FLIGHT MANUAL Objective Know the organization, contents, and revision procedures for the aircraft...

FLIGHT MANUALFLIGHT MANUALObjectivObjectiv

eeKnow the organization, contents, Know the organization, contents, and revision procedures for the and revision procedures for the aircraft flight manual.aircraft flight manual.

Sections 1 through 4 contain the FAA approved Sections 1 through 4 contain the FAA approved data necessary to operate the basic helicopter data necessary to operate the basic helicopter in a safe and efficient manner. in a safe and efficient manner.

Appendix A contains the approved Appendix A contains the approved supplements for optional equipment, which supplements for optional equipment, which shall be used in conjunction with the basic shall be used in conjunction with the basic Flight Manual when the respective optional Flight Manual when the respective optional equipment kits are installed. equipment kits are installed.

INTRODUCTIONINTRODUCTION

ORGANIZATION ORGANIZATION

This Rotorcraft Flight Manual is divided into four sections with This Rotorcraft Flight Manual is divided into four sections with an appendix as follows:an appendix as follows:

Section 1Section 1 -- LIMITATIONSLIMITATIONSSection 2Section 2 -- NORMAL PROCEDURESNORMAL PROCEDURESSection 3Section 3 -- EMERGENCY AND EMERGENCY AND

MALFUNCTION PROCEDURESMALFUNCTION PROCEDURESSection 4Section 4 -- PERFORMANCEPERFORMANCEAppendixAppendix -- OPTIONAL EQUIPMENT OPTIONAL EQUIPMENT

AND SUPPLEMENTSAND SUPPLEMENTS

The Manufacturer's Data (BHT-206L3-MD-l) The Manufacturer's Data (BHT-206L3-MD-l) manual, contains information to be used in manual, contains information to be used in conjunction with the Flight Manual. The manual conjunction with the Flight Manual. The manual is divided into four sections:is divided into four sections:

Section 1Section 1 -- WEIGHT AND WEIGHT AND BALANCEBALANCE

Section 2Section 2 -- SYSTEMS SYSTEMS DESCRIPTIONDESCRIPTION

Section 3Section 3 -- OPERATIONAL OPERATIONAL INFORMATIONINFORMATION

Section 4Section 4 -- HANDLING AND HANDLING AND SERVICING MAINTENANCESERVICING MAINTENANCE

TERMINOLOGYTERMINOLOGYWARNINGS, CAUTIONS, AND NOTESWARNINGS, CAUTIONS, AND NOTES

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

WARNINGWARNING

AN OPERATING PROCEDURE, PRACTICE, ETC., AN OPERATING PROCEDURE, PRACTICE, ETC., WHICH, IF NOT CORRECTLY FOLLOWED, COULD WHICH, IF NOT CORRECTLY FOLLOWED, COULD RESULT IN PERSONAL INJURY OR LOSS OF LIFE.RESULT IN PERSONAL INJURY OR LOSS OF LIFE.

CAUTIONCAUTION

AN OPERATING PROCEDURE, PRACTICE, AN OPERATING PROCEDURE, PRACTICE, ETC., WHICH IF NOT STRICTLY OB-ETC., WHICH IF NOT STRICTLY OB-SERVED, COULD RESULT IN DAMAGE TO SERVED, COULD RESULT IN DAMAGE TO OR DESTRUCTION OF EQUIPMENT.OR DESTRUCTION OF EQUIPMENT.

NOTENOTE

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

USE OF PROCEDURAL WORDSUSE OF PROCEDURAL WORDSThe concept of procedural word usage and intended The concept of procedural word usage and intended meaning which has been adhered to in preparing this meaning which has been adhered to in preparing this manual is as follows:manual is as follows:““ShallShall" has been used only when application of a " has been used only when application of a procedure is mandatory.procedure is mandatory.""ShouldShould” has been used only when application of a ” has been used only when application of a procedure is recommended.procedure is recommended.““MayMay" and "need not" have been used only when " and "need not" have been used only when application of a procedure is optional. application of a procedure is optional. ““WillWill" has been used only to indicate futurity, never to " has been used only to indicate futurity, never to indicate a mandatory procedure.indicate a mandatory procedure.

SECTION 1 - LIMITATIONSSECTION 1 - LIMITATIONSGENERAL GENERAL

Compliance with the limitations section is required by Compliance with the limitations section is required by appropriate operating rules. Anytime an operating appropriate operating rules. Anytime an operating limitation is exceeded, an appropriate entry shall be limitation is exceeded, an appropriate entry shall be made in the helicopter logbook. The entry shall state made in the helicopter logbook. The entry shall state which limit was exceeded, the duration of time, the which limit was exceeded, the duration of time, the extreme value attained, and any additional extreme value attained, and any additional information essential in determining the maintenance information essential in determining the maintenance action required. action required.

Intentional use of transient limits is prohibited.Intentional use of transient limits is prohibited.

BASIS OF CERTIFICATION BASIS OF CERTIFICATION

This helicopter is certified under Civil Air Regulation, This helicopter is certified under Civil Air Regulation, Part 6, Rotorcraft Airworthiness, Normal Category.Part 6, Rotorcraft Airworthiness, Normal Category.

TYPE OF OPERATIONTYPE OF OPERATION

The basic configured helicopter is approved for seven-The basic configured helicopter is approved for seven-place seating and is certified for land operation under place seating and is certified for land operation under day or night VFR nonicing conditions.day or night VFR nonicing conditions.

Flight operations are approved with the landing gear Flight operations are approved with the landing gear crosstube fairings installed or removed.crosstube fairings installed or removed.

NOTE NOTE

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

Flight with any combination of doors off is Flight with any combination of doors off is approved. Refer to AIRSPEED limitations.approved. Refer to AIRSPEED limitations.

OPTIONAL EQUIPMENTOPTIONAL EQUIPMENT

The following equipment shall be installed The following equipment shall be installed when conducting flight operations in falling when conducting flight operations in falling and/or blowing snow to reduce possibility of and/or blowing snow to reduce possibility of engine flameout:engine flameout:

The Snow Deflector Kit or the Particle Separator The Snow Deflector Kit or the Particle Separator Engine Air Induction System Kit and the Snow Engine Air Induction System Kit and the Snow Deflector Kit. (See BHT-206L3-FMS-3 and Deflector Kit. (See BHT-206L3-FMS-3 and BHT206L3-FMS-7.)BHT206L3-FMS-7.)Refer to appropriate Flight Manual Supplement(s) for Refer to appropriate Flight Manual Supplement(s) for additional limitations, procedures, and performance additional limitations, procedures, and performance data.data.

FLIGHT CREW FLIGHT CREW The minimum flight crew consists of one pilot who The minimum flight crew consists of one pilot who shall operate the helicopter from the right crew seat. shall operate the helicopter from the right crew seat. The left crew seat may be used for an additional pilot The left crew seat may be used for an additional pilot when the approved dual controls are installed.when the approved dual controls are installed.

WEIGHT AND CENTER OF GRAVITY WEIGHT AND CENTER OF GRAVITY

WEIGHTWEIGHT

CAUTIONCAUTION

LOADS THAT RESULT IN GROSS WEIGHTS LOADS THAT RESULT IN GROSS WEIGHTS ABOVE 4,150 POUNDS SHALL BE CARRIED ON ABOVE 4,150 POUNDS SHALL BE CARRIED ON THE CARGO HOOK AND SHALL NOT BE THE CARGO HOOK AND SHALL NOT BE IMPOSED ON LANDING GEAR.IMPOSED ON LANDING GEAR.

Maximum approved gross weight for takeoff and Maximum approved gross weight for takeoff and landing is 4,150 pounds.landing is 4,150 pounds.

Minimum combined crew weight at fuselage station Minimum combined crew weight at fuselage station 65.0 is 170 pounds.65.0 is 170 pounds.

CENTER OF GRAVITY LONGITUDINALCENTER OF GRAVITY LONGITUDINALNOTENOTE

Ballast as required to maintain weight empty CG within Ballast as required to maintain weight empty CG within limits shown on Center of Gravity vs Weight Empty limits shown on Center of Gravity vs Weight Empty chart in Maintenance Manual.chart in Maintenance Manual.Longitudinal center of gravity limits are variable Longitudinal center of gravity limits are variable depending on gross weight. The forward CG limit depending on gross weight. The forward CG limit varies between stations 118.0 and 119.2. The aft CG varies between stations 118.0 and 119.2. The aft CG limit varies between stations 126.7 and 128.5. limit varies between stations 126.7 and 128.5.

NOTENOTEStation 0 (reference datum) is located 55.16 inches Station 0 (reference datum) is located 55.16 inches forward of forward jack point centerline.forward of forward jack point centerline.

CENTER OF GRAVITY LATERALCENTER OF GRAVITY LATERAL

Lateral center of gravity limits are 4.0 Lateral center of gravity limits are 4.0 inches left of and 3.5 inches right of inches left of and 3.5 inches right of fuselage centerline. fuselage centerline.

