bht-412-fm-caa

0* 3IIMODEL 412

f. BHT-41 2-FMCAA

FLIGHT MANUALCAA CONFIGURATION

TYPE CERTIFICATE NO FR 14

REGISTRATION NO

SERIAL NO -. ',

APPROVED BYCHIEF

CIVIL AVIATION AUTHORITYAIRWORTHINESS DIVISION

BRABAZON HOUSEREDHILL

SURREY, ENGLANDDATE October 20. 1981

THIS DOCUMENT SHALL BE CARRIED IN AIRCRAFT AT ALL TIMES

Bell Helicopter i: i 1A Subsldlary of Textron InEVISION 3

POST OFFICE X 42REVISION 3 - 1POST OFFICE BOX 482 · FORT WORTH. TEXAS 76101

2 JANUARY 1984

CAA APPROVED 412 FLIGHT MANUAL Index

SECTION 1

SECTION 2

SECTION 3

SECTION 4

SECTION 5

FLIGHT MANUAL INDEX

PART 1 - CAA APPROVED

LIMITATIONS

NORMAL DRILLS

EMERGENCY/MALFUNCTION DRILLS

PERFORMANCE DATA

CHECKLIST

SECTION 6

SECTION 7

SECTION 8

SECTION 9

SECTION 10

PART 2 - MANUFACTURER'S DATA

WEIGHT AND BALANCE

SYSTEM DESCRIPTIONS/GENERAL

HANDLING AND SERVICING

CONVERSION TABLES

OPTIONAL EQUIPMENT SUPPLEMENTS

Index

CAA APPROVED 412 FLIGHT MANUAL Log of Page

LOG OF PAGES

Original ..... 0 ........ .October 20, 1981Revision .... 1 ........... April 15 1983Revision .... 2 ....... December 20, 1983Revision .... 3 ......... January 12, 1984

RevisionPage No. Page

RevisionNo.

Cover ......................Title.......................Index ......................A/B .......................Signature ...................HL 1/2 .....................i/ii ........................1-1/1-2.....................1-3- 1-12 ..................1-13.......................1-14- 1-16 .................2-1/2-2 ....................2-3 - 2-6 ...................2-7.......................2-8 ........................2-8A/2-8B ..................2-9 - 2-12..................2-12A/2-12B ................2-14......................2-14A/2-14B ................2-15 - 2-18 .................3-1/3-2.....................3-3 - 3-6 ...................3-6A/3-6B ..................3-7........................3-8 - 3-9 ...................3-10 - 3-11 .................3-12 - 3-13. ...............3-14.......................3-15- 3-17 .................3-18......................4-1/4-2 .....................4-3/4-4.....................

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4-5/4-6.....................4-7 - 4-58..................5-1/5-2.....................5-3 - 5-4 ...................5-5........................5-6........................5-7 - 5-8 ...................5-8A/5-8B ..................5-9 - 5-10..................5-11/5-12...................6-1/6-2.....................6-3 - 6-18 ..................7-1/7-2.....................7-3 - 7-8 ........ ..........7-9/7-10. ...................7-11/7-12 . .................7-13 - 7-16.................7-17/7-18...................8-1/8-2.....................8-3 - 8-4 ...................8-5 - 8-6 ...................9/1/9-2.....................9-3- 9-8 ...................9-9/9-10 ....................10-1 .......................10-2.......................

00003033330000000000300003

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

Rev. 3 A/B

CAA APPROVED 412 FLIGHT MANUAL Signature Page

LOG OF CAAAPPROVED REVISIONS

Original. ... 0........ October20, 1981Revision .... 1 ........... April 15, 1983Revision .... 2 ....... .December 20, 1983Revision .... 3 ........ .January12,1984

APPROVED:

for:CHIEFCIVIL AVIATION AUTHORITYAIRWORTHINESS DIVISIONBRABAZON HOUSEREDHILLSURREY, ENGLAND

January 12, 1984

Rev. 3 Signature Page

CAA APPROVED 412 FLIGHT MANUAL Revision Highliqhts

REVISION NO. 3 DATED 12 JANUARY 1984

Chapter/Sections which have been revised are outlined below together with the highlights of the revision

Remove and insert the affected pages as indicated in the lisr of effective pages

Chapter/Section Description of Change Effectivity

All Revision 3 incorporates operational Allinformation pertaining to the DroopRestraint. Main Rotor and StickCentering Indicator.

All Revision 3 supersedes Temporary AllRevision dated February 7. 1983, whenthe Droop Restraint, Main Rotor andStick Centering Indicator Kit 412 7041 14/115 have been installed.

All Revision 3 makes the requirement for Allblade tiedown conditional. Conditionsare provided in Manufacturer's Data.

HIGHLIGHTSHL 112

ORGANIZATIONPART I (Sections 1 through 5) contains CAAapproved data. PART II (Sections 6 through 9)contains supplemental data provided by themanufacturer. Section 10 contains approvedsupplements. See the Table of Contents ofeach section for specific content of thatsection.

CAA APPROVED DATAThis manual meets all CAA requirements forapproved data, and these data are sodesignated. It also contains supplemental datasupplied by the airframe manufacturer.

TERMINOLOGYWarnings, Cautions, and Notes. Warnings,cautions, and notes are used throughout thismanual to emphasize important and criticalinstructions and are used as follows:

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

CAUTION

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

NOTE

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

CAA APPROVED 412 FLIGHT MANUAL Introduction

INTRODUCTION

USE OF PROCEDURAL WORDS

The concept of procedural word usage andintended meaning which has been adhered toin preparing this manual is as follows:

"Shall" has been used only when applicationof a procedure is mandatory.

"Should" has been used only whenapplication of a procedure is recommended.

"May" and "need not" have been used onlywhen application of a procedure is optional.

"Will" has been used only to indicate futurity.never to indicate a mandatory procedure.

ABBREVIATIONS

Abbreviations used throughout this manualare defined as follows:

HD - Density Altitude

ITT - Inter Turbine Temperature

KCAS - Knots Calibrated Airspeed

KIAS - Knots Indicated Airspeed

NI - Gas Producer RPM

Nil - Power Turbine RPM

Nr - Rotor RPM

OEI - One Engine Inoperative

Vne - Never Exceed Velocity

Vno - Normal Operating Velocity

Vtoss - Velocity Takeoff Safety Speed

Vy - Best Rate of Climb Speed

i/ii

CAA APPROVED 412 FLIGHT MANUAL Section 1

* SeZtk 1TABLE OF CONTENTS

PageParagraph Number

Type of Operation .............................................................. ......... 1-3Flight With Doors Off/Open ............................................................. 1-3Flight With Optional Equipment Installed ................................................. 1-3Weight - CG Limitations ................................................................ 1-3Front Seat Weight Limits ................................................................ 1-6Longitudinal Center of Gravity Limits ..................................................... 1-6Lateral Center of Gravity Limits .......................................................... 1-6Airspeed Limitations ......................................................... .......... 1-6Altitude Limitations ...................................................................... 1-6Ambient Air Temperature Limitations ..................................................... 1-7IMC Operation Requirements ............................................................ 1-7Rotor Limitations .............................................................. .......... 1-7Powerplant Limitations .................................................................. 1-7Engine Restart Limitations ............................................................... 1-9Rotor Brake Limitations .................................................................. 1-9Engine Starter Limitations ............................................................... 1-9Generator Limitations .................................................................... 1-9Ground Power Start ............................................................ ......... 1-Transmission Limitations ................................................................. 1-9Fuel and Oil Limitations .................................................................. 1-9Hydraulic System Limitations ............................................................ 1-10Restrictions .................................................................. ........... 1-10Flight Crew ................................................................... .......... 1-10Internal Cargo Limitations ............................................................... 1-10Battery Limitations ............................................................ .......... 1-11AFCS Limitations ........................................................................ 1-11

LIST OF FIGURES

Figure PageNumber Title Number

1-1 Weight-Altitude-Temperature Limitations Chart ............................... 1-41-2 Gross Weight-Center of Gravity Chart ........................................ 1-51-3 Placards and Decals ......................................................... 1-121-4 Instrument Markings ........................................................ 1-13

1-1/1-2


* Set 1TYPE OF OPERATION

The basic configured helicopter is approved asa fifteen-place aircraft and is certified for oper-ation under day or night VMC non-icing condi-tions.

The IMC configured helicopter is certified foroperation during day or night non-icingconditions.

FLIGHT WITH DOORS OFF/OPEN.Refer to AIRSPEED LIMITATIONS.

Flight operation is approved for the followingconfigurations during VMC non-icing condi-tions.

Both crew doors on or off.

SLIDING DOORS - 0.3 IN.REMOVED ( 7.6 mm) AFT

SLIDING DOOR - 1.0 IN.OPEN (25.4 mm) AFT

NOTE

The helicopter may be flown withdoors open or off with BELLSTANDARD INTERIOR or BELLDELUXE INTERIOR installed. Otherinteriors shall be subject to separateapproval.

FLIGHT WITH OPTIONALEQUIPMENT INSTALLED.

Both sliding doors locked open or removedwith both hinged panels installed or removed.

In all cases, door configuration must beidentical for each side of the fuselage.

CAUTION

FLIGHT WITH DOORS REMOVEDOR WITH SLIDING DOORS OPENRESULTS IN A MAXIMUM CHANGEIN CG AS FOLLOWS:

Refer to appropriate Flight Manual Supple-ment(s) for additional Limitations,Procedures, and Performance Data.

The helicopter shall not be flown for publictransport when a hoist is in use or when anexternal cargo suspension hook is in use.

