOP IF AFCS IS LEFTTRIM switch forward and aft. Cyclic ENGAGED AND UNMONITOREDshould follow and AFCS PITCH light DURING GROUND OPERATIONS.remain illuminated. Center cyclicusing cyclic FORCETRIM switch. FOR PROLONGED GROUNDOPERATION, AFCS SHALL NOTRoll - Actuate roll trim wheel through BE OPERATED IN ATTD MODE.cycle. Cyclic should follow and AFCSROLL light remain illuminated. Centercyclic using cyclic FORCE TRIMswitch. Actuate AFCS TRIM switch

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BHT-2121FR-FM-1 FAA APPROVEDATTDswitch - DSENGAprior to takeoff. VENT BLOWERswitch - As desired.

2-6-H. CABIN HEATER CHECK 2-6-J. HYDRAULIC SYSTEMCHECKGAS PROD RPM (N,) - Check 75%minimum (both engines). NOTEAIR COND TEMP CONT switch - FullyCOOL. This check is to determine properoperation of hydraulic actuatorsfor each flight control system. Ifabnormal forces, unequal forces,CAUTION control binding, or motoring isencountered, it may be anindication of a malfunction of aSYSTEM SELECTOR SWITCH flight control actuator.SHALL BE TURNED OFF WHENHEATED AIRFLOW DOES NOT FORCE TRIM switch - OFF.SHUT OFF AFTER AIR CONDTEMP CONT SWITCH IS TURNED Collective - Down, friction removed.TO FULLY COLD, HEATER AIRLINE CAUTION LIGHT ROTORRPM(NR)- Set to 100%.ILLUMINATES, OR CABIN HTRCIRCUIT BREAKER TRIPS. Cyclic - Centered, friction removed.DO NOT OPERATE HEATERABOVE 21 C OAT. Hydraulic system - Check as follows:

HYDR SYS NO. 1 switch - OFF.SYSTEM SELECTOR switch - HEATER. CheckCheck MASTER CAUTION andVENT BLOWERswitch - ON. HYDRAULICcaution lights Illuminateand hydraulic system no. 1 pressureAIR COND TEMP CONT switch - Rotate decreases.counterclockwise and observe heatedyclic - Check normal operation byCyclic - Check normal operation byairflow. moving cyclic in an 'X' pattern rightforward to left aft, then left forward toDEFOG lever - ON; check airflow is right aft (approximately 1 inch).diverted from pedestal outlets to Centercyclic.windshield nozzles. Return lever toOFF. Collective - Check normal operationby Increasing collective slightly (1 to 2AFT OUTLET switch - ON; check inches). Return to down position.airflow distributed equally betweenpedestal outlets and aft outlets. Returnswitch to OFF. NOTE

Boost for tail rotor controls isNOTE furnished by hydraulic system no.1 only. When hydraulic systemHeater operation affects no. 1 is being checked, tail rotorperformance. Refer to Hover controls will be unboosted.Ceiling and Rate of Climb chartsfor HEATER ON in Section 4.SYSTEM SELECTOR switch - Asdesired.

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FAA APPROVED BHT-2121FR-FM-1Pedals - Displace slightly left andright. Note an increase in force WARNINGrequired to move pedals.

BOTH HYDRAULIC SYSTEMSWARNING SHALL BE OPERATIONAL PRIORTO TAKEOFF.DO NOT TURN BOTH HYDRAULIC NOTESYSTEMS OFF AT SAME TIMEDUE TO EXCESSIVE FORCE System 1 will normally operate 10REQUIRED TO MOVE FLIGHT to 20 C cooler than system 2.CONTROLS.HYDR SYS NO. 1 switch - ON. Check 2-7. BEFORE TAKEOFFMASTER CAUTION and HYDRAULICcaution lights extinguish and Engine, transmission, gearbox,hydraulic system no. 2 pressure hydraulic, and electrical Instruments -returns to normal. Check readings within operationalHYDR SYS NO. 2 switch - OFF. range.Check MASTER CAUTION and Flight instruments - Check operationHYDRAULICcaution lights illuminate and set.and hydraulic system no. 2 pressuredecreases. Attitude indicators - Erect and set.Cyclic - Check normal operation bymoving cyclic in an 'X' pattern, right NOTEforward to left aft, then left forward toright aft (approximately 1 Inch). If fast slaving is desired,set rollCenter cyclic. trim to null, push and hold VGFAST ERECT switch (if installed)Collective - Check normal operation until attitude indicator displaysby increasing collective slightly (1 to 2 zero degrees bank angle.inches). Return to down position. Turn and slip indicators - Operative.Pedals - Displace slightly left andright. Note no increase in force HSls - Slaved and heading correct,required to move pedals. course bar and bearing pointers set toproper navigation receivers.HYDR SYS NO. 2 switch - ON. CheckMASTER CAUTION and HYDRAULICcaution lights extinguish andhydraulic system no. 1 pressure CAUTIONreturns to normal.