DOOR(S) OFF DOOR(S) OFF

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

AIRSPEEDAIRSPEED

Basic VNE is 130 KIAS (150 MPH) sea level to Basic VNE is 130 KIAS (150 MPH) sea level to 3,000 feet density altitude. Decrease VNE for 3,000 feet density altitude. Decrease VNE for ambient conditions in accordance with ambient conditions in accordance with AIRSPEED LIMITATIONS placard. Refer to AIRSPEED LIMITATIONS placard. Refer to Placards and Decals.Placards and Decals.

VNE is 84 KIAS (96 MPH) at 85 to 100% VNE is 84 KIAS (96 MPH) at 85 to 100% TORQUE takeoff power.TORQUE takeoff power.

VNE is 90 KIAS (104 MPH) with any door(s) off, VNE is 90 KIAS (104 MPH) with any door(s) off, not to exceed placarded VNE.not to exceed placarded VNE.

ALTITUDEALTITUDEMaximum operating pressure altitude is 20,000 Maximum operating pressure altitude is 20,000 feet.feet.

NOTENOTEFor high altitude pressure operation, refer to For high altitude pressure operation, refer to appropriate rules for oxygen requirements.appropriate rules for oxygen requirements.

AMBIENT AIR TEMPERATUREAMBIENT AIR TEMPERATUREThe maximum sea level ambient air temperature The maximum sea level ambient air temperature for operation is +51.7for operation is +51.7ooC (+125C (+125ooF) and decreases F) and decreases with pressure altitude at the standard lapse rate with pressure altitude at the standard lapse rate of 2of 2ooC (3.6C (3.6ooF) / 1000 feet to 20,000 feet.F) / 1000 feet to 20,000 feet.

MANEUVERINGMANEUVERINGAerobatic maneuvers are prohibited.Aerobatic maneuvers are prohibited.

GENERATOR DC LOAD GENERATOR DC LOAD Continuous operation:Continuous operation:

0 to 90%0 to 90%Maximum:Maximum:

90%90%

POWERPLANTPOWERPLANT

Allison model 250-C30PAllison model 250-C30P

GAS PRODUCER RPMGAS PRODUCER RPMContinuous operation:Continuous operation:

63 to 105%63 to 105%Maximum:Maximum:

105%105%Maximum transient:Maximum transient:

106%106%

(Do not exceed 10 seconds above 105%)(Do not exceed 10 seconds above 105%)

POWER TURBINE RPM POWER TURBINE RPM

WARNINGWARNING

USE OF THE THROTTLE TO CONTROL RPM USE OF THE THROTTLE TO CONTROL RPM IS NOT AUTHORIZED. (Refer to Section 3, for IS NOT AUTHORIZED. (Refer to Section 3, for exception)exception)

Minimum:Minimum: 97%97%Continuous operation:Continuous operation: 97 to 100%97 to 100%Maximum continuous:Maximum continuous: 100%100%Transient overspeed range:Transient overspeed range: 100 to 103%100 to 103%

NOTENOTE

Refer to Allison Operation and Maintenance Refer to Allison Operation and Maintenance Manual for transient overspeed limits.Manual for transient overspeed limits.

TURBINE OUTLET TEMPERATURE (TOT)TURBINE OUTLET TEMPERATURE (TOT)

WARNINGWARNING

EXCEEDING 768EXCEEDING 768oC TURB OUT TEMP OR 100% C TURB OUT TEMP OR 100% TORQUE CAN CAUSE GAS PRODUCER TOPPING TORQUE CAN CAUSE GAS PRODUCER TOPPING WITH RESULTANT ROTOR RPM DROOP.WITH RESULTANT ROTOR RPM DROOP.

Continuous operation:Continuous operation: 100 to 716100 to 716oCCMaximum continuous:Maximum continuous: 716716oCC5 minute takeoff range:5 minute takeoff range: 716 to 768716 to 768oCCMaximum for takeoff:Maximum for takeoff: 768768oCCMaximum transient (10 seconds):Maximum transient (10 seconds): 768 to 871768 to 871oCCMaximum for starting and shutdownMaximum for starting and shutdown 927927oCC

(Do not exceed 10 seconds above 768(Do not exceed 10 seconds above 768oC)C)

NOTENOTE

Intentional use of power transient area (768 to 871Intentional use of power transient area (768 to 871oC) C) is prohibited. The TURB OUT TEMP gage is is prohibited. The TURB OUT TEMP gage is equipped with a red warning light that will illuminate equipped with a red warning light that will illuminate when either of the following conditions occur: 770 to when either of the following conditions occur: 770 to 927927oC more than 10 seconds or above 927C more than 10 seconds or above 927oC.C.

ENGINE TORQUEENGINE TORQUE

Continuous operation: Continuous operation: 0 to 85%0 to 85%Maximum continuous:Maximum continuous: 85%85%5 minute takeoff range5 minute takeoff range 85 to 100%85 to 100%Maximum for takeoff:Maximum for takeoff: 100%100%Maximum transient (5 seconds):Maximum transient (5 seconds): 105%105%

FUEL PRESSUREFUEL PRESSUREMinimumMinimum 4 PSI 4 PSI Continuous operation:Continuous operation: 4 to 25 PSI 4 to 25 PSI Maximum:Maximum: 25 PSI 25 PSI

Minimum for use of type A, A-l, or JP-5 Minimum for use of type A, A-l, or JP-5 fuel, or any mixture of these, at ambient fuel, or any mixture of these, at ambient 8 PSI 8 PSI temperature below -18temperature below -18oC (0C (0oF)F)

ENGINE OIL PRESSUREENGINE OIL PRESSUREMinimum for idle:Minimum for idle: 50 PSI50 PSIOperations below 79% N1:Operations below 79% N1: 50 to 90 PSI50 to 90 PSICont. operation below 94% N1:Cont. operation below 94% N1: 90 to 115 PSI90 to 115 PSIContinuous operation:Continuous operation: 115 to 130 PSI115 to 130 PSIMaximum:Maximum: 130 PSI130 PSI

ENGINE OIL TEMPERATUREENGINE OIL TEMPERATURE

Continuous operation:Continuous operation: 0 to 1070 to 107oCCMaximum:Maximum: 107107oCC

ANTI-ICEANTI-ICE

The The maximummaximum ambient temperature for use of ambient temperature for use of engine anti-ice is 4.4engine anti-ice is 4.4oC (40C (40oF).F).

ENGINE ANTl-lCING shall be ON for flight in ENGINE ANTl-lCING shall be ON for flight in visible moisture in temperature below 4.4visible moisture in temperature below 4.4oC C (40(40oF).F).

STARTERSTARTER

Limit starter energize time to the following:Limit starter energize time to the following:

Ext. Power StartExt. Power Start Battery StartBattery Start

40 Seconds ON40 Seconds ON 60 Seconds ON 60 Seconds ON 30 Seconds OFF30 Seconds OFF 60 Seconds OFF 60 Seconds OFF 40 Seconds ON40 Seconds ON 60 Seconds ON 60 Seconds ON 30 Seconds OFF30 Seconds OFF 60 Seconds OFF 60 Seconds OFF 40 Seconds ON40 Seconds ON 60 Seconds ON 60 Seconds ON 30 Minutes OFF30 Minutes OFF 30 Minutes OFF30 Minutes OFF

TRANSMISSIONTRANSMISSION

TRANSMISSION OIL PRESSURETRANSMISSION OIL PRESSURE

Minimum:Minimum: 30 PSI30 PSIContinuous operation:Continuous operation: 40 to 70 PSI40 to 70 PSIMaximum:Maximum: 70 PSI70 PSI

TRANSMISSION OIL TEMPERATURETRANSMISSION OIL TEMPERATURE

Continuous operation:Continuous operation: 15 to 11015 to 110oCCMaximum:Maximum: 110110oCC

ROTORROTORROTOR RPM - POWER ONROTOR RPM - POWER ON

Minimum transient (5 seconds):Minimum transient (5 seconds): 95%95%Minimum:Minimum: 97%97%Continuous operation:Continuous operation: 97 to 100%97 to 100%Maximum continuous:Maximum continuous: 100%100%Maximum transient (5 minutes):Maximum transient (5 minutes):103%103%

ROTOR RPM - POWER OFFROTOR RPM - POWER OFFMinimum:Minimum: 90%90%Maximum:Maximum: 107%107%

FUEL AND OILFUEL AND OIL

Turbine fuel ASTM-D-1655, Type B, or MIL-T-5624, Turbine fuel ASTM-D-1655, Type B, or MIL-T-5624, Grade JP-4, may be used at all ambient temperatures.Grade JP-4, may be used at all ambient temperatures.