WEIGHT-CG LIMITATIONS

Maximum approved gross weight for takeoffand landing: 11,600 pounds (5.261kilograms).

See Weight-Altitude-Temperature LimitationsChart (figure 1-1) for maximum allowableoperational weights for Group B operations.

CREW DOORSREMOVED

- 0.7 IN.(17.8 mm) AFT

HINGED PANELS- 0.2 IN.REMOVED ( 5.1 mm) AFT

Minimum approved weight for flight is 6400pounds (2903 kilograms).

1-3

Section 1 412 FLIGHT MANUAL CAA APPROVED

WEIGHT - ALTITUDE - TEMPERATURE LIMITATIONS

FOR TAKEOFF. LANDING AND IN-GROUND EFFECT MANEUVERS

NOTE: ALLOWABLE GROSS WEIGHTS OBTAINEDFROM THIS CHART MAY EXCEED AIRCRAFTHOVER CAPABILITY.

(4267) //

GROSS WEIGHT

I412900 -22B

-40-20 0 20 40 60 9 10 11 12

OAT -- °C GROSS WEIGHT - LBS X 1000

GROSS WEIGHT - (kg) X 1000412900-22B

Figure 1-1. Weight-altitude-temperature limitations for takoff.landing, and in-ground-effect maneuvers


12.000

11,000

10.000

o 9000z2

I 8000

o 7000

6000

5000

NOTE: MAX ASYMMETRIC C.G. LIMITSARE 4.5 INCHES ( 14.3 MILLIMETERS)LEFT AND RIGHT

LONGITUDINAL C. G. STA~ MILLIMETERS

3302 3350 3400 3450 3500 3550I I I I I I

3600 3650 ,3658

-5262

\ ,-\ 4000

0

MAXIMUM GROSS WEIGHT ATFORE AND AFT C.G. LIMITS -3500IS 8800 LBS (3992 kg)

MINIMUM WEIGHT 6400 LBS (2903.0 kg.) -30002903

130 132 134 136 138

LONGITUDINAL C. G. STA. ~ INCHES

140 142 144

412100-1C

Figure 1-2. Gross weight-center of gravity chart

1-5


NOTE

The two aft outboard facing seatsshould not be occupied unless at leasttwo of the forward and/or aft facingseats are occupied.

FRONT SEAT WEIGHT LIMITS

Minimum - 170 pounds (77.1 kilograms).

LONGITUDINAL CENTER OF GRAVITYLIMITS

Longitudinal center of gravity limits are fromstation 130 to 144. However, fore and aftlimits are variable depending on gross weight.Refer to GROSS WEIGHT CENTER OFGRAVITY CHART (figure 1-2) and Weight andBalance Data (Section 6).

NOTE

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

LATERAL CENTER OF GRAVITY LIMITS

Lateral center of gravity limits are 4.5 inches(114.3 millimeters) left of, and 4.5 inches(114.3 millimeters) right of the fuselagecenterline.

AIRSPEED LIMITATIONS

NOTE

All airspeed values are Indicated Air-speed (KIAS), except when CalibratedAirspeed (KCAS) is specificallystated. All indicated airspeed values inthis manual require instrument partnumber 412-075-009-105 beinstalled.

For temperatures 20°C (68°F) and above, theVNE at 3.000 feet (914 meters) HD (DensityAltitude) and below is 140 knots.

Decrease VNE 2.5 knots per 1.000 feet (305meters) HD above 3,000 feet (914 meters)HD.

For temperatures below 20°C (68°F), refer toPlacards and Decals (figure 1-3).

The VNE for steady state autorotation is:

105 knots below 10,000 feet (3048 meters),not to exceed VNE Placard for Steady StateFlight.

80 knots above 10,000 feet (3048 meters),not to exceed VNE Placard for Steady StateFlight.

The Vno is VNE minus 10 knots.

Sideward flight or crosswind hover limit is 20knots.

Rearward flight or tailwind hover limit is 20knots.

The VNE with doors off/open is 60 KIAS.

ALTITUDE LIMITATIONS

Maximum operating - 20,000 feet (6096meters) pressure altitude.

Maximum altitude for takeoff, landing, and in-ground-effect maneuvers - 14,000 feet(4267 meters) density altitude.

NOTE

For operations above 10,000 feet(3048 meters) refer to appropriateoperating rules for oxygenrequirements.


AMBIENT AIR TEMPERATURELIMITATIONS

The maximum sea level ambient airtemperature for approved operations is+51.7°C (+125°F) and decreases withpressure altitude at the standard lapse rate of2°C (3.6°F)/1000 feet (304 meters) to20.000 feet (6096 meters). The minimumtemperature for approved operations is -30°C(-22°F).

IMC OPERATIONREQUIREMENTS

IMC LIMITATIONS

Minimum IMC airspeed is 60 KIAS.

REQUIRED EQUIPMENT

In addition to the basic equipment required forCertification, the 412-705-018 IMC Kit shallbe installed and the following equipment shallbe operational for IMC flight.

Heated Pitot-Static System

Dual Windshield Wipers

Copilots Instrument Kit

OPERATIONAL EQUIPMENT

ROTOR LIMITATIONS

ROTOR RPM (Nr) LIMITS - 91 to 104.6%RPM.

Minimum - GW at orgreater than 8000Ibs. (3629 kg).

Maximum

91% RPM

104.6% RPM

POWER PLANT LIMITATIONS

Pratt and Whitney Aircraft of Canada, Ltd.PT6T-3B.

NOTE

Operation in intermediate contin-gency or maximum contingencypower range is intended foremergency use only, when one enginebecomes inoperative due to an actualmalfunction. Routine operation inintermediate or maximum contin-gency power range can affect enginewarranty and service life.

GAS PRODUCER RPM (NI) LIMITS

TWIN ENGINE OPERATION

Maximum Continu- 100.8% RPMous Operation andTakeoff

ONE ENGINE INOPERATIVE (OEI) NI

Maximum Contin-gency (21/ minutes)Range

Maximum Contin-gency (2% minutes)

POWER TURBINE(POWER ON)

Minimum

Continuous Opera-ation

Maximum Contin-uous

Operation withEngine Torque below30%

100.8 to 102.4% RPM

102.4% RPM

RPM (Nil) LIMITS

97%

97 to 100%

100%

ROTOR RPM (Nr) POWER ON -97to 100%RPM.

ROTOR RPM (Nr) POWER OFF.

Minimum - GW Less 80% RPMthan 8000 Ibs. (3629kg).

100 to 104.6%

1-7


NOTE

Operation at power turbine RPM of100 to 104.6% is permissible only ifboth engine torques are at or below30%.

INTERTURBINE TEMPERATURE (ITT)LIMITS

NORMAL OPERATIONS

Maximum 765°CContinuous

Takeoff Power Range 765 to 810 °C(5 Minutes)

Maximum Transient 850°C(6 Seconds)

Maximum for Start- 1090°Cing (Limit 2 secondsabove 960°C)

CAUTION

INTENTIONAL USE OF ITT ABOVE810°C IS PROHIBITED EXCEPTDURING START.

ONE ENGINE INOPERATIVE (OEI)

Continuous OEI 822°CRange (IntermediateContingency

Maximum Contin- 822 to 850°Cgency Range (21/2minutes

Maximum Contin- 850°Cgency Power Limits(2/2 minutes)

TORQUE LIMITS

TWIN ENGINE OPERATION TORQUELIMITS

(Transmission scale on torquementer.)

Twin Engine Max- 84%imum Continuous

Takeoff Range 84 to 100%(5 Minutes)

WARNIN

TAKEOFF POWER NOT TO BEUTILIZED ABOVE 105 KNOTS.

Maximum 100%

NOTE

For normal operation, maximum per-missible torque needle split is 4%.

ONE ENGINE INOPERATIVE (OEI) TORQUELIMITS

(Engine Scale)

Continuous 5 to 76%

Maximum Power 76%

OIL PRESSURE LIMITS

Engine

Minimum -(Below 79% NI) 40 PSI

Normal -(79% to 100% NI) 80 to 115 PSI

Maximum 115 PSI


Combining Gearbox

Minimum (Below 40 PSI97% N11)

Normal (94% to 60 to 80 PSI100% N11)

GENERATOR LIMITATIONS

Maximum 150 Amps perAmmeter

NOTE

Maximum 80 PSI

OIL TEMPERATURE LIMITS

EngineNormal O to 115°C

Combining GearboxNormal O to 115°C

ENGINE RESTART LIMITATIONS

Above 15,000 Feet (4572 Meters) PressureAltitude. Accomplish restart in manual fuelcontrol mode only.

Below 15,000 Feet (4572 Meters) PressureAltitude. Accomplish restart in either manualor automatic fuel control mode.

ROTOR BRAKE LIMITATIONS

Engine starts with rotor brake engaged areprohibited. Rotor brake application is limitedto ground operation and shall not be applieduntil the engines are shut down and rotor R PMhas decreased below 40% Nr.

ENGINE STARTER LIMITATIONS

Limit Starter energizing time to:

30 Seconds ON

60 Seconds OFF

30 Seconds ON

5 Minutes OFF

30 Seconds ON

15 Minutes OFF

Loading above 200 Amps is permittedwhen using generator to assist batterywhen starting second engine.

GROUND POWER START

28V ground power units for starting arelimited to 1000 Amps maximum.

TRANSMISSION LIMITATIONS

TRANSMISSION OIL PRESSURELIMITS

Minimum 30 PSI

Below flight idle 30 to 40 PSI

Continuous 40 to 70 PSI

Maximum 70 PSI

TRANSMISSION OIL TEMPERATURELIMITS

Continuous 15° to 110 ° C

Maximum 110°C

FUEL AND OIL LIMITATIONS

FUEL

Fuel conforming to ASTM D-1655, Type B,NATO F-40, D.E.R.D. 2454, or MIL-T-5624,Grade JP-4, may be used at all ambienttemperatures.