Cyclic and collective friction - As INDICATOR IS CPLT/PLTdesired. INDICATOR IS ILLUMINATED,CHANGING COURSE SETTING ONHSI OF COPILOT/PILOT INORCE TRIM switch-ON. COMMAND WILL CHANGECOURSE SETTING ONREMAINING HSI (IF INSTALLED).Magnetic compasses - Fluid level andheading.

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BHT-2121FR-FM-1 FAA APPROVEDAltimeters - Set. 2-7-B. PROLONGED GROUNDVertical speed indicators - Zero. OPERATIONClocks - Set and running. NOTECommunication and navigation For prolonged ground operation,equipment - Set and functioning. AFCS shall not be operated inATTD mode.Position lights - As required.Anti-collision lights - As required. 2-8. TAKEOFFPitot heater - As required. ENG RPM (N2) - 100%.Cyclic - Fiction as desired.

NOTENOTE No more than 15% torque aboveModerate friction shall be applied hover power shall be usedto each throttle to overcome accelerating to Takeoff Climboutfollow-through coupling between Speed.twist grips. Collective - Initiate takeoff from a hoverThrottles - Full open, friction adjusted. height of 4 feet.

ENG RPM (N2) - 100% (both engines).FORCE TRIM switch - As desired.COCKPIT VOICE RECORDER TESTswitch (if installed)-- press and hold for OBSER VE VMINITS IN3 seconds. Verify meter indicates GOOD. SECTION 1 FOR IFR OPERATION.Passenger STEPswitch (if installed)- NOTEAs desired. Takeoff must be executed inPassenger seat belts - Fastened. accordance with Height-Velocitylimitations for type of operationAll doors- Secured. being conducted. Refer toSection 1.Caution and warning lights -Extinguished. Refer to Section 4 for additionalclimb performance data.

2-7-A. POWER ASSURANCECHECK ATTD switch - ENGA as desired above40 KIAS.Perform power assurance check daily.Refer o Section 4. 2-9. IN-FLIGHT OPERATIONS

Maneuvering with AFCS on may beaccomplished by one of followingmethods:2-16 Rev. 2


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FAA APPROVED BHT-2121FR-FMto maintain balanced flight duringturning maneuver. CAUTION

Method 3:Method 3: CYCLIC CONTROLS MAY MOTORPress cyclic FORCE TRIM switch and TO STOP IF AFCS IF LEFTmaneuver as desired. Release switch ENGAGED AND UNMONITOREDwhen maneuver is complete and with DURING GROUND OPERATIONS.helicopter at level attitude. Collective - Down.

2-10. DESCENT AND Cyclic control and pedals - Centere2-10LANDIN and frictioned.FORCE TRIM switch - ON.Flight controls - Adjust friction asdesired. Throttles - Idle.

Throttles - Full open. ITT - Stabilize for one minute at idprior to shut down.ENG RPM (N2) - 100%. Engine instruments - Within limits.FORCE RIMswitch As desired. ELT (if installed) - Check fo

inadvertent transmission.Passenger STEP switch - As desired.Radios - OFF.

WARNING IDLE STOP REL switch - ENG 1.Engine 1 throttle - Closed. Check ITOBSERVE VMIN LIMITS IN and GAS PROD RPM (N1) decreasing.SECTION 1 FOR IFR OPERATION.BATTERY BUS 1 switch - ON.Flight path - Establish in accordancewith Height-Velocity diagram. Single IDLE STOP REL switch - ENG 2.engine balked landings can be madefrom a landing decision point (LDP) of Engine 2 throttle - Closed. Check IT100 feet altitude, 40 knots airspeed, and and GAS PROD RPM (N.) decreasing.500 feet rate of descent. Anticipatedsingle engine landings initiated from GEN 1 and GEN 2 switches - OFF.these conditions require reference tolanding performance data in Section 4. INV 1, INV 2, and INV 3 switches - OF

ATTD switch - DSENGA as desired. ENGINE 1 FUEL switch - OFF.ENGINE 1 BOOST PUMP switch - OFFNOTE ENGINE 2 FUEL switch - OFF.ATTD switch must be disengagedbelow 40 knots. ENGINE 2 BOOST PUMP switch - OFF

2-11. ENGINE SHUTDOWNAFCS power - OFF.