Turbine fuel ASTM-D-1655, Type A or A-l, or MIL-T-Turbine fuel ASTM-D-1655, Type A or A-l, or MIL-T-5624, Grade JP-5, limited to ambient temperatures 5624, Grade JP-5, limited to ambient temperatures above -17.8above -17.8ooC C (0(0ooF)F) when equipped with fuel pressure when equipped with fuel pressure gage PIN 206-075-676-101, -105, or -111.gage PIN 206-075-676-101, -105, or -111.

Turbine fuel ASTM-D-1655, Type A or A-l, or MIL-T-Turbine fuel ASTM-D-1655, Type A or A-l, or MIL-T-5624, Grade JP-5, limited to ambient temperatures -5624, Grade JP-5, limited to ambient temperatures -3232ooC C (-25(-25ooF)F) and above when equipped with fuel and above when equipped with fuel pressure gage PIN 206-075-676-117, red triangle at pressure gage PIN 206-075-676-117, red triangle at 88 PSI.PSI.

NOTENOTEAnti-icing fuel additives are not required for any ambient Anti-icing fuel additives are not required for any ambient temperature. Refer to Allison Operation and Maintenance temperature. Refer to Allison Operation and Maintenance Manual for cold weather fuel and blending instructions. Manual for cold weather fuel and blending instructions.

ENGINE OIL ENGINE OIL Turbine oil MIL-L-7808 may be used at all ambient Turbine oil MIL-L-7808 may be used at all ambient temperatures. DOD-L-85734 (AS) or MIL-L-23699 limited to temperatures. DOD-L-85734 (AS) or MIL-L-23699 limited to ambient temperatures above -40ambient temperatures above -40ooC / F). C / F).

NOTE NOTE Refer to Allison Operation and Maintenance Manual and Refer to Allison Operation and Maintenance Manual and BHT206L3-MD-l manual for approved oils and mixing of oils of BHT206L3-MD-l manual for approved oils and mixing of oils of different brands, types, and manufacturers.different brands, types, and manufacturers.

TRANSMISSION ANDTRANSMISSION ANDTAIL ROTOR GEARBOX OILTAIL ROTOR GEARBOX OIL

Turbine oil MIL-L-7808 may be used Turbine oil MIL-L-7808 may be used at all ambient temperatures. DOD-at all ambient temperatures. DOD-L-85734(AS) or MIL-L-23699 limited L-85734(AS) or MIL-L-23699 limited to ambient temperatures above -to ambient temperatures above -4040ooC / F). C / F).

HYDRAULIC HYDRAULIC

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

SECTION 2 - NORMAL PROCEDURESSECTION 2 - NORMAL PROCEDURESINTRODUCTION INTRODUCTION

This section contains instructions and procedures for This section contains instructions and procedures for operating the helicopter from the planning stage, operating the helicopter from the planning stage, through actual flight conditions, to securing the through actual flight conditions, to securing the helicopter after landing. Normal and standard helicopter after landing. Normal and standard conditions are assumed in these procedures. Pertinent conditions are assumed in these procedures. Pertinent data in other sections is referenced when applicable.data in other sections is referenced when applicable.

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

OPERATING LIMITATIONSOPERATING LIMITATIONS

The minimum and maximum limits, and the The minimum and maximum limits, and the normal and cautionary operating ranges for the normal and cautionary operating ranges for the helicopter, and its subsystems, are indicated by helicopter, and its subsystems, are indicated by instrument markings and placards.instrument markings and placards.

The instrument markings and placards The instrument markings and placards represent careful aerodynamic calculations that represent careful aerodynamic calculations that are substantiated by flight test data.are substantiated by flight test data.

Refer to Section 1, for a detailed explanation of Refer to Section 1, for a detailed explanation of each operating limitation.each operating limitation.

FLIGHT PLANNINGFLIGHT PLANNINGEach flight should be planned adequately to ensure safe Each flight should be planned adequately to ensure safe operations and to provide the pilot with the data to be operations and to provide the pilot with the data to be used during flight. used during flight.

Check type of mission to be performed and destination. Check type of mission to be performed and destination.

Select appropriate performance charts to be used from Select appropriate performance charts to be used from Section 4, and/or the appropriate optional equipment Section 4, and/or the appropriate optional equipment supplement.supplement.

TAKEOFF AND LANDING DATATAKEOFF AND LANDING DATARefer to Section 1 for takeoff and landing weight limits, Refer to Section 1 for takeoff and landing weight limits, and to Section 4 for performance information.and to Section 4 for performance information.

WEIGHT AND BALANCEWEIGHT AND BALANCEDetermine proper weight and balance of the Determine proper weight and balance of the helicopter as follows:helicopter as follows:

1.1. Consult BHT-206L3-MD-l for instructions.Consult BHT-206L3-MD-l for instructions.

2.2. Compute takeoff and anticipated landing Compute takeoff and anticipated landing gross weight, check helicopter Center of gross weight, check helicopter Center of Gravity (CG) locations, and determine weight Gravity (CG) locations, and determine weight of fuel, oil, payload, etc.of fuel, oil, payload, etc.

3.3. Ensure Weight / CG limits listed in Section 1 Ensure Weight / CG limits listed in Section 1 have not been exceeded.have not been exceeded.

PREFLIGHTPREFLIGHTSEQUENCESEQUENCE

SECTION 3SECTION 3EMERGENCY / MALFUNCTION EMERGENCY / MALFUNCTION

PROCEDURESPROCEDURES

INTRODUCTION INTRODUCTION

The following procedures contain the indications The following procedures contain the indications of failures or malfunctions which affect safety of of failures or malfunctions which affect safety of the crew, the helicopter, ground personnel or the crew, the helicopter, ground personnel or property; the use of emergency features of property; the use of emergency features of primary and backup systems; and appropriate primary and backup systems; and appropriate warnings, cautions, and explanatory notes. The warnings, cautions, and explanatory notes. The following list fault conditions and corrective following list fault conditions and corrective actions for warning lights and caution lights actions for warning lights and caution lights respectively.respectively.

DEFINITIONS DEFINITIONS

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

LAND AS SOON AS POSSIBLELAND AS SOON AS POSSIBLE: Land without delay : Land without delay at the nearest suitable area (i.e., open field) at which a at the nearest suitable area (i.e., open field) at which a safe approach and landing is reasonably assured.safe approach and landing is reasonably assured.

LAND AS SOON AS PRACTICALLAND AS SOON AS PRACTICAL: The landing site : The landing site and duration of flight are at the discretion of the pilot. and duration of flight are at the discretion of the pilot. Extended flight beyond the nearest approved landing Extended flight beyond the nearest approved landing area is not recommended.area is not recommended.

The following terms are used to describe the The following terms are used to describe the operating condition of a system, subsystem, operating condition of a system, subsystem, assembly, or component. assembly, or component.

AffectedAffected: Fails to operate in the intended or : Fails to operate in the intended or usual manner.usual manner.

NormalNormal: Operates in the intended or usual : Operates in the intended or usual manner. manner.

All procedures listed herein assume the pilot All procedures listed herein assume the pilot gives first priority to helicopter control and a gives first priority to helicopter control and a safe flight path.safe flight path.

PANELPANELWORDINGWORDING

FAULTFAULTCONDITIONCONDITION CORRECTIVE ACTIONCORRECTIVE ACTION

ENG OUTENG OUT(audio if(audio if

functional)functional)

Gas Producer less than Gas Producer less than 55 55 ++ 3% RPM; Power 3% RPM; Power Turbine RPM Turbine RPM decreasingdecreasing

Verify engine condition. Verify engine condition. Accomplish engine failureAccomplish engine failure procedures.procedures.

Battery overheating. Battery overheating. Temperature 140Temperature 140ooF (60F (60ooC) C) or higher. or higher.

Turn BAT switch OFF and Turn BAT switch OFF and Land as soon as practical. If Land as soon as practical. If BATTERY RLY caution light BATTERY RLY caution light illuminates, land as soon asilluminates, land as soon as possiblepossible

BATTERYBATTERYHOTHOT

WARNING LIGHTSWARNING LIGHTS

LITTERLITTERDOORDOOROPEN OPEN

Litter door not securely Litter door not securely latched.latched.

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



CAUTION LIGHTSCAUTION LIGHTS

ROTOR below ROTOR below 90% RPM90% RPM

Reduce collective pitch Reduce collective pitch and ensure throttle is and ensure throttle is fully open. Light and fully open. Light and audio should cease audio should cease when ROTOR increases when ROTOR increases above approximately above approximately 90% RPM.90% RPM.

ROTORROTOR LOW RPMLOW RPM

(Audio & Light)(Audio & Light)

XMSN OIL XMSN OIL pressurepressure is below is below minimum. minimum.

TRANSTRANSOIL PRESSOIL PRESS

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

XMSN OIL XMSN OIL temperature is temperature is at or above at or above red line.red line.