Fuel conforming to ASTM D-1655, Type A. orA-1, NATO F-44, D.E.R.D. 2452. or MIL-T-5624, Grade JP-5, may be used at ambienttemperatures above -30°C (-22°F).

1-9


ENGINE OIL HYDRAULIC PRESSURE LIMITS

Oil conforming to PWA Specification No.521, Type 1, NATO 0-148. and MIL-L-7808Eand subsequent suffixes may be used at allambient temperatures.

Oil conforming to PWA Specification No.521, Type II, NATO 0-156. Royco Turbine Oil555, Aero Shell Turbine Oil 555, and MIL-L-23699, may be used at ambient temperaturesabove -40°C (-40°F). In all cases refer toSection 8 for Approved Vendors and theEngine Maintenance Manual for servicinginstructions.

Maximum

Normal

Caution

Minimum

1100 PSI

900 to 1100 PSI

600 to 900 PSI

600 PSI

HYDRAULIC TEMPERATURE LIMITS

Maximum

RESTRICTIONS

88°C

TRANSMISSION, INTERMEDIATE.AND TAIL ROTOR GEARBOX OIL

Oil conforming to NATO 0-148 and MIL-L-7808E, and subsequent may be used at allambient temperatures. See Section 8 forApproved Vendors.

Oil conforming to NATO 0-156 or MIL-L-23699, or Aero Shell Turbine Oil 555 orRoyco Turbine Oil 555, may be used at allambient temperatures above -40°C (-40°F).Refer to Section 8 for Approved Vendors. Forservicing instructions, in all cases, seeMaintenance Manual.

HYDRAULIC SYSTEMLIMITATIONS

Hydraulic fluid type MIL-H-5606 is authorizedfor use at all ambient temperatures.

Both hydraulic systems shall be operativeprior to takeoff.

WARNING

THE HELICOPTER IS NOT CON-TROLLABLE WITH BOTH HYDRAU-LIC BOOST SYSTEMS INOPERA-TIVE.

Aerobatic maneuvers are prohibited.

FLIGHT CREW

VMC OPERATION

VMC Minimum Flight Crew

The minimum flight crew for VMC operationsshall consist of one pilot.

VMC Passenger Operations

The minimum flight crew consists of one pilot.

The left front seat may be used as a secondpilots station for VMC day and nightoperations.

IMC OPERATION

IMC Minimum Flight Crew

With both helipilots operating the minimumflight crew shall be one pilot.

INTERNAL CARGO LIMITATIONS

Allowable deck loading for cargo is 100pounds per square foot (4.9 kg/100 sq cm).Deck mounted cargo tie-down fittings areprovided and have an airframe structuralcapacity of 1250 pounds (667.0 kilograms)vertical and 500 pounds (226.8 kilograms)

1-10

CAA APPROVED 412 FLIGHT-MANUAL Section 1

horizontal per fitting. Provisions forinstallation of cargo tie-down fittings areincorporated in the aft cabin bulkhead andtransmission support structure and have anairframe structural capacity of 1250 pounds(567.0 kilograms) at 90 ° to the bulkhead and500 pounds (226.8 kilograms) in any directionparallel to the bulkhead. Cargo shall besecured by an approved restraint method thatwill not impede access to the cargo in the eventof an emergency.

BATTERY LIMITATIONS

BATTERY TEMP -

130°F (54.4°C) Battery Case Temperature.

145°F (62.7°C) Battery Internal Temperature.

AFCS LIMITATIONS

A functional AFCS is required for day andnight operations. HP1 and HP2 shall both beturned on prior to takeoff and shall remain onfor duration of flight.

AFCS shall be operated in ATT mode duringIMC flight.

Maximum rate of climb or descent with oneHP inoperative is 1000 ft/min.

WARNING

AFTER BATTERY TEMP LIGHT ILLU-MINATES. THE BATTERY SHALL BEREMOVED. BENCH CHECKED.AND SERVICED IN ACCORDANCEWITH MANUFACTURER'S IN-STRUCTIONS PRIOR TO THERETURN OF BATTERY TO SERVICE.

All phases of flight with one helipilotinoperative shall be executed with hands on.

With one helipilot inoperative, flight dispatchwith passengers is prohibited.

For prolonged ground operation, AFCS shallbe operated in SAS mode only.

1-11

-

1-12

412075-4/-2A

Figure 1-4. Instruments markings (2 of 4)



Introduction ............................................................................. 2 -3Flight Restrictions .................................................... ................... 2-3Flight Planning .......................................................................... 2-3Takeoff and Landing Data ................................................................ 2-3Weight and Balance ..................................................................... 2-3Preflight Check .......................................................................... 2-3Before Exterior Check ............................ ....................................... 2-5Exterior Check .......................................................................... 2-5Interior Check ........................................................................... 2-7Prestart Check .......................................................................... 2-7Starting Engines......................................................................... 2-9Attempted Engine Start With No Light off ........................... 2.............. 2-10Dry Motoring Run ..................................................................... .. 2-11Start Attempt After Dry Motoring Run ................... ................. ............. 2-11Systems Checks ............................ ......... .................................... 2-11Stick Centering Indicator System Checks ................................................. 2-11Hydraulic System Check ................................................. ................ 2-11Electrical System Check ..... ..... .............................................. 2-12Engine Runup ........................................................................... 2-12Engine Fuel Control Check ............................................................... 2-12AFCS Check ............................................... 1............... ............. 2-13AFCS Actuator Centering Check ..................................................... .... 2-13Force Trim Check ...................................................... .................. 2-14Fuel Crossfeed Valve Check .............................................................. 2-14Heater Operation Check ...................................................... ........... 2-14Before Takeoff ................................................................ .......... 2-15Takeoff ................................................. .......................... ..... 2-16In-Flight Operation .......................................................... ............ 2-16Before Landing ............................................... ....................... 2-17Engine Shutdown ........................................................ ............... 2-17After Exiting Helicopter ........................................... ..................... .. 2-17

LIST OF FIGURES


2-1 Preflight Check Sequence ................................................. 2-4

Rev. 3 2-1/2-2


INTRODUCTION

This section contains instructions and pro-cedures covering flight of the helicopter fromthe planning stage, through actual flightconditions, to securing the helicopter afterlanding.

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

The instructions and procedures containedherein are written for the purpose of standard-ization and are not applicable to all situations.

FLIGHT RESTRICTIONS

The minimum, normal, maximum, andcautionary operation ranges for the helicopterand its subsystems are indicated byinstrument markings and placards.

These instrument markings and placardsrepresent careful aerodynamic calculationsthat are substantiated by flight test data.

Refer to Section 1, Limitations, forsubsystems restrictions.

FLIGHT PLANNING

The safe and efficient planning of the missionto be accomplished will provide the pilot withthe data to be used during flight. Theinformation to be used can be compiled asfollows:

Check type of mission to be performed anddestination.

Select appropriate performance charts to beused from Section 4.

TAKEOFF AND LANDING DATA

Refer to Section 1 or appropriate supplementfor takeoff and landing weight limit and toSection 4 for performance information whenplanning various types of missions that requireuse of the data.

WEIGHT AND BALANCE

Ascertain proper weight and balance of thehelicopter as follows:

Consult applicable weight and balanceinstructions provided in Section 6.

Compute takeoff and anticipated landinggross weight, check helicopter center ofgravity (CG) locations, and ascertain weight offuel, oil, payload, etc.

Check that loading limitations listed inSection 1 have not been exceeded.

PREFLIGHT CHECK

A preflight check by the pilot is required. Referto figure 2-1 for preflight sequence.

NOTE

Forthepilotswalk-around and interiorcheck, the following procedure isoutlined. This preflight is not intendedto be a detailed mechanicalinspection, but a guide to help thepilot' check the condition of thehelicopter. It may be made ascomprehensive as conditionswarrant, at the discretion of the pilot.

2-3


Figure 2-1. Preflight check sequence

2-4


BEFORE EXTERIOR CHECK

Mission planning - Completed.

Gross weight and CG - Compute (refer toSection 6).

Publications - Checked.

Portable fire extinguishers - Installed andsecured.

Fuel sumps - Drain as follows:

BOOST PUMP switches - Off.

Fuel switches - Off.

BAT switches - On BUS 1 and BUS 2.

Fuel Sump Drain Buttons (left and right) -Depress.

Fuel Filters - Drain before first flight of day,as follows:

Boost Pump Switches - ON.

Fuel switches - ON.

Fuel filter (left and right) - Drain samples.

Fuel switches - OFF.

Boost pump switches - OFF.

BAT switches - OFF.

EXTERIOR CHECK

1. Cabin area - Condition; all glass clean.

Remote hydraulic filter bypass indicator -Check green.

Static port(s) (left and right) -Unobstructed.

Pitot tube(s) - Cover(s) removed;unobstructed.

Rotor blade - Visually check conditionand cleanliness. Remove tiedown.

Cabin nose ventilators - Unobstructed.

Nose Compartment - Check batteryconnected; door secured.

Battery vent and drain tubes -Unobstructed.

Searchlight and landing light - Stowed.

Antenna - Condition and security.


2. FUSELAGE - CABIN LEFT SIDE.

Copilot door - Condition and operation;glass clean. Check security of emergencyrelease handles.

Passenger door - Condition andoperation; glass clean. Condition of pop-out window.

Position lights - Condition.

Landing gear - Condition; handlingwheels removed.