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FAA APPROVED BHT-2121FR-FM

2121FR-FM-2-1

Figure 2-1. Exterior check diagram

2-19/2


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FAA APPROVED BHT-2121FR-FM-1

Section 3TABLE OF CONTENTS PageSubject Paragraph Number

INTRODUCTION ................................................. 3-1 ........... 3-3DEFINITIONS................................................... 3-2........... 3-3ENGINE......................................................... 3-3........... 3-3SINGLE 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 CONTROLGOVERNORFAILURE .................................................... 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 ....... 3-9FIRE....................................................... 3-4.......... 3-9ENGINE FIRE............................................... 3-4-A ....... 3-9CABIN SMOKE OR FUMES................................. 3-4-B ...... .. 3-10BAGGAGE COMPARTMENT FIRE.......................... 3-4-C ........ 3-10TAIL 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 ORDESCENT ................................................... 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 ....... 3-12FIXED PITCH FAILURE IN FLIGHT......................... 3-5-H ........ 3-12LOSS OF PITCH CHANGE CONTROL LINKAGE .......... 3-5-J......... 3-14HYDRAULIC SYSTEM ........................................... 3-6.......... 3-14ELECTRICAL SYSTEM .......................................... 3-7 .......... 3-14DC POWER FAILURE....................................... 3-7-A ....... 3-14AC FAILURE TO PRODUCE POWER...................... ..3-7-B .... 3-14AC FAILURE SYSTEM NO.1.............................. 3-7-C ........ 3-14AC FAILURE SYSTEMNO. 2 .................................................... ... 3-7-D........ 3-14FUEL SYSTEM..................................... 3-8...........3- 3-15FUEL BOOST PUMP FAILURE ............................. 3-8-A ........ 3-15FUEL FILTER PARTIALLY BLOCKED ...................... 3-8-B ........ 3-15FUEL QUANTITY INDICATION MALFUNCTIONS ........ ... -8-C ........ 3-15AUTOMATIC FLIGHT CONTROLS SYSTEM .................... 3-9........... 3-15AFCS WILL NOT ENGAGE ANY CHANNEL............... 3-9-A ........ 3-15

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BHT-2121FR-FM-1 FAA APPROVEDTABLE OF CONTENTS (Cont) PageSubject Paragraph Number

AFCS WILL NOT ENGAGE YAW CHANNEL ONLY ....... 3-9-B ........ 3-16FEEDBACK FELT IN CYCLIC DURING SCAS ONLYFLIGHT...................................................... 3-9-C........ 3-16OSCILLATIONS IN AFCS ANY CHANNEL................. 3-9-D ........ 3-16HYDRAULIC FAILURE SYSTEM NO. 1.................... 3-9-E ........ 3-16SYSTEM REENGAGE AFTER DISENGAGE ................ 3-9-F......... 3-16INOPERATIVE CHANNEL SCAS........................... 3-9-G ........ 3-16INOPERATIVE CHANNEL AFCS ........................... 3-9-H ........ 3-16INOPERATIVE ATTITUDE GYRO COPILOT ............... 3-9-J......... 3-16INOPERATIVE HEADING GYRO COPILOT ................ 3-9-K ........ 3-17HYDRAULIC FAILURE SYSTEM NO. 2 .................... 3-9-L......... 3-17AFCS RUNAWAY, HARDOVER, OR OTHER UNUSUALCHARACTERISTIC .......................................... 3-9-M ........ 3-17EMERGENCY EVASIVE MANEUVER ....................... 3-9-N ........ 3-17COMMUNICATION SYSTEM ..................................... 3-10 ......... 3-17NAVIGATION RADIO FAILURE ............................. 3-10-A ....... 3-17INTERCOM FAILURE ....................................... 3-10-B ....... 3-17CABIN HEATER ................................................. 3-11 ......... 3-17LANDING GEAR ................................................. 3-12 ......... 3-18STATIC PORT OBSTRUCTION .................................. 3-13 ......... 3-18