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

TRANSTRANS OIL OIL

TEMPTEMP



Metallic Metallic particles in particles in engine oil. engine oil.

Land as soon as Land as soon as possible. possible. ENGENG CHIPCHIP

Battery relay has Battery relay has malfunctioned to malfunctioned to closed position closed position with BAT switch with BAT switch OFFOFF. .

BATTERY RLYBATTERY RLY If BATTERY HOT light is If BATTERY HOT light is illuminated, land as illuminated, land as soon as possible. soon as possible. Battery will not drop off Battery will not drop off line.line.

Approximately Approximately 50 - 75 LBS of 50 - 75 LBS of fuel remain. fuel remain.

Verify FUEL QTY. Land Verify FUEL QTY. Land as soon as practical. as soon as practical. FUEL LOWFUEL LOW

Metallic particles Metallic particles in transmission in transmission oil. oil.

Land as soon as Land as soon as possible. possible. TRANS CHIPTRANS CHIP



Failure of Failure of generator.generator.

GEN switch - RESET GEN switch - RESET then ON.then ON. If GEN If GEN FAIL light remains FAIL light remains illuminated, GEN illuminated, GEN switch - OFF. Land switch - OFF. Land as soon as practical. as soon as practical.

GEN FAILGEN FAIL

AIR FRAME AIR FRAME fuel filter fuel filter clogged. clogged.

FUEL FILTERFUEL FILTER Land as soon as Land as soon as possible.possible.Clean before next Clean before next flight.flight.

Metallic Metallic particles in tail particles in tail rotor gearbox rotor gearbox oil. oil.

Land as soon as Land as soon as possible. possible.

T/R CHIPT/R CHIP



Right pump of Right pump of the dual boost the dual boost pump assembly pump assembly failed. failed.

R/FUEL PUMPR/FUEL PUMP Descend below 6,000 Descend below 6,000 feet pressure altitude, if feet pressure altitude, if flight permits. Land as flight permits. Land as soon as practical.soon as practical.

Left pump of Left pump of the dual boost the dual boost pump assembly pump assembly failed. failed.

L/FUEL PUMPL/FUEL PUMP Descend below 6,000 Descend below 6,000 feet pressure altitude, if feet pressure altitude, if flight permits. Land as flight permits. Land as soon as practical.soon as practical.

WARNINGWARNINGIF BOTH FUEL BOOST PUMPS FAIL, UNUSABLE FUEL MAY BE IF BOTH FUEL BOOST PUMPS FAIL, UNUSABLE FUEL MAY BE AS HIGH AS 160 POUNDS DUE TO INABILITY TO TRANSFER AS HIGH AS 160 POUNDS DUE TO INABILITY TO TRANSFER FUEL FROM FORWARD CELLS. LAND AS SOON AS FUEL FROM FORWARD CELLS. LAND AS SOON AS PRACTICAL.PRACTICAL.

ENGINE EMERGENCIES ENGINE EMERGENCIES

ENGINE FIRE DURING START OR SHUTDOWNENGINE FIRE DURING START OR SHUTDOWN

INDICATIONS:INDICATIONS:

1.1. Excessive TURBINE OUTLET TEMP (TOT).Excessive TURBINE OUTLET TEMP (TOT).

2.2. Visible smoke or fire.Visible smoke or fire.

PROCEDURE:PROCEDURE:

1.1. Throttle - Closed.Throttle - Closed.

2.2. FUEL VALVE switch -FUEL VALVE switch - OFF.OFF.

3.3. STARTER switch - Press to motor engine until TOT stabilizes at STARTER switch - Press to motor engine until TOT stabilizes at normal temperature.normal temperature.

4.4. Shut down and exit helicopter.Shut down and exit helicopter.

ENGINE FIRE DURING FLIGHT ENGINE FIRE DURING FLIGHT


1.1. Smoke.Smoke.2.2. Fumes.Fumes.3.3. Fire.Fire.


1.1. Throttle - Closed.Throttle - Closed.2.2. Autorotation - Enter Immediately.Autorotation - Enter Immediately.33 FUEL VALVE switch - OFF.FUEL VALVE switch - OFF.4.4. BAT switch - OFF.BAT switch - OFF.55 GEN switch - OFF.GEN switch - OFF.6.6. Execute autorotative descent and landing.Execute autorotative descent and landing.

Do not restart engine until correctiveDo not restart engine until corrective maintenance has been performed.maintenance has been performed.

ENGINE FAILUREENGINE FAILURE HOVERING IN GROUND EFFECTHOVERING IN GROUND EFFECT


1.1. Left yaw.Left yaw.

2.2. ENG OUT warning light illuminated.ENG OUT warning light illuminated.

3.3. Engine out audio (if functional) activated when GAS Engine out audio (if functional) activated when GAS PRODUCER drops below 55% RPM.PRODUCER drops below 55% RPM.

4.4. ROTOR RPM decreases with ROTOR LOW caution ROTOR RPM decreases with ROTOR LOW caution light and audio on when ROTOR drops below 90% light and audio on when ROTOR drops below 90% RPM.RPM.

5.5. Engine instruments indicate power loss.Engine instruments indicate power loss.


1.1. Maintain heading and landing attitude.Maintain heading and landing attitude.

2.2. Adjust Collective to control rate of descent and Adjust Collective to control rate of descent and cushion landing. It is recommended that level cushion landing. It is recommended that level touchdown be made prior to passing through touchdown be made prior to passing through 70% Rotor RPM.70% Rotor RPM.

33 Land.Land.

4.4. Shut down helicopter.Shut down helicopter.

ENGINE FAILUREENGINE FAILUREHOVERING OUT OF GROUND EFFECTHOVERING OUT OF GROUND EFFECT


1.1. Left yaw. Left yaw.

2.2. ENG OUT warning light illuminated. ENG OUT warning light illuminated.

3.3. Engine out audio (if functional) activated when GAS Engine out audio (if functional) activated when GAS PRODUCER drops below 55% RPM. PRODUCER drops below 55% RPM.

4.4. ROTOR RPM decreases with ROTOR LOW caution ROTOR RPM decreases with ROTOR LOW caution light and audio on when ROTOR drops below 90% light and audio on when ROTOR drops below 90% RPM. RPM.

5.5. Engine instruments indicate power loss.Engine instruments indicate power loss.


1.1. Maintain heading and attitude control.Maintain heading and attitude control. 2.2. Collective Adjust as required to maintain 90 to Collective Adjust as required to maintain 90 to

107% ROTOR RPM.107% ROTOR RPM. 3.3. Apply collective pitch as flare effect decreases to Apply collective pitch as flare effect decreases to

further reduce forward speed and cushion further reduce forward speed and cushion landing. It is recommended that level touch landing. It is recommended that level touch down be made prior to passing through 70% down be made prior to passing through 70% ROTOR RPM. Upon ground contact, collective ROTOR RPM. Upon ground contact, collective pitch shall be reduced smoothly while maintain-pitch shall be reduced smoothly while maintain-ing cyclic in neutral or centered position.ing cyclic in neutral or centered position.

CAUTIONCAUTION

EXCESSIVE GROUND RUN WITH COLLECTIVE EXCESSIVE GROUND RUN WITH COLLECTIVE UP, OR ANY TENDENCY TO FLOAT FOR LONG UP, OR ANY TENDENCY TO FLOAT FOR LONG DISTANCE PRIOR TO GROUND CONTACT DISTANCE PRIOR TO GROUND CONTACT SHOULD BE AVOIDED.SHOULD BE AVOIDED.

NOTENOTE

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

4.4. Cyclic - Adjust to obtain desired Cyclic - Adjust to obtain desired autorotative AIRSPEED. (52-69 KIAS)autorotative AIRSPEED. (52-69 KIAS)

CAUTIONCAUTION

AVOID LARGE FORWARD CYCLIC INPUTS UNTIL AVOID LARGE FORWARD CYCLIC INPUTS UNTIL COLLECTIVE IS FULLY DOWN AND ROTOR DECAY COLLECTIVE IS FULLY DOWN AND ROTOR DECAY HAS CEASED. HAS CEASED.

NOTENOTE

Maximum AIRSPEED for steady autorotation is Maximum AIRSPEED for steady autorotation is 100 KIAS. Autorotation above this speed 100 KIAS. Autorotation above this speed results in high rates of descent and low ROTOR results in high rates of descent and low ROTOR RPM. A blue radial is installed on the AIRSPEED RPM. A blue radial is installed on the AIRSPEED indicator as a reminder of this condition. indicator as a reminder of this condition. Nominal autorotative AIRSPEED is Nominal autorotative AIRSPEED is 61 KIAS61 KIAS..

5.5. Attempt engine restart if ample Attempt engine restart if ample altitude remains. (Refer to ENGINE altitude remains. (Refer to ENGINE RESTART.)RESTART.)