No. 1 engine air intake - Cover removed;unobstructed.

3. FUSELAGE - AFT LEFT SIDE.

Drain lines - Clean and unobstructed.

No. 1 Engine compartment - Check.

No. 1 Engine oil level - Verify actualpresence of oil in sight gage. Visuallycheck oil level.

Nil governor spring - Check condition.

Engine fire extinguisher - Check bottlepressure gage and temperature range.

2-5


Combining gearbox filter - Check bypassindicator retracted.

Access doors and engine cowling -Secured.


Engine exhaust ejector tubes - Coversremoved; unobstructed.

4. AFT FUSELAGE.

Tailboom - Condition.

Tail rotor driveshaft covers - Secured forflight.

Elevator - Condition and security. Checkfor spring condition by moving elevatortoward the leading edge down position.


Baggage compartment - Cargo secured:door secured.


5. FUSELAGE -- AFT RIGHT SIDE.

Engine fire extinguisher - Check bottlepressure gage and temperture range.

Combining gearbox oil level - Verifyactual presence of oil in sight gage.Visually check oil level.

No. 2 engine compartment - Check.

No. 2 engine oil level - Verify actualpresence of oil in sight gage. Visuallycheck oil level.


CAUTION

DO NOT BEND ELEVATORTRAILING EDGE TAB.

Tail rotor 90 ° gearbox - Verify actualpresence of oil in sight gage. Visuallycheck oil level, filler cap and chip detectorplug.

Tail rotor - Condition and free movementon flapping axis.

Tail skid - Condition and security.

Tail rotor 42 ° gearbox - Verify actualpresence of oil in sight gage. Visuallycheck oil level, filler cap, and chip detectorplug.

Elevator - Condition and security.

Fuel filler - Visually check quantity;secure cap.

6. FUSELAGE - CABIN RIGHT SIDE.

No. 2 engine air intake - Cover removed;unobstructed.

Pilot door - Condition and operation;glass clean. Check security of emergencyrelease handles.


Transmission oil - Verify actual presenceof oil in sight gage. Visually check oil level.



2-6


7. CABIN TOP.

Swashplate, support assembly, andcollective lever - Check condition.

Hub and sleeve assembly - Checkcondition.

Main rotor pitch links - Security andcondition.

Main rotor hub - Check general condition.

Pitch horns - Security and condition.

Elastomeric bearings, lead-lag dampers -Check general condition.

Blade retention bolts - Security andproper latching.

Rotor blades - Visually check conditionand cleanliness.

Droop restraints - Security and condition.

Main driveshaft and coupling - Conditionand security where visible; coupling forgrease leakage and appearance ofoverheating.

Transmission oil filler cap - Secured.

No. 1 and No. 2 hydraulic oil reservoirs -Visually check fluid levels; caps secured.

Antenna(s) - Condition and security.

Combining gearbox oil filler cap -Secured.

Anti-Collision light - Condition andsecurity.

No. 1 and No. 2 Engine air intakes -Unobstructed; check particle separatordoors closed.

Engine and transmission cowling -Secured.

Fresh air inlet screen - Unobstructed.

Rotor brake reservoir cap - Security.

INTERIOR CHECK

Cabin interior - Cleanliness and security ofequipment.

Cargo (if applicable) - Check security.

Protective breathing equipment (if installed)-Condition and properly secured.

Passenger doors - Secured.

PRESTART CHECK

Seat and pedals - Adjust.

Seat belt and shoulder harness - Fasten andadjust.

Shoulder harness inertia reel and lock -Check.

Directional control pedals - Check freedomof movement; position for engine start.

Flight controls - Position for start; friction asdesired.

Collective control head switches - OFF.

Transmission chip detector indicators -Check; reset if required.

Lower pedestal circuit breakers - IN.

Radio equipment - OFF.

Conpass slaving switch(es) - MAG (slaveposition).

Fuel interconnect switch - NORM.

Boost pump switches - OFF.

Fuel crossfeed switch - NORM.

Fuel switches - OFF.

Particle separator switches - NORM.

Rev. 3 2-7


Governor switches - AUTO.

Hydraulic switches - ON.

Step switch - OFF.

Rotor RPM audio switch - Spring loaded toAUDIO.

Force trim switch - ON.

Instruments - Static check.

Altimeter - Set.

Clock - Set.

Fire extinguisher switch - OFF.

Fire pull handles - In (forward).

Aft dome light switches - OFF.

Pitot heater switch - OFF.

Wiper select switch (both) - OFF.

Cargo release switch - OFF.

Vent blower switch - OFF.

Aft outlet switch - OFF.

Heater switch - OFF.

Circuit breakers - In.

All light switches - OFF.

Master caution switch - Spring loaded toNORMAL.

Position lights - OFF.

Anti-collision lights - OFF.

Emergency load switch - NORMAL.

Non-essential bus switch - NORMAL.

Inverters - OFF.

Generators - OFF.

If external power is used - Connect.Check DC voltmeters for 27 ± 1 volts andadjust power source if required.

Battery switches (BUS 1 and BUS 2) - ON;check BATTERY caution light illuminates.

NOTE

Test operate all lights when nightflights are planned or anticipated.Accomplish light tests with externalpower connected or during enginerun-up.

Master caution switch (overhead) - TEST;check all caution panel lights extinguishexcept CAUTION PANEL segment andMASTER CAUTION light. (Both ENG OUTlights and RPM light will dim during test.)

Rotor brake lights - Test. Pull brake ON andcheck that both lights illuminate: return toOFF and check lights extinguish.

NOTE

Rotor brake shall be OFF at all timeswhen the engines are running.

Engine fire warning light - Test.

Baggage fire warning light - Test.

All press to test lights - Test.

Caution panel lights - Test and reset.

Inverter 1 - ON; check No. 1 AC voltmeter for104 to 122 volts.

Inverter 2- ON; check No. 2 AC voltmeterfor104 to 122 volts.

Fuel quantity gage - Test.


STARTING ENGINES

Twist grips Rotate No. 1 twist grip fullopen, then back against flight idle stop.Actuate No. 1 flight idle stop release, roll No.1 twist grip to full closed, then apply friction asdesired. Repeat procedure using No. 2 twistgrip and No. 2 flight idle release.

NOTE

When either flight idle stop release isactivated, the appropriate flight idlestop plunger will not release ifpressure is applied toward the closedposition of the twist grip.

Moderate throttle frictions should be appliedto overcome follow-through couplingbetween twist grips.

RPM increase-decrease switch - DECR for 8seconds.

NOTE

Either engine may be started first;however, the following procedure isprovided for starting No. 1 enginefirst.

NO. 1 ENGINE START

No. 1 Boost pump switch - ON; check No. 1FUEL BOOST light out.

No. 1 Fuel switch - ON. (FUEL VALVEcaution lights will illuminate momentarily.)

Rev. 3 2-8A/2-8BI


No. 1 Fuel pressure - Check.

Rotor - Clear.

No. 1 Engine starter - Engage. Observestarter limitations.

No. 1 Engine oil pressure - Indicating.

No. 1 Twist grip - Open to flight idle at 12%NI RPM minimum.

ITT - Monitor to avoid a hot start. MaximumITT during start is 1090°C. not to exceed twoseconds above 960°C. If ITT continues to rise,abort start by activating flight idle stop releaseand rolling twist grip to full closed. Startershould remain engaged until ITT decreases.Consult PT6T-3B Engine MaintenanceManual if ITT limits are exceeded.

Collective pitch - Lower as rotor RPMincreases.

CAUTION

IF STICK CENTERING INDICA-TOR SYSTEM IS INOPERATIVE,NR FOR GROUND OPERATIONSHALL BE 97% OR ABOVE.

ON SIDE SLOPES GREATERTHAN FIVE DEGREES. DISRE-GARD CYC CTR CAUTIONLIGHTS AND POSITION CYCLICAS REQUIRED.

No. 1 Engine Starter - Disengage at 55% NIRPM.

Gas Producer - Check 61 ± 1% NI RPM whentwist grip is on flight idle stop.

Engine, transmission and gearbox oilpressures - Check.

No. 1 PART SEP OFF light - Checkextinguished.

No. 1 Twist grip - Increase to 85% Nil RPM;friction as desired.

If external power is used, proceed to No.2 ENGINE START. If battery was utilized,proceed as follows:

NI RPM - Check 71% minimum.

No. 1 Generator switch - ON.

NOTE

Before attempting generator assistedstart on second engine; it isrecommended that the battery becharged until the ammeter load dropsbelow 150 amps.

NO. 2 ENGINE START

No. 1 Ammeter - Check at or below 150amps.

No. 2 Boost pump switch - On; check. No. 2FUEL BOOST light - Out.

No. 2 Fuel switch - ON (FUELVALVE cautionlight will illuminate momentarily).

No. 2 Fuel pressure - Check.

Cyclic - Position as necessary to extinguishCYC CTR caution lights.

NOTE

At RPM between 95 and 105% NR,CYC CTR caution lights are inhibited.

No. 2 Engine starter - Engage. Observestarter limitations.Cyclic - Center as rotor RPM increases.

Rev. 3 2-9


No. 2 Engine oil pressure - Indicating. No. 2 Generator switch - ON. (BAT BUS 1will switch off automatically.)

No. 2 Twist grip - Open to flight idle at 12%NI RPM minimum.

CAUTIONITT - Monitor. Observe ITT limitations.