LIST OF FIGURES Figure PageTitle Number Number

LIST OF TABLES Table PageTitle Number NumberWARNING LIGHTS .............................................. 3-1 ........... 3-19CAUTION LIGHTS ............................................... 3-2........... 3-21

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Section 3

EMERGENCY/MALFUNCTION PROCEDURES

3-1. INTRODUCTION

Following procedures contain indications of

equipment or system failure or malfunction,

use of emergency features of primary and

backup systems, and appropriate warnings,

cautions, and explanatory notes. Table 3-1

lists fault conditions and corrective actions

required for illumination of red warning lights.

Table 3-2 addresses malfunction proceduresassociated with yellow caution lights.

Corrective action procedures listed herein

assume pilot gives first priority to helicopter

control and a safe flight path.

Helicopter should not be operated following

any precautionary landing until cause of

malfunction has been determined and

corrective maintenance action taken.

3-2. DEFINITIONS

Following terms indicate degree of urgency in

landing helicopter.

LAND AS SOON AS POSSIBLE Land

without delay at nearest suitable area (i.e.,

open field) at which a safe approach and

landing is reasonably assured.

LAND AS SOON AS PRACTICAL Duration of

flight and landing site are at discretion of pilot.Extended flight beyond nearest approved

landing area is not recommended.

Following terms are used to describe

operating condition of a system, subsystem,

assembly, or component:

AFFECTED Fails to operate in intended o

usual manner.

NORMAL Operates in intended or usua

manner.

3-3. ENGINE

3-3-A. SINGLE ENGINE FAILUREENG RPM (N2) of operating engine is allowe

to droop to 97% during transition from twi

engine operation to single engine operation

When best rate of climb airspeed (58 KIAS) i

attained, ENG RPM (N2) should be increased t

100% if possible.

Flight can be continued on remaining engin

until a desirable landing site is available. Ther

are certain combinations of GW, altitude, an

ambient air temperatures that will result in OEtorque limit being exceeded. A run-on landin

at 20 to 30 knots is recommended.

Loss of an engine while hovering at high GW

and extremely cold conditions is likely t

result in exceeding OEI torque limit. If a

overtorque is observed or suspected, an entr

sha l l be made in log book. Refer t

performance charts in Section 4.

NOTE

Refer to ENGINE RESTART if an

engine restart is to be attempted.

INDICATIONS:

ENG 1 OUT or ENG 2 OUT warning ligh

illuminated.

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GAS PROD RPM (NI) below 61 1% and

decreasing.

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 caution

lights 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 R

OPERATIONS, MONITOR TORQUE

OF OPERATING ENGINE WHEN

ONE ENGINE FAILS OR IS SHUT

DOWN IN FLIGHT.

Shut down affected engine as follows:

Collective Reduce as required to maintain

ROTOR RPM (NR) within limits and powerwithin OEI limits.

NOTE

Airspeed 55 to 65 KIAS for

Minimum Power for level flight.

RPM INCR DECR switch INCR, set

remaining 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.

ENGINE (1 or 2) FUEL switch OFF.

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).

BATTERY BUS 2 switch OFF.

BATTERY BUS 1 switch ON.

MASTER CAUTION light Reset.

Land as soon as practical.

3-3-B. ENGINE RESTART IN FLIGHT

Conditions which would warrant an attempt to

restart an engine would probably be a

flameout, caused by a malfunction of

automatic mode of fuel control unit. Decision

to attempt an engine restart during flight is

pilot responsibility. If an engine restart is to be

made, proceed as follows:

CAUTION

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

CONTROL MODE.

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 2 switches ON.

INV 3 switch (if equipped) ON DC

BUS 1.

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FAA APPROVED BHT-2121FR-FM-1START switch-ENG 1. PROD RPM (N.) is attained. Adjustengine to desired power level. CareAfter 12% GAS PROD RPM (N|) is must be taken to make smallattained and oil pressure is indicating, adjustments with throttle asslowly open throttle until a rise is compressor stall may result.seen in ITT which indicates engine isself sustaining. Do not open throttle GEN 2 switch - ON.farther until GAS PROD RPM (N|) andITT are stabilized. Continue to openthrottle slowly to complete start. 3-3-C. DUALENGINEAILURECenter START switch after 55% GASPROD RPM (N|) is attained. Adjust INDICATIONS:engine to desired power level. Caremust be taken to make small ENG 1 OUT and ENG 2 OUT warningadjustments with throttle as lights illuminated.compressor stall may result. RPMcaution light illuminated.GEN 1 switch - ON. ROTOR RPM audio on.BATTERY BUS 1 switch - OFF.