6.6. At low altitude:At low altitude:

a.a. Throttle - Closed. Throttle - Closed. b.b. FUEL VALVE switch - OFF. FUEL VALVE switch - OFF. c.c. Accomplish autorotative landing.Accomplish autorotative landing.

7.7. Complete helicopter shutdown.Complete helicopter shutdown.

ENGINE RESTARTENGINE RESTARTAn engine restart may be attempted in An engine restart may be attempted in flight if time and altitude permit. flight if time and altitude permit. Successful starts have been Successful starts have been accomplished up to and including 20,000 accomplished up to and including 20,000 feet pressure altitude.feet pressure altitude.

CAUTIONCAUTION

IF THE CAUSE OF FAILURE IS OBVIOUSLY IF THE CAUSE OF FAILURE IS OBVIOUSLY MECHANICAL AS EVIDENCED BY MECHANICAL AS EVIDENCED BY ABNORMAL METALLIC OR GRINDING ABNORMAL METALLIC OR GRINDING SOUNDS, DO NOT ATTEMPT A RESTART.SOUNDS, DO NOT ATTEMPT A RESTART.

PROCEDURES:PROCEDURES:

1.1. Maintain control of helicopter.Maintain control of helicopter.2.2. Collective Adjust to maintain 90 to Collective Adjust to maintain 90 to

107% ROTOR RPM.107% ROTOR RPM.3.3. Throttle Closed.Throttle Closed.4.4. AIRSPEED - 52 KIAS.AIRSPEED - 52 KIAS.5.5. FUEL VALVE switch - ON. FUEL VALVE switch - ON. 6.6. STARTER switch - Press to engage.STARTER switch - Press to engage.7.7. Throttle - Idle.Throttle - Idle.

CAUTIONCAUTION

IF START IS NOT INITIATED BEFORE GAS IF START IS NOT INITIATED BEFORE GAS PRODUCER DECREASES BELOW 30% RPM PRODUCER DECREASES BELOW 30% RPM (APPROXIMATELY 10 SECONDS AFTER (APPROXIMATELY 10 SECONDS AFTER ENGINE FAILURE), THROTTLE SHALL BE ENGINE FAILURE), THROTTLE SHALL BE MODULATED DURING START TO PREVENT MODULATED DURING START TO PREVENT EXCEEDING TURB OUT TEMP LIMIT.EXCEEDING TURB OUT TEMP LIMIT.

8.8. TURB OUT TEMP - Monitor range 716 TURB OUT TEMP - Monitor range 716 to 768'C. to 768'C.

9.9. Throttle - Advance smoothly to fully Throttle - Advance smoothly to fully open position.open position.

If a restart is unsuccessful, abort start and If a restart is unsuccessful, abort start and secure engine as follows:secure engine as follows:

10.10. Throttle Closed.Throttle Closed.11.11. FUEL VALVE switch OFF.FUEL VALVE switch OFF.12.12. Accomplish autorotative descent and Accomplish autorotative descent and

landing.landing.

ENGINE OVERSPEEDENGINE OVERSPEED

An engine overspeed may be due to one of the following: fuel An engine overspeed may be due to one of the following: fuel control failure, power turbine governor failure, or mechanical control failure, power turbine governor failure, or mechanical drive failure to the power turbine or gas producer accessory drive failure to the power turbine or gas producer accessory sections. sections.

lt the GAS PRODUCER RPM can be controlled with throttle, lt the GAS PRODUCER RPM can be controlled with throttle, then a power turbine governor failure or power turbine then a power turbine governor failure or power turbine accessory drive failure is indicated. accessory drive failure is indicated.

If the GAS PRODUCER RPM and POWER TURBINE RPM If the GAS PRODUCER RPM and POWER TURBINE RPM are unstable and cannot be controlled with throttle, then the are unstable and cannot be controlled with throttle, then the fuel control has malfunctioned or the gas producer accessory fuel control has malfunctioned or the gas producer accessory drive has failed. A gas producer accessory drive failure is drive has failed. A gas producer accessory drive failure is indicated by a rapid loss of ENG OIL pressure.indicated by a rapid loss of ENG OIL pressure.


1.1. Increase in ROTOR RPM. Increase in ROTOR RPM.

2.2. Increase in POWER TURBINE RPM. Increase in POWER TURBINE RPM.

3.3. Increase in GAS PRODUCER RPM. Increase in GAS PRODUCER RPM.

4.4. Increase in TORQUE.Increase in TORQUE.


1.1. Throttle - Retard.Throttle - Retard.

2.2. GAS PRODUCER RPM or POWER TURBINE RPM - GAS PRODUCER RPM or POWER TURBINE RPM - Stabilized with throttle control.Stabilized with throttle control.

3.3. TOT - Monitor for normal operation. TOT - Monitor for normal operation.

4.4. Collective - Adjust as required to maintain 90 to 107% Collective - Adjust as required to maintain 90 to 107% ROTOR RPM.ROTOR RPM.

5.5. Cyclic - Adjust as required to maintain desired Cyclic - Adjust as required to maintain desired AIRSPEED. AIRSPEED.

6.6. Prepare for power-off landing.Prepare for power-off landing.

CAUTIONCAUTION

IF RPM AND TURBINE OUTLET TEMPERATURE IF RPM AND TURBINE OUTLET TEMPERATURE CANNOT BE MAINTAINED, THE ENGINE MUST CANNOT BE MAINTAINED, THE ENGINE MUST BE SHUT DOWN.BE SHUT DOWN.

ENGINE COMPRESSOR STALLSENGINE COMPRESSOR STALLS


1.1. Engine pops.Engine pops.

2.2. High or erratic TURB OUT TEMP.High or erratic TURB OUT TEMP.

3.3. Decreasing or erratic GAS PRODUCER RPM Decreasing or erratic GAS PRODUCER RPM or POWER TURBINE RPM.or POWER TURBINE RPM.

4.4. TORQUE oscillations.TORQUE oscillations.


1.1. Collective Reduce power, maintain slow cruise Collective Reduce power, maintain slow cruise flight.flight.

2.2. TURB OUT TEMP and GAS PRODUCER TURB OUT TEMP and GAS PRODUCER RPM - Check for normal indications. RPM - Check for normal indications.

3.3. ENGINE ANTI-ICING switch - ON.ENGINE ANTI-ICING switch - ON.

NOTENOTE

The severity of the compressor stalls will dictate if the The severity of the compressor stalls will dictate if the engine should be shut down and treated as an engine engine should be shut down and treated as an engine failure. Violent stalls can cause damage to the engine failure. Violent stalls can cause damage to the engine and drive system components, and must be handled as and drive system components, and must be handled as an emergency condition. an emergency condition.

Stalls of a less severe nature (one or two low intensity Stalls of a less severe nature (one or two low intensity pops) may permit continued operation of the engine at pops) may permit continued operation of the engine at a reduced power level, avoiding the condition that a reduced power level, avoiding the condition that resulted in the compressor stall.resulted in the compressor stall.

If pilot elects to If pilot elects to continuecontinue flight: flight:

4.4. Collective - Increase slowly to achieve desired Collective - Increase slowly to achieve desired power level.power level.

5.5. TURB OUT TEMP and GAS PRODUCER TURB OUT TEMP and GAS PRODUCER RPM - Monitor for normal response.RPM - Monitor for normal response.

6.6. Land as soon as practical.Land as soon as practical.

If pilot elects to If pilot elects to shut downshut down engine: engine:

7.7. Throttle - Closed.Throttle - Closed.

8.8. FUEL VALVE switch - OFF.FUEL VALVE switch - OFF.

9.9. Collective - Adjust as required to maintain 90 Collective - Adjust as required to maintain 90 to 107% ROTOR RPM.to 107% ROTOR RPM.

10.10. Cyclic - Adjust as required to maintain desired Cyclic - Adjust as required to maintain desired AIRSPEED.AIRSPEED.

11.11. Prepare for power-off landing.Prepare for power-off landing.

HYDRAULIC SYSTEM FAILUREHYDRAULIC SYSTEM FAILURE


1.1. Grinding or howling noise from pump.Grinding or howling noise from pump.

2.2. Increase in force to move flight controls.Increase in force to move flight controls.

3.3. Feedback forces may be evident during flight Feedback forces may be evident during flight control movement.control movement.

4.4. Cyclic and collective movements are rate Cyclic and collective movements are rate limited.limited.


1.1. Reduce AIRSPEED to 61 to 69 KIAS.Reduce AIRSPEED to 61 to 69 KIAS.

2.2. HYDR SYSTEM circuit breaker - Out. If power HYDR SYSTEM circuit breaker - Out. If power not restored, push breaker in.not restored, push breaker in.