No. 2 Engine starter - Disengage at 55% NI ONLY BATTERY BUS 2 SWITCHRPM. SHOULD REMAIN ON WITH

BOTH GENERATORS OPERAT-ING.AUTIONCAUTION

ENSURE THAT THE SECONDENGINE HAS ENGAGED. A NON-ENGAGED ENGINE IS INDICATED DURING RPM INCREASE. ANYBY 10 TO 15% HIGHER Nil RPM ABNORMAL INCREASE IN 1THAN THE ENGAGED ENGINE AND PER REV VIBRATION MAYNEAR ZERO TORQUE. IF A NON- INDICATE ONE OR MORE MAINENGAGEMENT OCCURS. CLOSE RESTRAINTS

ENGAGED ENGINE. WHEN THENON-ENGAGED ENGINE. W HEN THE STATIC POSITION. VERIFYNON-ENGAGED ENGINE HASSTOPPED, SHUT DOWN THE PROPER OPERATION PRIORTOENGAGED ENGINE. FLIGHT.

IF A SUDDEN (HARD) ENGAGE- NR - 77% or above.MENT OCCURS, SHUT DOWNBOTH ENGINES. MAINTENANCE Radios - ON as required.ACTION IS REQUIRED.

Caution panel lights - Check all extinguished.

Engine tachometer and torquemeter - Verify ATTEMPTED ENGINE START WITH NOengagement of second engine. LIGHT OFF

Engine oil pressures - Check. When the power section of the engine fails tolight off within 15 seconds after the twist grip

No. 2 PART SEP OFF light - Check extin- has been opened to flight idle, the followingguished. action is recommended:

NI RPM - Check 71% minimum. Flight idle stop release - Actuate.

Twist grip - Rotate to full closed.

If external power was used - Starter - Disengage.Disconnect. Generator 1 and 2 switches- ON, one at a time. Battery BUS 1 will Fuel switch - OFF.switch off automatically.

______________________Boost pump switch - OFF.

2-10 Rev. 3


After the NI RPM has decreased to zero, allow30 seconds for fuel to drain from the engine.Conduct a "dry motoring run" beforeattempting another start.

DRY MOTORING RUN

The following procedure is used to clear anengine whenever it is deemed necessary toremove internally trapped fuel and vapor, or ifthere is evidence of a fire within the engine.

Twist grip Full closed.

Boost pump switch - ON.

Fuel switch - ON.

Ingniter circuit breaker - Pull out.

Starter - Engage for 15 seconds, thendisengage.

Fuel switch - OFF.

Boost pump switch - OFF.

Igniter circuit breaker - Push in.

Cyclic - Displace forward. Observe CYCCTR caution lights illuminate.

Cyclic - Displace aft. Observe CYC CTRcaution lights extinguish then illuminate.


Cyclic - Displace right. Observe CYC CTRcaution lights illuminate.

Cyclic - Displace left. Observe CYC CTRcaution lights extinguish then illuminate.


FLIGHT CONTROLS CHECK

CAUTION

DURING EXTREME COLDAMBIENT TEMPERATURESLIMIT CYCLIC MOVEMENTSUNTIL TRANSMISSION OILTEMPERATURE REACHES15°C.

START ATTEMPT AFTER DRYMOTORING RUN.

Allow the required cooling period for thestarter before proceeding. Follow normal startsequence as described on preceding pages.

SYSTEMS CHECKS

STICK CENTERING INDICATOR SYSTEMCHECKS.

CAUTION

CYCLIC DISPLACEMENT OFMORE THAN 1.5 INCHES FROMCENTER IS NOT REQUIRED TOCHECK THE SYSTEM. IF THECYC CTR CAUTION LIGHTS DONOT ILLUMINATE WITHIN A 1.5INCH DISPLACEMENT, THESYSTEM IS INOPERATIVE.

Control frictions - Off.

Collective lock - Removed.

Force trim switch - OFF.

HYDRAULIC SYSTEM CHECK.

Hydraulic system No. 1 switch OFF. Notethat HYDRAULIC caution light and MASTERCAUTION light illuminate and system No. 1pressure drops to zero. Check that cyclic andcollective controls operate normally. Note anincrease in control pedal forces in bothdirections.

NOTE

An electrical interlock prevents bothhydraulic systems from beingswitched off at the same time. If onesystem is off and the second systemis switched off, the second systemwill remain on.

Rev. 3 2-11


NOTE NOTE

CYC CTR caution lights may The No. 1 hydraulic system willilluminate momentarily during cyclic operate 10 ° to 20°C cooler than thecontrol check. No. 2 hydraulic system.

ELECTRICAL SYSTEM CHECK

Hydraulic system No. 2 switch - OFF. Notethat hydraulic system No. 2 remains DC Voltmeters Check 27 1 Vdc.operational.

AC Voltmeters - Check 104 to 122 Vac.

Hydraulic system No. 2 switch - ON. .Ammeters - Check within limits.Hydraulic system No. 1 switch - ON. Notethat HYDRAULIC caution light and MASTERCAUTION light extinguish. Check that hec that the tems remaoperational.hydraulic system No. 1 regains normalpressure and that control pedal forces return One helipilot.One helipilot.to normal.

One NAV-COM.Hydraulic system No. 2 switch - OFF. Notethat HYDRAULIC caution light and MASTER Panel lights.CAUTION light illuminate. Check thathydraulic system No. 2 pressure drops to zero ICS lights.and that all controls operate normally.

Essential engine instruments.

NOTEEssential navigation instruments.

CYC CTR caution lights mayCTR caution lights may Emergency Load switch - Normal. Checkilluminate momentarily during cyclic

control check. that all loads dropped regain power.

AC System - Check as follows:Hydraulic system No. 1 switch - OFF. Notethat hydraulic system No. 1 remains Inverter 1 switch - OFF: check INVERTER 1operational. caution light illuminates. Check No. 1 and No.

2 ac voltmeters for indication inverter 2 hasHydraulic system No. 1 switch - ON. assumed all ac loads. Return inverter 1 switch

to an ON position.Hydraulic system No. 2 switch - ON. Notethat HYDRAULIC caution light and MASTER Inverter 2 switch - OFF; check INVERTER 2CAUTION light extinguish. Check that caution light illuminates. Check No. 1 and No.hydraulic system No. 2 returns to normal. 2 AC voltmeters for indication inverter No. 1

has assumed all AC loads. Return inverter 2Both hydraulic systems shall be operational switch to ON.prior to takeoff.

ENGINE RUNUPControl frictions - Adjust to desired level. 0

Engine oil temperatures and pressures --Force trim switch - ON. Within limits.

2-12 Rev. 3


''ransmission oil temperatures and pressures-- Within limits.

Gearbox oil temperature and pressure -Within limits.

NOTE

During extreme cold ambienttemperatures do not increase thethrottles above flight idle until themain transmission oil temperature isat or above 1 5°C. The No. 1 hydraulicsystem will run 10 ° to 200 C coolerthan the No. 2 system.

Ammeters Within limits.

NOTE

No. 2 ammeter will indicate a higherload than No. 1 until battery is fullycharged.

ENGINE FUEL CONTROL CHECK

Twist grips (both) - Flight idle.

WARNING

DO NOT ALLOW NI SPEED TODECREASE BELOW 50%.

Rev. 3 2-12A/2-12B


NOTE AFCS ACTUATOR CENTERING CHECK

In the vicinity of 8,000 feet pressurealtitude, NI RPM may not changesignificantly when manual fuelcontrol is selected.

Governor switch (No. 1 or No. 2) - MANUALposition: observe a change in NI RPM andGOV MANUAL light on caution panel. Openrespective twist grip carefully to assure NIresponds upward, then return twist grip toflight idle position. Return governor switch toAUTO. Check for a return to original NI RPMand GOV MANUAL caution lightextinguishes. Check second governor in likemanner.

No. 1 Twist grip - Full open. Check Nil RPMstabilizes at 95 ± 1%.

No. 2 Twist grip - Full open. Check No. 1engine RPM increases 2% and both enginesstabilize at 97 ± 1% Nil RPM.

RPM increase-decrease switch - Full INCR.Check Nil RPM does not exceed 101.5%. Setat 100%.

AFCS CHECK

NOTE

A verification of AFCS actuatorcentering should be accomplished.Failure of the actuators to centercould result in reduced controlmargins and abnormal controlpositions.

NOTE

AFCS actuator centering may bechecked before the 3 minute delayrequired for attitude gyro full erectionspeed by the following procedure:

API - Note SYS 2 actuator position (with HP1and HP2 OFF on the AFCS control panel. HP2API is displayed).

HP1 switch - Depress and hold; observe SYS1 actuator position (HP1 API is displayed aslong as HP1 switch is depressed).

HP1 and HP2 switches - ON. Observe ATTlight on, actuator position indicators (APIs)centered, and caution panel AFCS light out.

WARNING

IF AFCS IS LEFT ENGAGED BUTUNMONITORED DURING GROUNDOPERATION. THE SERIES ACTU-ATORS MAY BE DRIVEN TOHARDOVER POSITIONS AND THECYCLIC CONTROL DISPLACED TOA CONTROL STOP.

NOTE

Both HP1 and HP2 shall beoperational prior to takeoff.

FORCE TRIM switch - ON.

Move cyclic forward, aft, right, left. Observethe APIs do not move.

SYS 2 switch - Press and hold.

Move cyclic forward, aft, right, left. Observethat APIs do not move.

SYS 2 switch - Release.

ATT Trim Switch, right for 2 seconds, then aftfor 2 seconds. Observe APIs move right, up.

SYS 2 switch - Depress - Observe SYS 2actuators agree.

Cyclic Force TRIM release button - Depress.Observe APIs move to center.

2-13


System 2 switch - Release. Observe System1 actuators agree.

SAS/ATT switch - Depress. Observe SASlight on.

Move cyclic right, left. Observe roll API movesright, left.