GAS PROD RPM (N|) below 61 1% andBATTERY BUS 2 switch - ON. decreasing (both engines).ENGINERESTART NO. 2) ENG RPM (N2 ) below 85% anddecreasing (both engines).

Engine 2 throttle - Closed. ITT below 400 C and decreasing (bothENGINE 2 BOOST PUMP switch - ON. engines).Fuel Crossfeed switch - Normal ENG 1 and ENG 2 OIL PRESSURE, DCGENERATOR, and PART SEP OFFENGINE2 FUELswitch - ON. caution lights illuminated.ENGINE NO. 2 GOV switch - PROCEDURES:MANUAL.BATTERY BUS 1 switch - OFF. WARNINGBATTERY BUS 2 switch - ON. DO NOT ALLOW ROTOR RPM (NR)INV 1 and 2 switches - ON. TO DECAY BELOW MINIMUMLIMITS.INV 3 switch (if installed) - ON DCBUS . Collective - Reduce, establishautorotative glide. Minimum rate ofSTART switch - ENG 2. descent (65 KIAS) or maximum glide (90KIAS).After 12% GAS PROD RPM (N|) isattained and oil pressure is indicating, Autorotative landing - Accomplish.slowly open throttle until a rise isseen in ITT which Indicates engine isself sustaining. Do not open throttle If time permits before landing and afarther until GAS PROD RPM (N|) and restart will not be attempted, proceedITT are stabilized. Continue to open as follows:throttle slowly to complete start.Center START switch after 55% GAS Throttles - Closed.

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BHT-2121FR-FM-1 FAA APPROVEDENGINE 1 and ENGINE 2 FUEL switches audio if power demand is in excess of- OFF. single engine power available).ENGINE 1 and ENGINE 2 BOOST PUMP TORQUE split (proportional to powerswitches - OFF. demand).After landing: Low GAS PROD RPM (N1), ITT, andTORQUE on affected engine.Engine shutdown - Complete. PROCEDURES:Helicopter - Exit.

3-3-D. ENGINE UNDERSPEEDROTOR RPM (NR) CAN DECAYNOTE EXCESSIVELY IF CORRECTIVEACTION IS NOT IMMEDIATELYNormal deviations of ROTOR RPM

(NR) from the governed settingmay occur when large collective Collective - Adjust as necessary tochanges are made but should notbe confused with fuel control mantan ROTOR PMNR).failure, unless a large steady-stateTORQUEsplit occurs. Airspeed - 55 to 65 KIAS for MinimumPower for level flight.If there is a low power demand (less thansingle engine power available) at time of Affected engine - Identify.low side failure, ROTOR RPM (NR) and ENGRPM (N2) of affected engine will decrease Throttle friction - Tighten on normaland stabilize, at or slightly below governed engine, reduce on affected engine.value. TORQUE, ITT, and GAS PROD RPM(N1)of affected engine will also decrease. Throttle (affected engine) - Reduce toAs ROTOR RPM (NR) decreases, normal idle.engine will increase TORQUE output toassume load. If power demand is near GOV switch (affected engine) -zero, there might not be a significant MANUAL.TORQUE split.If there is a high power demand (greater CAUTIONthan single engine power available) at timeof low side failure, ROTOR RPM (NR) willdecrease along with ENG RPM (N2 ), WHEN OPERATING IN MANUALTORQUE, ITT, and GAS PROD RPM (N1) of FUEL CONTROL MODE, MAKEaffected engine. As ROTOR RPM (NR) SLOW, SMOOTH THROTTLEdecreases, normal engine will increase to MOVEMENTS TO AVOIDmaximum power to assume load, causing COMPRESSOR STALL,significant increases in TORQUE, ITT, and OVERTEMPERATURE, OVER-GAS PROD RPM (N1) while ENG RPM (N2) SPEED, AND POSSIBLEwill remain below governed value. DRIVETRAIN DAMAGE.INDICATIONS: COORDINATE THROTTLE ANDCOLLECTIVE CHANGES TOLow ENG RPM (N2) and ROTOR RPM (NR) AVOID OVERLOADING NORMAL(possibly with RPM caution light and ENGINE.3-6 Rev.2