3.3. HYDRAULIC SYSTEM switch - ON; OFF if HYDRAULIC SYSTEM switch - ON; OFF if power not restored.power not restored.


5.5. A run-on landing at approximately 9 KIAS is A run-on landing at approximately 9 KIAS is recommended.recommended.

TAIL ROTOR FAILURESTAIL ROTOR FAILURES

There is no single emergency procedure There is no single emergency procedure for all types of antitorque malfunctions. for all types of antitorque malfunctions. The key to successful handling of a tail The key to successful handling of a tail rotor emergency lies in the pilot's ability to rotor emergency lies in the pilot's ability to quickly recognize the type of malfunction quickly recognize the type of malfunction that has occurred.that has occurred.

COMPLETE LOSS OFCOMPLETE LOSS OFTAIL ROTOR THRUSTTAIL ROTOR THRUST

This is a situation involving a break in the drive This is a situation involving a break in the drive system (e.g., severed driveshaft), wherein the system (e.g., severed driveshaft), wherein the tail rotor stops turning and delivers no thrust.tail rotor stops turning and delivers no thrust.

INDICATIONS:INDICATIONS:1.1. Uncontrollable yawing to the right.Uncontrollable yawing to the right.2.2. Nose down tucking.Nose down tucking.3.3. Possible roll of the fuselage.Possible roll of the fuselage.

NOTENOTEThe severity of the initial reaction The severity of the initial reaction of the helicopter will be affected by of the helicopter will be affected by AIRSPEED, cabin loading, center of AIRSPEED, cabin loading, center of gravity, power being used, and gravity, power being used, and density altitude.density altitude.


HOVERINGHOVERING

Chop throttle and perform a hovering auto-Chop throttle and perform a hovering auto-rotation landing.rotation landing.

A slight rotation can be expected on touchdown.A slight rotation can be expected on touchdown.

IN-FLIGHTIN-FLIGHT

Reduce throttle to idle, immediately enter Reduce throttle to idle, immediately enter autorotation, and maintain a minimum autorotation, and maintain a minimum AIRSPEED of 52 KIAS during descent.AIRSPEED of 52 KIAS during descent.

NOTE NOTE

The large vertical fin may permit controlled flight at low power The large vertical fin may permit controlled flight at low power levels and sufficient AIRSPEED when a suitable landing site is levels and sufficient AIRSPEED when a suitable landing site is not available. not available.

During the final stages of the approach, a mild flare should be During the final stages of the approach, a mild flare should be executed, making sure that all power to the rotor is off.executed, making sure that all power to the rotor is off.

Maintain the helicopter in a slight flare and use the collective Maintain the helicopter in a slight flare and use the collective smoothly to execute a soft, slightly nose-high landing.smoothly to execute a soft, slightly nose-high landing.

Landing on the aft portion of the skids will tend to correct side Landing on the aft portion of the skids will tend to correct side drift. This technique will, in most cases, result in a run-on type drift. This technique will, in most cases, result in a run-on type landing.landing.

FIXED PITCH FAILURESFIXED PITCH FAILURESThis is a situation involving the inability to change the This is a situation involving the inability to change the tail rotor thrust (blade angle) with the anti-torque tail rotor thrust (blade angle) with the anti-torque pedals due to a mechanical problem with the anti-pedals due to a mechanical problem with the anti-torque system.torque system.

INDICATIONS:INDICATIONS:1.1. Lack of directional response.Lack of directional response.2.2. Locked pedals.Locked pedals.

NOTENOTEIf the pedals cannot be moved with a moderate amount If the pedals cannot be moved with a moderate amount of force, do not attempt to apply a maximum effort, of force, do not attempt to apply a maximum effort, since a more serious malfunction condition could since a more serious malfunction condition could result.result.If the helicopter is in a trimmed condition when the If the helicopter is in a trimmed condition when the malfunction is discovered, the TORQUE and malfunction is discovered, the TORQUE and AIRSPEED should be noted, and the aircraft flown to AIRSPEED should be noted, and the aircraft flown to a suitable landing area.a suitable landing area.Combinations of TORQUE, ROTOR RPM, and Combinations of TORQUE, ROTOR RPM, and AIRSPEED will correct or aggravate a yaw attitude, AIRSPEED will correct or aggravate a yaw attitude, and these are what will be used to land the helicopter.and these are what will be used to land the helicopter.

PROCEDURES:PROCEDURES:

HOVERINGHOVERING

Do not chop throttle unless a severe right yaw Do not chop throttle unless a severe right yaw occurs. If pedals lock in any position at a hover, occurs. If pedals lock in any position at a hover, landing from a hover can be accomplished with landing from a hover can be accomplished with greater safety under power-controlled flight greater safety under power-controlled flight rather than by chopping throttle and entering rather than by chopping throttle and entering autorotation.autorotation.

IN-FLIGHT - LEFT PEDAL APPLIED IN-FLIGHT - LEFT PEDAL APPLIED

In a high power condition, the helicopter will yaw to In a high power condition, the helicopter will yaw to the left when power is reduced. Power and the left when power is reduced. Power and AIRSPEED should be adjusted to a value where a AIRSPEED should be adjusted to a value where a comfortable yaw angle can be maintained. If comfortable yaw angle can be maintained. If AIRSPEED is increased, the vertical fin will become AIRSPEED is increased, the vertical fin will become more effective and an increased left yaw attitude will more effective and an increased left yaw attitude will develop. To accomplish landing, establish a power-on develop. To accomplish landing, establish a power-on approach with sufficiently low AIRSPEED (zero if approach with sufficiently low AIRSPEED (zero if necessary) to attain a rate of descent with a necessary) to attain a rate of descent with a comfortable sideslip angle. (A decrease in POWER comfortable sideslip angle. (A decrease in POWER TURBINE RPM decreases tail rotor thrust.) As TURBINE RPM decreases tail rotor thrust.) As collective is increased just before touchdown, left yaw collective is increased just before touchdown, left yaw will be reduced.will be reduced.

IN-FLIGHT - RIGHT PEDAL APPLIEDIN-FLIGHT - RIGHT PEDAL APPLIED

In cruise flight or reduced power situation, the In cruise flight or reduced power situation, the helicopter will yaw to the right when power is helicopter will yaw to the right when power is increased. A low power run-on type landing will increased. A low power run-on type landing will be necessary by gradually reducing throttle to be necessary by gradually reducing throttle to maintain heading while adding collective to maintain heading while adding collective to cushion the landing. If right yaw becomes cushion the landing. If right yaw becomes excessive, roll off the throttle completely.excessive, roll off the throttle completely.

ELECTRICAL FAILURESELECTRICAL FAILURESGENERATOR FAILUREGENERATOR FAILURE


1.1. GEN FAIL caution light illuminated.GEN FAIL caution light illuminated.

2.2. DC loadmeter indicates 0% LOAD.DC loadmeter indicates 0% LOAD.


1.1. Check GEN FIELD and GEN RESET circuit breakers Check GEN FIELD and GEN RESET circuit breakers in.in.

2.2. Place GEN switch to RESET position, then return to Place GEN switch to RESET position, then return to GEN position.GEN position.

3.3. If power not restored, place GEN switch to OFF; land as If power not restored, place GEN switch to OFF; land as soon as practical.soon as practical.

EXCESSIVE ELECTRICAL LOAD EXCESSIVE ELECTRICAL LOAD


1.1. DC loadmeter indicates excessive loads.DC loadmeter indicates excessive loads.

2.2. Smoke or fumes.Smoke or fumes.


1.1. GEN switch - OFF.GEN switch - OFF.

2.2. BAT switch - OFF.BAT switch - OFF.

3.3. LEFT FUEL BOOST circuit breaker - Check LEFT FUEL BOOST circuit breaker - Check IN.IN.

WARNINGWARNINGALTITUDE MUST BE REDUCED BELOW ALTITUDE MUST BE REDUCED BELOW 6,000 FEET PRESSURE ALTITUDE PRIOR 6,000 FEET PRESSURE ALTITUDE PRIOR TO BATTERY DEPLETION.TO BATTERY DEPLETION.

UNUSABLE FUEL MAY BE AS HIGH AS UNUSABLE FUEL MAY BE AS HIGH AS 160 LBS AFTER THE BATTERY IS 160 LBS AFTER THE BATTERY IS DEPLETED DUE TO INABILITY TO DEPLETED DUE TO INABILITY TO TRANSFER FUEL FROM THE FORWARD TRANSFER FUEL FROM THE FORWARD CELLS.CELLS.

NOTENOTEWith all electrical equipment OFF, the battery, With all electrical equipment OFF, the battery, when 80% charged, will operate the left fuel when 80% charged, will operate the left fuel boost pump approximately 3 hours to transfer boost pump approximately 3 hours to transfer fuel from the forward fuel cells, and maintain fuel from the forward fuel cells, and maintain the helicopter within CG limits.the helicopter within CG limits.

For night operation, approximately one (1) For night operation, approximately one (1) hour of battery power will be available.hour of battery power will be available.