Move cyclic forward, aft. Observe pitch APImoves down, up.

Move pedals, right, left. Observe yaw APImoves right, left.

System 2 switch - Depress.



System 2 switch - Release.

FORCE TRIM CHECK

Check proper operation of magnetic brakesand cyclic trim release button with force trimswitch ON, then OFF.

NOTE

Force trim caution light will be illum-inated if force trim is OFF.

NOTE

FUEL XFEED and FUEL BOOSTcaution lights will illuminate momen-tarily during test.

If after turning either boost pump off, the fuelpressure remains 4 to 6 PSI below normal(10 ± 4 PSI), the appropriate checkvalve is notfunctioning properly.

No. 1 Boost pump switch - OFF. Check No. 1fuel pressure decreases, then returns tonormal. (This indicates that the crossfeedvalve has opened by Bus No. 1 power and thatthe check valve is functioning properly.)Return switch to ON.

Fuel crossfeed test switch - TEST BUS 2 andhold.

No. 2 Boost pump switch - OFF. Check No. 2fuel pressure decreases, then returns tonormal. Return switch to ON.

Fuel crossfeed test switch - NORM.

Fuel crossfeed switch - OVRD CLOSE.

No. 1 Boost pump switch - OFF. Check fuelpressure drops to zero on affected system.Return switch to ON. Repeat procedure forNo. 2 boost pump switch.


HEATER OPERATION CHECKNOTE

Force trim shall be operable for IFRflight.


FUEL CROSSFEED VALVE CHECK


NOTE

Operation check may be accom-plished at this time or at any timeheater operation is desired.

Nil RPM - Set at 100% (both engines).


NI RPM - Check 75% minimum (bothengines).


I CAUTION

MINIMUM NR FOR GROUNDOPERATION, WITH STICKCENTERING INDICATORSYSTEM INOPERATIVE, IS 97%.

NR - 77% or above._CAUTION


ON SIDE SLOPES GREATERTHAN FIVE DEGREES, DISRE-GARD CYC CTR CAUTIONLIGHTS AND POSITION CYCLICAS REQUIRED.

NOTE

Use of the VG FAST ERECT switcheswill disengage the respectivehelipilot. HP switches will reengagethe appropriate helipilot after VGFAST ERECT switch has beendepressed.

Position lights - As required.

Anticollision light - ON.

Pitot heater - ON; Check ammeter for loadindication. Turn OFF if not required.

Radio(s) Check functioning.

Flight controls - Adjust frictions as desiredfor flight.

Cyclic control - Centered or slightly into thewind.

Cyclic Position as necessary to extinguishCYC CTR caution lights.

NOTE

At RPM between 95 and 105% NR.CYC CTR caution lights areinhibited.

WARNING

MODERATE FRICTION SHALL BEAPPLIED TO EACH THROTTLE TOOVERCOME FOLLOW-THROUGHCOUPLING BETWEEN TWISTGRIPS.

BEFORE TAKEOFF

Engine, gearbox, transmission, hydraulic, andelectrical instruments - Within operatingranges.

Flight instruments - Check operation and set.

Pilot and copilot attitude indicators - Erectand set as necessary.

NOTE

If fast slaving is desired, set roll trim tonull, push and hold VG FAST ERECTswitch (if installed) until attitudeindicator displays zero degrees bankangle.

Twist grips - Full open. Adjust frictions.

Nil RPM - 100% (both engines).

Hydraulic systems No. 1 and No. 2 - ON.

Force trim - As desired. (ON for IMC flight.)

Passenger steps - As desired.

Passenger seat belts - Fastened.

All doors - Secured.

Caution and warning lights - Extinguished.

Rev. 3 2-15


Perform power assurance check before firstflight of the day or as desired. (Refer toSection 4.)

NOTE

It is recommended that the FORCETRIM release button be depressedbefore lift off and touchdown to trimactuators to center positions.

AFCS MODE - Select ATT or SAS operationas desired: ATT mode shall be used during IMCflight.Cyclic control - Apply forward cyclic toaccelerate smoothly.

Collective pitch - Adjust as desired afterreaching Vtocs.

IN-FLIGHT OPERATION

I

TAKEOFF

CAUTION

DURING LIFTOFF TO HOVER.ANY ABNORMAL INCREASE IN1 PER REV VIBRATION MAYINDICATE ONE OR MORE MAINROTOR DROOP RESTRAINTSFAILED TO DISENGAGE FROMSTATIC POSITION. VERIFYPROPER OPERATION PRIOR TOFLIGHT.

Nil RPM 100%.

Area - Clear.

Nil RPM - Adjust INCR-DECR switch toselect desired RPM between 97 and 100%.

Airspeed - Within limits for gross weight andflight altitude.

Engine, gearbox and transmission instru-ments - Within limitations.

NOTE

Refer to ANO for oxygen require-ments above 10,000 feet.

MANEUVERING WITH AFCS IN SASMODE

Hover power Check torque required tohover at four feet skid height.

NOTE

Downwind takeoffs are notrecommended since the publishedtakeoff distance performance will notbe realized. When near zero windconditions prevail, determine truedirection of wind.

NOTE

During takeoff, pitch attitude must beadjusted commensurate with powerapplication to minimize flight in theAVOID area of the Height-Velocitydiagram. Torque shall not exceed 15%above hover power while acceleratingto Takeoff Climbout Speed (Vtocs).(Refer to Section 4.)

Use normal pilot control techniques.

MANEUVERING WITH AFCS IN ATTMODE

Depress cyclic stick FORCE TRIM releasebutton and maneuver as desired. Releasebutton when desired attitude is reached.AUTO PILOT will hold attitude until retrimmedto new attitude. Attitude may also be adjustedwith cyclic beep trim or may be "flownthrough" for momentary attitude changes.

NOTE

Actuators may be saturated to limitauthority when using "fly through"feature.

02-16 Rev. 3


BEFOHI LANDING

Flight controls - Adjust friction as desired.

AFCS Control - ENGAGE ATT/SAS asdesired.

FORCE TRIM switch - ON in ATT MODE, asdesired in SAS MODE.

Twist grips - Check full open.

Nil RPM - 100%.

Force trim -- As desired.


Flight path - Stay clear of AVOID areas of theHeight - Velocity diagram. For landingdistance information in the event of enginefailure during approach, refer to Section 4.

ENGINE SHUTDOWN

NOTE

For prolonged ground operation,AFCS shall not be operated in ATTmode.

ON SIDE SLOPES GREATERTHAN FIVE DEGREES, DISRE-GARD CYC CTR CAUTIONLIGHTS AND POSITION CYCLICAS REQUIRED.

CYCLIC DISPLACEMENT OFMORE THAN 1.5 INCHES FROMCENTER IS NOT REQUIRED TOCHECK THE SYSTEM. IF THECYC CTR CAUTION LIGHTS DONOT ILLUMINATE WITHIN A 1.5INCH DISPLACEMENT. THESYSTEM IS INOPERATIVE.

Cyclic - Displace forward. Observe CYC CTRcaution lights illuminate.





FORCE TRIM release button - Depress andcheck for actuator centering.

HELIPILOT CONTROLLER - Depress HP1and HP2 - Observe that annunciatorsextinguish.

Collective pitch control - Down and locked.

CAUTION


Cyclic - Position and friction as necessary toextinguish CYC CTR caution lights.

Pedals - Center.

Cyclic control and pedals - Centered andfrictioned.

Force trim switch - ON.

NR - 77% or above.

ITT - Stabilize for one minute at 77% NR orabove prior to shutdown (flat pitch).

Engine instruments - Within limits.

Radios - OFF.

Idle stop release switch - ENG 1 position.

Rev. 3 2-17

CAA APPROVED 'Section 2 412 FLIGHT MANUAL

No. 1 Twist grip - Full closed. Check ITT andNI RPM decreasing.

No. 1 Fuel switch - OFF.

No. 1 Boost pump switch - OFF.

Idle stop release switch - ENG 2 position.

No. 2 Twist grip - Full closed. Check ITT andNI RPM decreasing.

No. 2 Fuel switch - OFF.

No. 2 Boost pump switch - OFF.

Generator 1 and 2 switches - OFF.

Inverter 1 and 2 switches - OFF.

Rotor brake - As desired. Apply at or below40% rotor RPM. Return to stowed positionafter main rotor stops.

Pilot - Remain at flight controls until rotorhas come to a complete stop.

Lighting and miscellaneous switches - OFF.

Battery switches - OFF.

Collective down lock - ON.

AFTER EXITING HELICOPTER

If conditions require, perform the following: I(Refer to Manufacturer's Data).

Install main rotor blade tie-down socks onblades and secure to mooring points.

Install exhaust covers and engine inletprotective plugs if conditions require.

2-18 Rev. 3


rs 3

TABLE OF CONTENTS


Introduction .. ........................................................................... 3-3D efinitions . ... . .. ....... .. . . .............................................. 3-3Emergency Drills ......... ...... ................ .......... 3-5Engine Fire . .. .... ................................................................. 3-5Engine Failure .. ...... ..... ......... .......... .. 3-6Hydraulic System Failure ..................... ................ 3-7Cabin Smoke .................. .......................................... 3-7AFCS Hardover or Abnormal Control Perturbation . .... ................................ 3-7Autotrim Runaway ....... ...... ............. ...................... ..... .... .. 3-8Emergency Evasive Maneuver . .................. ......................................... 3-8Tail Rotor Failures ................... . ................. .... .. . .............. 3-8Malfunction Drills ... 3...-..................................................... 3-11Electrical Power Failure .................. ............. .............. ...... 3-14Engine Fuel Control Malfunction ............................ 3-15AFCS Malfunctions ................... ...... ... ... ..... ..... . .. ... ....... 3-16Engine Restart ........... ............. 317Hydraulic Malfunction ................. .. . ....................................... 3-18Heater Malfunction ............... ............................... ... 3-18Stick Centering Indicator System Failure .. ............................................... 3-18

LIST OF TABLES

Table PageNumber Title Number

3-1 Emergency Caution Lights ........................ 3-33-2 Malfunction Caution Lights ........................................... 3-11

Rev.3 3-1/3-2


INTRODUCTION

The following procedures contain theindication of equipment or system failure ormalfunction, the use of emergency features ofprimary or back-up systems, and appropriatewarnings, cautions, and explanatory notes.Table 3-1 lists caution panel wording, faultconditions, and required action.