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FAA APPROVED BHT-2121FR-FM-Throttle (affected engine) - Increase Definite TORQUE split (proportional toslowly. Adjust throttle and collective as power demand).required to maintain TORQUEof affectedengine slightly below TORQUE of normal High GAS PROD RPM (N), ITT, andengine. TORQUEon affected engine.MASTER CAUTION light - Reset. Return of ENG RPM (N2) and ROTOR

RPM (NR) to governed value (if poweLand as soon as practical. demand is very high).3-3-E. ENGINE OVERSPEED - FUEL PROCEDURES:CONTROL/GOVERNOR FAILURE

CAUTIONNOTENormal deviations of ROTORRPM ROTOR RPM ( N) CAN(NR) from the governed setting OVERSPEED EXCESSIVELY IFmay occur when large collective CORRECTIVE ACTION IS NOTchanges are made but should not IMMEDIATELY INITIATED.be confused with fuel controlfailure, unless a large steady-state Collective - Adjust as necessary toTORQUE split occurs, maintain ROTOR RPM (NR).

If there is a low power demand (less than Affected enine - Identifysingle engine power available) at time ofhigh side failure, ROTOR RPM (NR) and Throttle (affected engine) - Reduce toENG RPM (N2 ) of affected engine will maintain TORQUE at or slightly belowincrease considerably above governed TORQUEof normal engine.value. TORQUE, ITT, and GAS PROD RPM(No)of affected engine will also increase. Throttle friction - Tighten on normaAs ENG RPM (N2 ) and ROTOR RPM (NR) engine, reduce on affected engine.increase above governed value, normalengine will reduce power to keep itself Throttle (affected engine) - Reduce tofrom overspeeding and will indicate idle.significantly lower TORQUE, ITT, and GASPROD RPM (N|) than affected engine.If there is a high power demand (greaterthan single engine power available) at time.of high side failure, ROTOR RPM (NR) and CAUTIONENG RPM (N2 ) of affected engine will surge .................initially along with TORQUE, ITT, and GASPROD RPM (N,). As ENG RPM (N2) and WHEN OPERATING IN MANUALROTOR RPM (NR) increase, normal engine FUEL CONTROL MODE, MAKEwill reduce power to keep itself from SLOW, SMOOTH THROTTLEoverspeeding. Affected engine then tries MOVEMENTS TO AVOIDto assume all of load, which is beyond its COMPRESSOR STALL,capability due to high power demand. OVERTEMPERATURE, OVER-ENG RPM (N2) of affected engine and SPEED, AND POSSIBLEROTOR RPM (NR) will then decrease and DRIVETRAIN DAMAGE.rejoin ENG RPM (N,) of normal engine, COORDINATE THROTTLE ANDstabilizing at or slightly above governedvalue as normal engine adjusts poweroutput to share load. AVOID OVERLOADING NORMALINDICATIONS: Throttle (affected engine) - IncreaseHigh ENG RPM (N2) and ROTOR RPM slowly. Adjust throttle and collective, as(NR)possibly with RPMcaution light. required, to maintain TORQUE of

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FIRE EXT switch MAIN.

If FIRE warning light remains illuminated for

more than 10 seconds:

FIRE EXT switch RESERVE.

ENG RPM (N2) (remaining engine) Set at100%.

Land as soon as possible.

Engine shutdown Complete.

Helicopter Exit.

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

INDICATIONS:

FIRE 1 and/or F IRE 2 PULL handle

illuminated.

PROCEDURES:

Immediately initiate emergency descent, if

possible.

Shut down affected engine (1 or 2) as

follows:

FIRE PULL handle Pull.

FIRE EXT switch Main.

Throttle Closed.

Fuel Crossfeed switch Override Close.

Fuel Interconnect switch OPEN.

Engine BOOST PUMP OFF.

Verify FIRE handle light, FUEL BOOST

caution light, and FUEL switch to be

turned off are all for affected engine.

ENGINE FUEL switch OFF.

If FIRE warning light remains illuminated for

more than 10 seconds:

FIRE EXT switch RESERVE.

ENG RPM (N2) (remaining engine) Set at

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).



After landing:

Engine shutdown Complete.

Helicopter Exit.