SECTION 4PERFORMANCE

POWER ASSURANCE CHECK

A Power Assurance Check chart is provided for the Allison Model 250-C30P engine. The Power Assurance Check chart indicates the minimum percent torque that must be available from an engine meeting the minimum Allison specification. The engine must develop these values in order to meet the performance data contained in this flight manual.

The Power Assurance Check chart may be used to monitor the engine performance periodically.

To perform power assurance check, turn off all sources of bleed To perform power assurance check, turn off all sources of bleed air, including ENGINE ANTI-ICING. Establish level flight at air, including ENGINE ANTI-ICING. Establish level flight at an AIRSPEED of 85 to 105 KIAS or VNE whichever is lower.an AIRSPEED of 85 to 105 KIAS or VNE whichever is lower.

NOTE NOTE

For altitudes above approximately 8000 feet, it may be desirable For altitudes above approximately 8000 feet, it may be desirable to check engine power during IGE hover prior to takeoff. The to check engine power during IGE hover prior to takeoff. The Power Assurance Check chart can be used to accomplish this Power Assurance Check chart can be used to accomplish this procedure. The IGE hover installation losses require as much procedure. The IGE hover installation losses require as much as 2% more power than in flight. Therefore, the hover power as 2% more power than in flight. Therefore, the hover power check may be 2% below that shown, and still achieve predicted check may be 2% below that shown, and still achieve predicted flight manual performance.flight manual performance.

Record the following information from cockpit Record the following information from cockpit instruments: instruments:

• HHpp (Example 6000 ft) (Example 6000 ft)

• OAT (Example 25OAT (Example 25ooC) C)

• TOT (Example 720TOT (Example 720ooC) C)

• TORQUE (Actual reading) TORQUE (Actual reading)

Enter Power Assurance Check chart at observed OAT Enter Power Assurance Check chart at observed OAT (Example 25(Example 25ooC), proceed vertically to intersect C), proceed vertically to intersect indicated TOT (Example 720indicated TOT (Example 720ooC), follow horizontally to C), follow horizontally to intersect Hp (Example 6000 feet), then drop vertically intersect Hp (Example 6000 feet), then drop vertically to read minimum torque available (97%).to read minimum torque available (97%).

NOTENOTE

If cruise power check cannot be accomplished below If cruise power check cannot be accomplished below helicopter 85% torque and the 84 KIAS VNE helicopter 85% torque and the 84 KIAS VNE limitation, perform check at a higher altitude, or in a limitation, perform check at a higher altitude, or in a stabilized 57 KIAS climb. Subtract 1% from the chart stabilized 57 KIAS climb. Subtract 1% from the chart percent torque reading. For the previous example, the percent torque reading. For the previous example, the chart percent torque would become 96%. chart percent torque would become 96%.

If actual torque indication is the same or greater than If actual torque indication is the same or greater than the required chart torque, engine power equals or the required chart torque, engine power equals or exceeds minimum performance specification and the exceeds minimum performance specification and the performance data contained in this manual can be performance data contained in this manual can be achieved.achieved.

NOTENOTE

If actual torque indication is less than the If actual torque indication is less than the required chart torque, engine power is less than required chart torque, engine power is less than minimum specification, and all performance minimum specification, and all performance data contained in this manual cannot be data contained in this manual cannot be achieved. Refer to the appropriate achieved. Refer to the appropriate maintenance manual to determine cause of low maintenance manual to determine cause of low power.power.

DENSITY ALTITUDE DENSITY ALTITUDE

A Density Altitude Chart is provided to aid in A Density Altitude Chart is provided to aid in calculation of performance and limitations. Density calculation of performance and limitations. Density altitude (Hg) is an expression of the density of the air altitude (Hg) is an expression of the density of the air in terms of height above sea level; hence, the less dense in terms of height above sea level; hence, the less dense the air, the higher the density altitude.the air, the higher the density altitude.

For standard conditions of temperature and pressure, For standard conditions of temperature and pressure, density altitude is the same as pressure altitude (Hp). density altitude is the same as pressure altitude (Hp). As temperature increases above standard for any As temperature increases above standard for any altitude, the density altitude will also increase to values altitude, the density altitude will also increase to values higher than pressure altitude.higher than pressure altitude.

The Density Altitude chart expresses density altitude The Density Altitude chart expresses density altitude as a function of pressure altitude and temperature.as a function of pressure altitude and temperature.

The chart also includes the inverse of the The chart also includes the inverse of the square root of the density ratio, which is used to square root of the density ratio, which is used to calculate KTAS by the relation:calculate KTAS by the relation:

KTAS = KCAS x Square root of the density KTAS = KCAS x Square root of the density ratio.ratio.

EXAMPLE: EXAMPLE:

If the ambient temperature is -15If the ambient temperature is -15ooC and the C and the pressure altitude is 6000 feet, find the density pressure altitude is 6000 feet, find the density altitude and true airspeed for 100 KCAS.altitude and true airspeed for 100 KCAS.

Solution:Solution:

a.a. Enter the bottom of the chart at -15 Enter the bottom of the chart at -15ooC. C.

b.b. Move vertically upward to the 6000 foot Move vertically upward to the 6000 foot pressure altitude line. pressure altitude line.

c.c. From this point, move horizontally to the From this point, move horizontally to the left and read a density altitude of 4000 left and read a density altitude of 4000 feet, and move horizontally to the right feet, and move horizontally to the right and read 1.06.and read 1.06.

d.d. True airspeed = KCAS x Square root of True airspeed = KCAS x Square root of the density ratio = 100 x 1.06 = 106 the density ratio = 100 x 1.06 = 106 KTAS.KTAS.

IGE AND OGE HOVER CEILINGS IGE AND OGE HOVER CEILINGS

NOTE NOTE

Hover performance charts are based on 100% ROTOR RPM. Hover performance charts are based on 100% ROTOR RPM.

The Hover Ceiling - In Ground Effect charts and Hover Ceiling The Hover Ceiling - In Ground Effect charts and Hover Ceiling Out Of Ground Effect charts present hover performance Out Of Ground Effect charts present hover performance (allowable gross weight) for conditions of pressure altitude and (allowable gross weight) for conditions of pressure altitude and OAT. Each chart is divided into two areas. OAT. Each chart is divided into two areas.

AREA AAREA A (Unshaded Area) as shown on the hover ceiling charts (Unshaded Area) as shown on the hover ceiling charts presents hover performance for which satisfactory stability and presents hover performance for which satisfactory stability and control has been demonstrated in relative winds of control has been demonstrated in relative winds of 26 knots26 knots (30 (30 MPH) sideward and rearward at all loading conditions. MPH) sideward and rearward at all loading conditions.

NOTE NOTE

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

Tail rotor control margin and/or control of engine temperature Tail rotor control margin and/or control of engine temperature (TOT) may preclude operation in AREA B of the hover ceiling (TOT) may preclude operation in AREA B of the hover ceiling charts when the relative wind is in the CRITICAL WIND charts when the relative wind is in the CRITICAL WIND AZIMUTH AREA.AZIMUTH AREA.

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

CAUTIONCAUTION

CAUTION SHOULD BE EXERCISED CAUTION SHOULD BE EXERCISED WHEN OPERATING AT LOW WHEN OPERATING AT LOW AIRSPEEDS ABOVE ALTITUDES PUB-AIRSPEEDS ABOVE ALTITUDES PUB-LISHED IN PERFORMANCE CHARTS.LISHED IN PERFORMANCE CHARTS.

TAIL ROTOR EFFECTIVENESS MAY TAIL ROTOR EFFECTIVENESS MAY BE MARGINAL AT HIGH POWER BE MARGINAL AT HIGH POWER SETTINGS UNDER THESE CON-SETTINGS UNDER THESE CON-DITIONS. DITIONS.

The following example is for use with the Hover The following example is for use with the Hover Ceiling - In Ground Effect chart with ENGINE Ceiling - In Ground Effect chart with ENGINE ANTI-ICING - OFF, and is typical for use of all ANTI-ICING - OFF, and is typical for use of all other hover ceiling charts.other hover ceiling charts.

EXAMPLE: EXAMPLE:

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

Hp = 10,000 ft.Hp = 10,000 ft.

OAT = 30OAT = 30ooC.C.

From the appropriate IGE chart obtain:From the appropriate IGE chart obtain:

A maximum of 3550 pounds for all allowable A maximum of 3550 pounds for all allowable wind conditions, and a maximum of 4150 wind conditions, and a maximum of 4150 pounds when wind conditions are calm or pounds when wind conditions are calm or outside the critical wind azimuth area. outside the critical wind azimuth area.

From the appropriate OGE chart obtain: From the appropriate OGE chart obtain:

A maximum of 3450 pounds for all allowable A maximum of 3450 pounds for all allowable wind conditions, and a maximum of 3550 wind conditions, and a maximum of 3550 pounds when wind conditions are calm or pounds when wind conditions are calm or outside the critical wind azimuth area.outside the critical wind azimuth area.