DEFINITION

1. The following terms indicate thedegree of urgency in landing the helicopter.

LAND ASSOON ASPRACTICAL

The duration of the flightand landing site are at thediscretion of the pilot.Extended flight beyondthe nearest approvedlanding area is notrecommended.

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

LANDIMMEDIATELY

The urgency of the land-ing is paramount. Theprimary consideration isto assure the survival ofthe occupants.

Affected

Normal

Fails to operate in thenormal or usual manner.

Operates in the normalor usual manner.

LAND ASSOON ASPOSSIBLE

Land without delay at thenearest suitable area(i.e., open field) at whicha safe approach and land-ing is reasonably as-sured.

3. The corrective action procedures listedbelow assume the pilot gives first priority toaircraft control and a safe flight path.

PANELWORDING

Table 3-1. Emergency caution lights

FAULTCONDITION

CORRECTIVEACTION

FIRE 1 PULL Fire indication inNo. 1 Enginecompartment.

Pull No. 1 handle. Select MAIN bottle. Close No. 1twist grip, then RESERVE if necessary. Land assoon as possible.

3-3


Table 3-1. Emergency caution lights (Cont)

PANEL FAULT CORRECTIVEWORDING CONDITION ACTION

FIRE 2 PULL Fire indication in Pull No. 2 handle, select MAIN bottle, close No. 2No. 2 Engine twist grip, then RESERVE if necessary. land ascompartment. soon as possible.

BAGGAGE FIRE Smoke in Baggage Reduce powertominimumrequired. Landimmedi-compartment. ately. Inspect tailboom area for damage.

ENG 1 OUT No. 1 engine NI Observe NI, Nil, and ITT engine instruments. IfRPM abnormally engine is not to be restarted, turn off main fuellow. switch, close twist grip, and turn off generator.

Reset remaining engine Nil to normal range. Landas soon as practical.

ENG 2 OUT No. 2 engine NI Observe NI, NII, and ITT instruments. If engine isRPM abnormally not to be restarted turn off main fuel switch, closelow. twist grip, and turn off generator. Reset MASTER

caution light. Reset remaining engine Nil to normalrange. Land as soon as practical. -

C BOX OIL PRESS Combining gearbox Reduce power. Land as soon as possible.oil presure belownormal.

C BOX OIL TEMP Combining gearbox Reduce power. Observe temperature within limits.oil temperature If not, land as soon as possible.above limit.

XMSN OIL TEMP Transmission oil Reduce power. Observe temperature within limits.temperature above If not, land as soon as possible.limit.

XMSN OIL PRESS Transmission oil Reduce power. Land immediately.pressure below limit.

BATTERY TEMP Battery case temp- Battery Switch - OFF. Land as soon as practical.erature above limits. After landing, DO NOT USE HELICOPTER

BATTERY for an engine restart. This will causemore battery heating.

HYDRAULIC Hydraulic pressure Verify fault and affected system from gage read-below limits or ings. Turn off affected system. Land as soon astemperature above possible.limits.

3-4


EMERGENCY DRILLS

ENGINE FIRE

DURING STARTING

NOTE

An engine fire during starting isusually caused by excessive fuel in thecombustion chamber and delayed fuelignition. The result is flames emittingfrom the tail pipe and/or excessive ITTindication.

5. If no landing site is available continuethe takeoff. When an indicated speed of 55knots is attained, pull "T" handle anddischarge one bottle. Land as soon as possible.

6. Discharge remaining bottle ifapplicable.

DURING DESCENTAPPROACH TO LANDING

AND/OR

1. Land as soon as possible.

2. If altitude permits, pull "T" handle anddischarge one bottle during descent.

3. After landing, pull "T" handle anddischarge bottle(s) as applicable.

1. Twist grip - Closed; continue tomotor engine.

If fire persists

2. Fuel switch - OFF.

DURING FLIGHT

#1 ENGINE

1. T-handle of #1 engine - PULL.

3. Boost pump - OFF.

4. Continue to motor engine until ITTdecreases.

DURING TAKEOFF

1. Land as soon as possible. If anappropriate landing site is available, thetakeoff should be terminated and an approachbegun.

2. Pull the "T" handle and discharge onefire bottle.

3. If an altitude in excess of 100 feet (30meters) has been attained, pull the "T" handleand discharge one bottle prior to landing.

4. If altitude permits, pull "T" handle anddischarge one bottle prior to starting landingapproach.

2. Select main bottle to extinguish fire.

3. Twist grip of #1 engine - Closed.

4. #1 Fuel switch - OFF.

5. Fuel crossfeed - OVERRIDE CLOSE.

6. #1 Boost pump - OFF.

7. #1 Generator - OFF.


9. If engine compartment fire warninglight does not go out within 10 seconds, selectreserve bottle by moving leverlock switch toappropriate position.

#2 ENGINE

1. T-handle of #2 engine - PULL.

2. Select main bottle to extinguish fire.

3-5


3. Twist grip of #2 engine - Closed.

4. #2 Fuel switch - OFF.

5. Fuel Crossfeed - OVERRIDE CLOSE.

6. #2 Boost pump - OFF.

7. BATTERY BUS 2 switch - OFF.

8. BATTERY BUS 1 switch - ON.



11. If engine compartment fire warninglight does not go out within 10 seconds, selectreserve bottle by moving leverlock switch toappropriate position.

Secure failed engine as follows:

#1 ENGINE

1. Fuel Crossfeed - OVERRIDE CLOSE.

2. #1 Fuel Switch - OFF.

3. #1 Boost Pump - OFF.

4. #1 Twist Grip - Closed.


6. Interconnect valve - OPEN.

7. Reset #2 engine N11 to normal range.

8. Establish OEI cruise speed of 100knots.

ENGINE FAILURE

SINGLE ENGINE FAILURE

NOTE

The normally operating engines NIIspeed is allowed to drop to 97% duringtransition from two (2) engineoperaion to single (1) engineoperation. When the best rate of climbairspeed (65 knots) is obtained, the NIlshould be increased to normaloperating range of 97% to 100%.

Evidence of an engine failure (or flame-out)will result in the following:

1. ENG 1 OUT or ENG 2 OUT - Light.

3. NI below 61% ± 1% and decreasing.

3. Nil below 85% and decreasing.

4. ITT below 400°C and decreasing.

#2 ENGINE

1. Fuel Crossfeed-- OVERRIDE CLOSE.

2. #2 Fuel Switch - OFF.

3. #2 Boost Pump - OFF.

4. #2 Twist Grip - Closed.

5. BATTERY BUS 1 Switch - ON.

6. BATTERY BUS 2 Switch - OFF.


8. Interconnect valve - OPEN.

9. Reset #1 engine NIl to normal range.

10. Establish OEI cruise speed of 100knots.

Flight can be continued on remaining engineuntil a desirable landing site is available. Referto Performance Charts in Section 4.

3-6


NOTE LIGHT AND TACHOMETER INDI-CATION WILL RESULT IN LOSS OFCONTROL.

If an engine restart is to be made, referto Engine Restart paragraph of this INDICATIONS:section.

TWIN ENGINE FAILURE 1. Leftyaw.1. Collective pitch - Reduce. Establish

autorotative glide at 65 to 70 knots.

2. Twist grips - Full closed (BOTH).

3. Main Fuel Valves- Off if restart is notto be attempted (BOTH).

4. Fuel Boost Pumps - Off if restart isnot to be attempted (BOTH).

5. Accomplish autorotative landing.

NOTE

Best angle of glide for autorotation is94 knots (sea level).

MAIN DRIVESHAFT FAILURE

WARNING

_ FAILURE OF THE MAIN DRIVE-SHAFT TO THE TRANSMISSIONWILL RESULT IN COMPLETE LOSSOF POWER TO THE MAIN ROTOR.ALTHOUGH THE COCKPIT INDI-CATIONS FOR A DRIVESHAFTFAILURE ARE SOMEWHAT COM-PARABLE TO A DUAL ENGINEFAILURE, IT IS IMPERATIVE THATAUTOROTATIVE FLIGHT PROCE-DURES BE ESTABLISHED IMMEDI-ATELY. FAILURE TO REACT IMME-DIATELY TO THE LOW ROTORRPM AUDIO SIGNAL, WARNING

Rev. 2 3-6A/3-6B


2. Rapid decrease in NR.

3. Rapid increase in Nil.

4. Illumination of ROTOR RPM warninglight with audio.

5. Possible increase in noise due to:

a. Overspeeding engine turbines.

b. Overspeeding C BOX.

c. Driveshaft breakage.