3-4-B. CABIN SMOKE OR FUMES

INDICATIONS:

Smoke, toxic fumes, etc. in cabin.

PROCEDURES:

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 is

suspected to be electrical:

Affected system Attempt to identify and

isolate.


3-4-C. BAGGAGE COMPARTMENTFIRE

INDICATIONS:

BAGGAGE FIRE warning light illuminated.

PROCEDURES:

Reduce power to minimum required.

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BHT-2121FR-FM-1 FAA APPROVEDDuring final stages of approach, a Landing technique is same asmild flare should be executed and all prescribed for climb condition above.power to rotor should be off. Maintainhelicopter in a slight flare and usecollective smoothly to execute a soft, 3-5-E. LOSS OF TAIL ROTORslightly nose high landing. Landing COMPONENTSon aft portion of skids will tend tocorrect side drift. If helicopter startsto turn, move cyclic as necessary to Loss of any tail rotor component will resultfollow turn until helicopter comes to a in a forward CG shift. Other thancomplete stop. This technique will, in additional nose down pitching, thismost cases, result in a run on type situation would be quite similar tolanding. complete loss of tail rotor thrust asdiscussed above.

CAUTION 3-5-F. TAIL ROTOR FIXED PITCHFAILURESFOR ZERO GROUND SPEEDLANDING, FLARE AND ABRUPT INDICATIONS:USE OF COLLECTIVE MAY CAUSENOSE TO YAW LEFT. DO NOTNOSE TO YAW LEFT. DO NOT Tail rotor pitch change control failures areCORRECTITH THROTTLE. characterized either by a lack ofALTHROUGHAPPLICATION OF directional response when a pedal isTHROTTLE WILL RESULT INYAWING TO RIGHT, ADDITION OF pushed or by locked pedals. If pedals canYAWINGOWER a moderate amount ofRESPONSE MEASURE AND IS force, do not attempt to apply a maximumTOOENSITIVEOR PILOT effort since a more serious malfunctionTOO SENSITIVE FOR PILOT TO could result.MANAGE PROPERLY. DO NOTADD POWER AT THIS TIME.SLIGHT YAWING UPON3-5-G. FIXED PITCH FAILURE AT ATOUCHDOWN AT ZERO GROUNDSPEED MAY BE EXPECTED. HOVER

3-5-D. LOSS OF TAIL ROTOR PROCEDURES:THRUST IN LEVEL FLIGHT OR Do not close throttles unless a severeDESCENT right yaw occurs. If pedals lock in anyposition at a hover, landing from a hovercan be accomplished with greater safetyPROCEDURES: under power controlled flight rather thanby closing throttles and enteringClose throttles and reduce collective autorotation.immediately. Attain an airspeed slightlyabove normal autorotative glide speed. 3-5-H. FIXED PITCH FAILURE INIf altitude permits with AIRSPEED above FLIGHT60 KIAS, throttle and collective may begently applied to determine if somedegree of powered flight can be If tail rotor fixed pitch failure occursresumed. If unacceptable yawing Is during climb (left pedal applied), cruiseexperienced, re-enter autorotation and (approximately neutral pedals), andcontinue descent to a landing. descent (right pedal applied), a descent

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FAA APPROVED BHT-2121FR-FM-and landing can be effected safely by use Reduce power and maintain ENG RPMof power and throttle changes. (N2) within green arc. Normal turnscan be safely made under thesePROCEDURES: conditions, although helicopter nosmay be displaced to left.If helicopter is in a trimmed conditionwhen malfunction is discovered, engine On final approach, begin a slowpower and airspeed should be noted and deceleration so as to arrive at a poinhelicopter flown to a suitable landing area. about four to five feet above intendetouchdown area as effectiveCombinations of ENG TORQUE, ROTOR translational lift is lost.RPM (NR), and AIRSPEED will correct oraggravate yaw attitude and these should Apply collective to stop rate obe adjusted as required to control yaw descent and forward speed, and toduring landing. align helicopter with intended landingpath. Allow helicopter to touch dowat near zero ground speedRight Pedal Locked Forward of maintaining alignment with throttle.Neutral

Pedals Locked in NeutralPower should be reduced and ENGRPM (N2) maintained within green arc. Reduce power and maintain ENG RPMThis will help streamline helicopter in (N2) within green arc. Normal turnsflight. Right turns are easier than left can be safely made under theseturns. AIRSPEED should be conditionsmaintained at or above 60 KIAS.