RATE OF CLIMB RATE OF CLIMB

NOTE NOTE

Rate of Climb charts are presented for various combinations of Rate of Climb charts are presented for various combinations of power settings and ENGINE ANTI-ICING switch positions. power settings and ENGINE ANTI-ICING switch positions.

The rate of climb data shown in the charts are “tapeline" rates, The rate of climb data shown in the charts are “tapeline" rates, which means actual rates of climb. The rate of climb as which means actual rates of climb. The rate of climb as measured with an altimeter will equal the “tapeline” rate of measured with an altimeter will equal the “tapeline” rate of climb only on a standard day with a standard temperature lapse climb only on a standard day with a standard temperature lapse rate. rate.

The following example is for use with Rate of Climb chart at The following example is for use with Rate of Climb chart at takeoff power. The example is typical for use with all other takeoff power. The example is typical for use with all other Rate of Climb charts.Rate of Climb charts.

EXAMPLE: EXAMPLE:

Find the maximum rate of climb that can be attained using Find the maximum rate of climb that can be attained using takeoff power under the following conditions: takeoff power under the following conditions:

• ENGINE ANTI-ICING - OFF ENGINE ANTI-ICING - OFF

• OAT = 10OAT = 10ooC.C.

• Hp = 14,000 ft. Hp = 14,000 ft.

• Gross Weight = 3600 Lbs. Gross Weight = 3600 Lbs.

Enter temperature scale at 10Enter temperature scale at 10ooC and proceed vertically to C and proceed vertically to intersection of the 14,000 feet pressure altitude curve. From intersection of the 14,000 feet pressure altitude curve. From this point, move horizontally to the right to intersect the 3600 this point, move horizontally to the right to intersect the 3600 pound gross weight line. Drop vertically and read a rate of pound gross weight line. Drop vertically and read a rate of climb of 1530 feet per minute.climb of 1530 feet per minute.

RATE OF CLIMB - DOOR(S) OFFRATE OF CLIMB - DOOR(S) OFFReduce Rate of Climb chart data 100 feet per Reduce Rate of Climb chart data 100 feet per minute when operating with any combination of minute when operating with any combination of door(s) off.door(s) off.

BEST RATE OF CLIMB AIRSPEEDBEST RATE OF CLIMB AIRSPEED

• Calibrated airspeed - 52 KCAS.Calibrated airspeed - 52 KCAS.

• Indicated airspeed - 57 KIAS.Indicated airspeed - 57 KIAS.

HEIGHT - VELOCITY DIAGRAMHEIGHT - VELOCITY DIAGRAM

The Height-Velocity Diagram defines the conditions The Height-Velocity Diagram defines the conditions from which a safe landing can be made on a smooth, from which a safe landing can be made on a smooth, level, firm surface following an engine failure.level, firm surface following an engine failure.

The Height-Velocity Diagram is valid only when the The Height-Velocity Diagram is valid only when the helicopter gross weight does not exceed the limits of helicopter gross weight does not exceed the limits of the Altitude Versus Gross Weight Limits for Height-the Altitude Versus Gross Weight Limits for Height-Velocity Diagram.Velocity Diagram.

AIRSPEED CALIBRATIONAIRSPEED CALIBRATION

Refer to AIRSPEED INSTALLATION Refer to AIRSPEED INSTALLATION CORRECTION TABLE for airspeed installation CORRECTION TABLE for airspeed installation correction during level flight.correction during level flight.

BH206L3BH206L3

WEIGHT AND BALANCEWEIGHT AND BALANCE

WEIGHT EMPTY CENTER OF WEIGHT EMPTY CENTER OF GRAVITY GRAVITY

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

GROSS WEIGHT CENTER OF GRAVITY GROSS WEIGHT CENTER OF GRAVITY

It shall be the pilot's responsibility to ensure It shall be the pilot's responsibility to ensure that the helicopter is properly loaded so that the that the helicopter is properly loaded so that the entire flight is conducted within the limits of the entire flight is conducted within the limits of the Gross Weight Center of Gravity chart in Gross Weight Center of Gravity chart in BHT206L3-FM-l. BHT206L3-FM-l.

The gross weight center of gravity may be The gross weight center of gravity may be calculated from the helicopter Actual Weight calculated from the helicopter Actual Weight Record (historical records) and the Loading Record (historical records) and the Loading Tables in the flight manual, or in appropriate Tables in the flight manual, or in appropriate flight manual supplements to assure safe flight manual supplements to assure safe loading.loading.

COCKPIT AND CABIN LOADINGCOCKPIT AND CABIN LOADING

A minimum crew weight of 170 pounds in the cockpit A minimum crew weight of 170 pounds in the cockpit is required.is required.

Passengers may be loaded in any sequence if only one Passengers may be loaded in any sequence if only one crew seat is occupied.crew seat is occupied.

If both crew seats are occupied, only one mid-If both crew seats are occupied, only one mid-passenger is permitted unless there are two aft passenger is permitted unless there are two aft passengers.passengers.

If any doors are removed, gross weight shall be If any doors are removed, gross weight shall be computed. The cabin floor loading limit is 75 pounds computed. The cabin floor loading limit is 75 pounds per square foot.per square foot.

BAGGAGE COMPARTMENT LOADINGBAGGAGE COMPARTMENT LOADING

The baggage compartment is accessible from the left The baggage compartment is accessible from the left side of the fuselage and contains approximately 16 side of the fuselage and contains approximately 16 cubic feet of space.cubic feet of space.

The baggage compartment has a load limit of The baggage compartment has a load limit of 250250 poundspounds, not to exceed , not to exceed 86 pounds per square86 pounds per square. These are . These are structural limitations only, and do not infer that the structural limitations only, and do not infer that the CG will remain within approved limits.CG will remain within approved limits.

When weight is loaded into the baggage compartment, When weight is loaded into the baggage compartment, indiscriminate crew, passenger, and fuel loading can indiscriminate crew, passenger, and fuel loading can no longer be assumed, and the pilot must compute no longer be assumed, and the pilot must compute gross weight CG to assure loading within approved gross weight CG to assure loading within approved limits.limits.

Loading of the baggage compartment should be Loading of the baggage compartment should be from front to rear.from front to rear.

The load shall be secured to tiedown fittings if The load shall be secured to tiedown fittings if shifting of the load in flight could result in shifting of the load in flight could result in structural damage to the baggage compartment structural damage to the baggage compartment or in gross weight center of gravity limits being or in gross weight center of gravity limits being exceeded.exceeded.

The center of gravity shall be computed with The center of gravity shall be computed with the load in the most adverse position.the load in the most adverse position.

FUEL LOADINGFUEL LOADING

At the beginning of any flight with full fuel on At the beginning of any flight with full fuel on board, the CG of the fuel moves forward as it is board, the CG of the fuel moves forward as it is consumed because fuel is consumed from the aft consumed because fuel is consumed from the aft fuel cell first. fuel cell first. The maximum forward CG condition The maximum forward CG condition of the fuel occurs when 70 gallons remainsof the fuel occurs when 70 gallons remains..

The CG then begins to move aft as fuel is The CG then begins to move aft as fuel is consumed from the forward fuel cells. consumed from the forward fuel cells. The The maximum aft CG condition of the fuel occurs when maximum aft CG condition of the fuel occurs when 46.9 gallons remains.46.9 gallons remains.

The CG then begins to move forward again as the The CG then begins to move forward again as the remaining fuel is consumed.remaining fuel is consumed.

FLIGHTFLIGHTMANUALMANUAL

QUESTIONQUESTIONS?S?

OPERATIONAL PROCEDURESOPERATIONAL PROCEDURES

ObjectivObjectivee

Know the proper procedures and Know the proper procedures and policies associated with the aircraft policies associated with the aircraft operation under the auspices of the operation under the auspices of the Company Operations Manual and Company Operations Manual and FAR Part 135.FAR Part 135.

REMOTE AREA PREVENTIVE REMOTE AREA PREVENTIVE MAINTENANCE PROCEDURESMAINTENANCE PROCEDURES

ObjectivObjectivee

Know the proper procedures Know the proper procedures associated with aircraft servicing, associated with aircraft servicing, changing igniters, chip detector changing igniters, chip detector inspection, and litter installation.inspection, and litter installation.

ObjectiveObjectiveDemonstrate an understanding and Demonstrate an understanding and retention of the elements discussed in retention of the elements discussed in each segment module.each segment module.

Correct any error or misunderstanding of Correct any error or misunderstanding of an element item to the 100% level.an element item to the 100% level.

BH206 GROUND TRAININGBH206 GROUND TRAININGEXAMINATIONEXAMINATION

FLIGHT MANUAL Objective Know the organization, contents, and revision procedures for the aircraft...

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