Execute a normal to shallow approach,Execute a normal to steep approach holding AIRSPEEDat 60 KIAS duringadjusting power as necessary to initial part of approach. Adjust poweminimize or prevent right yaw. as necessary to minimize or prevenMaintain ENG RPM (N 2) and an right yaw.AIRSPEED of 60 KIAS during initialpart of approach. At 50 to 75 feet AGL and when landingarea can be made, start a decelerationAt 60 to 75 feet AGL and when landing to arrive at intended landing point witharea can be made, start a slow AIRSPEED at 25 KIAS.deceleration to arrive at intendedlanding point with AIRSPEED at about At 2 to 5 feet AGL, use throttle slowly25 KIAS. as necessary to maintain alignmenwith landing area and to control yawAt 2 to 5 feet AGL, slowly reduce do not allow helicopter to settle untithrottle to overcome yaw effect and alignment is assured, then touchallow helicopter to settle. When down.aligned with landing area, allowhelicopter to touch down. After ground contact, use collectiveand throttle as necessary to minimizeAfter ground contact, use collective forward speed and to maintainand throttle as necessary to maintain alignment. Move cyclic as necessaryalignment with landing strip, and to to follow turn until helicopter hasminimize forward speed. If helicopter come to a complete stop.starts to turn, move cyclic asnecessary to follow turn untilhelicopter comes to a complete stop.Left Pedal Locked Forward of Neutral

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BHT-2121FR-FM-1 FAA APPROVED3-5-J. LOSS OF PITCH CHANGECONTROL any inverter fails to produce power,CONTROLS LINKAGE check appropriate AC circuit breakers in.

INDICATIONS: 3-7-C. AC FAILURE - SYSTEMIn this type of failure, pitch change NO.1mechanism is broken at some point andtail rotor will assume a blade angledetermined by aerodynamic and NOTEcounterbalance forces. No. 3 inverter will supply power toeither bus If failure of no. 1 or no.PROCEDURES: 2 Inverter should occur (SN 30554

and sub.).Corrective action procedures aredescribed in FIXED PITCH FAILURES If no power available on no.1 bus, proceedabove. Specific procedure to be used as follows:depends on yaw change experienced. Pitch, roll, and yaw channel ARM switches3-6. HYDRAULIC SYSTEM OFFThe helicopter has two hydraulic powered CAUTIONflight control systems (1 and 2). Both ......systems supply power to collective andcyclic but tail rotor is powered only by C O P I LOT AC P O W E Rsystem 1. INSTRUMENTS AND NO. 1ENGINE PRESSUREIf system pressure or temperature exceeds INSTRUMENTS WILL BElimits, affected system should be turned INOPERATIVE.off. Continued flight and normalmaneuvers can be accomplished onremaining system. If system no. 1 fails and 3-7-D. AC FAILURE - SYSTEMis turned off, tail rotor control forces will NO.2increase but no change in limitationsresult. NOTE3-7. ELECTRICAL SYSTEM No. 3 inverter (if installed) willsupply power to either bus Iffailure of no. 1 or no. 2 inverter3-7-A. DC POWER FAILURE should occur.

If no power is available on no. 2 bus,If either generator has not failed but circuit proceed as follows:is open, reset generator by movinggenerator switch to RESET, then ON. Roll channel ARM switch - OFF.For single generator operation, PitchchannelARMswitch-OFF.nonessential busses may be restored bymoving NON ESS BUS switch fromNORMALto MANUAL. Monitor to ensure CAUTIONloads are within limits. .

PILOT AC POWERED3-7-B. AC - FAILURE TO PRODUCE INSTRUMENTS AND NO. 2POWER ENGINE PRESSURE3-14 Rev. 2


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FAA APPROVED BHT-2121FR-FMINSTRUMENTS WILL BE 3-8-C. FUEL QUANTITY

INOPERATIVE. INDICATION MALFUNCTIONS.3-8. FUEL SYSTEM INDICATIONS:Fuel quantity indication freezes in place(Possible power failure to the fuel quantit3-8-A. FUEL BOOST PUMP indicator.)FAILURE PROCEDURE:INDICATIONS: FUEL QTY circuit breaker - Recycle.

FUEL Interconnect switch-- OPEN.NO.1 or NO.2 FUEL BOOST Caution Li

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