PROCEDURES:

1. Collective - As required to establishautorotation descent.

2. Airspeed - Establish airspeed forminimum rate of descent or maximum glide.

3. Throttles - Off, if time permits.

4. Controls - As required for autorotativelanding.

HYDRAULIC SYSTEM FAILURE

INDICATIONS

1. MASTER caution light illuminated.

2. HYDRAULIC system light illuminated.

3. Fluctuating or no hydraulic pressure inaffected system.

4. Increased pedal forces (if No. 1 systemhas failed).

PROCEDURES

1. MASTER caution light - Reset.

2. Failed system - Identify positively.

3. Failed system - Off.


WARNING

DO NOT EXTEND FLIGHT WITHFAILED HYDRAULIC BOOSTSYSTEM. THE HELICOPTER IS NOTCONTROLLABLE WITH BOTHHYDRAULIC BOOST SYSTEMSINOPERATIVE.

CABIN SMOKE, ETC.

INDICATION

1. Smoke, toxic fumes, etc., in cabin.

PROCEDURE

1. Ventilation switch - VENT.

2. Vents, windows, cabin doors - Open.


AFCS HARDOVER OR ABNORMALCONTROL PERTURBATION

WARNING

IF HP1 OR HP2 FAILS DURINGFLIGHT, REMAINDER OF FLIGHTSHALL BE EXECUTED HANDS ON.

Helicopter attitude - Press FORCE TRIMrelease and correct with cyclic and pedals.

Actuator Position Panel - Check. If anyposition indicator shows maximum displace-ment or erratic operation of any actuator, turnHP1 switch OFF. Land as soon as practical.

Actuator Position Panel - Check HP2 system.If either pitch or roll position indicators showmaximum displacement or erratic operation ofany actuator, turn HP2 switch OFF. Land assoon as practical.

Rev. 2 3-7


AUTOTRIM RUNAWAY

NOTE

An autotrim runaway will beevidenced by the cyclic stick beingdriven or displaced in a directionopposite to ATT/SAS actuator APIindications (HP1 or HP2). This condi-tion occurs because the seriesactuators will be driven to limitauthority to compensate for theautotrim runaway. When theactuators are saturated (on stops), thehelicopter will respond to the runawaytrim command; however, with eitherHP1 or HP2 inoperative, the autotrimwill be automatically cut off twoseconds after actuator saturation.

COMPLETE LOSS OF TAIL ROTORTHRUST

This is a situation involving a break in the drivesystem, such as a severed driveshaft, whereinthe tail rotor stops turning and delivers nothrust. A failure of this type, in powered flight,will result in the nose of the helicopterswinging to the right (left side slip) and usuallya roll of the fuselage. Nose down tucking willalso be present. The severity of the ships initialreaction will be affected by airspeed, cabin-loading, center of gravity, power being used,and density altitude.

Corrective Action

1. HOVERING. Chop throttles (twistgrips) immediately and make a hovering auto-rotation landing. A slight rotation can beexpected on touchdown.

FORCE TRIM release button (cyclic stick)Depress to center actuators and retrimhelicopter to desired attitude.

APIs - Monitor for proper operation.

EMERGENCY EVASIVEMANEUVER

Flight controls - Use as required to maneuverhelicopter.

FORCE TRIM release button - Depress andhold until reaching desired attitude, thenresume AFCS control.

TAIL ROTOR FAILURES

The key to successful handling of a tail rotoremergency lies in the pilots ability to quicklyrecognize the type of malfunction and to selectthe proper emergency procedure.

Following is a discussion of some types of tailrotor malfunctions and their probable effects.

2. CLIMB. Chop throttles and lowercollective pitch immediately. Establish a glidespeed slightly above normal autorotationapproach speed. With the higher powerrequired in a climb maneuver, the degree ofright yaw will be greater. If a turn is required toreach a more desirable place to land or to aligninto the wind, make it to the right. A turn to theright can be more nearly streamlined by theuse of a little power. Once aligned for landing,maintain heading in the following manner:

a. If the nose is turning to the right withpower off, a "pulse" of up-collective willproduce more friction in the mast thrustbearings creating a left moment. The greaterthe input of the pulse, the more the responseshould be. By moving the collective upwardabruptly, you create more load on the rotor. Donot hold the collective up, as the rpm willdecrease lower than desirable. It is essentialthat the collective is returned to the downposition for autorotation. This cycle is onepulse. The pulse should be rapid (up and down)and not used at low altitudes.

3-8


WARNING

DO NOT ALLOW ROTOR RPM TODECAY BELOW MINIMUM LIMITS.

b. Should the nose turn left with poweroff, a slight addition of power should arrest it.Further increase in power results in more rightturn response.

c. During the final stages of theapproach, a mild flare should be executedmaking sure that all power to the rotor is OFF.Maintain the helicopter in a slightflare and usethe collective smoothly to execute a soft,slightly nose-high landing. Landing on the aftportion of the skid will tend to correct sidedrift. This technique will, in most cases, resultin a run-on type landing.

3. LEVEL FLIGHT OR POWER DIVE.Chop throttles and reduce pitch immediately.Attain an airspeed slightly above the normalautorotative glide speed.

NOTE

If altitude permits with airspeed above60 knots, throttle and pitch can begently applied to see if some degree ofpowered flight can be resumed. If anyadverse yawing is experienced, re-enter autorotation and continuedescent to a landing. The landingtechnique is the same as prescribedfor the climb condition, in paragraph2.. step c.. above.

4. DESCENT (LOW POWER OR POWEROFF).

a. If the throttles are not off at the timeof the failure, roll them off.

b. Proceed as prescribed in the previouscondition of level flight, step 3., above.

LOSS OF TAIL ROTOR COMPONENTS

The loss of any tail rotor components willresult in a forward center of gravity shift.Other than additional nose down trim, thissituation would be quite similar to completeloss of tail rotor thrust as discussed above.

FIXED PITCH FAILURES

Failures of this type (broken tube, jammedguide, etc.) are characterized either by a lack ofdirectional response when a pedal is pushed orthe pedals will be in a locked position. If thepedals cannot be moved with a moderateamount of force do not attempt to apply amaximum effort, since a more seriousmalfunction and set of circumstances couldresult. If the helicopter is in a trimmedcondition when the malfunction is discovered,the engine power and airspeed should benoted and the aircraft flown to a suitablelanding area. Combinations of engine torque,rotor rpm, and airspeed will correct oraggravate a yaw attitude and these are whatwill be used to land the aircraft.

Corrective Action

1. HOVERING. Do notchopthrottlesunlessasevere right yaw occurs. If pedals lock inany position at a hover, landing from ahover can be accomplished with greatersafety under power controlled flight ratherthan by chopping throttle and enteringautorotation.

3-9


2. FORWARD FLIGHT. If control is lost although the helicopter nose may be displaced toduring climb (left pedal forward), cruise the left (depending on how far the pedal is(approximately neutral pedals), and descent forward). Maintain about 60 knots during the(right pedal forward), a descent and landing initial part of the approach.can be safely effected by use of power andthrottle changes.

(2) On final approach, reducethrottles to minimum operating rpm (91% Nr)

a. Right Pedal Locked Forward of and simultaneously begin a slow decelerationNeutral: so as to arrive at a point about two feet above

the intended touchdown area as effectivetranslational lift is lost.

(1) Power should be reduced andengine rpm maintained within the green arc. collectve pitch (maintain-This will help streamline the helicopter in

left turns, but airspeed should be maintained, ec opter wt te intended landing path Ifhelicopter with the intended landing path. Ifnot aligned after pitch application, increasethe throttle to further help with the alignment.

(2) Execute a shallow to normal Allow the helicopter to touch down at near)approach, maintaining engine rpm and an zero ground speed, maintaining alignmentairspeed of about 60 knots during the initial with the throttle.part of the approach.

c. Pedals Locked in Neutral:

(3) At 50 to 75 feet AGL and when (1) Reduce power and maintainthe landing area can be made, start a slow engine rpm within the green arc. Normal turnsdeceleration to arrive at the intended landing can be safely made under these conditions.point with about 25 knots indicated airspeed. Execute a shallow approach, holding 60 knots

indicated airspeed during the initial part of theapproach.

(4) At 2-5 feet AGL, slowly reducethrottle to overcome the yaw effect and allow (2) At 50 to 75 feet AGL and whenthe helicopter to settle. When aligned with the the landing area can be made, start a slowlanding area, allow the aircraft to touch down. deceleration to arrive at the intended landingAfter ground contact use collective and point with 25 knots indicated airspeed.throttle as necessary to maintain alignmentwith the landing strip, and minimize forwardspeed. lfthehelicopterstartstoturn, movethe (3) At 2-5 feet AGL, use throttlecyclic as necessary to follow the turn until the slowly as necessary to maintain alignmenthelicopter comes to a complete stop. with the landing area and overcome yaw; do

not allow the helicopter to settle untilalignment is assured, then effect a

b. Left Pedal Locked Forward of touchdown. After ground contact, useNeutral: collective and throttle as necessary to

minimize forward speed and to maintain(1) Reduce power and maintain alignment. Move the cyclic as necessary to

engine rpm within the green arc. Normal turns follow the turn until the helicopter has come tocan be safely made under these conditions a complete stop.

3-10 Rev. 3

AA APPROVED 412 FLIGHT MANUAL Section 3

LJOSS .F PITCH-CHANGE CONTROLL1NKA 'E

I;: this type of failure the pitch-changermechanism is broken at some point and the tailrotor will assume a blade angle determined byt'e aerodynamic and counter-balance forces.

Corrective Action

The corrective action procedure is described inFIXED PITCH FAILURES, paragraph a.. b., orc.. above, depending on the yaw changeexperienced.

ZERO GROUND SPEED LANDINGS

1. If it is essential that the landing bemade at zero ground speed, the only change inthe technique described previously is that theflare will be more abrupt.

2. The flare should be executed moresteeply and will require a more rapid forwardcyclic input to land as near level as possible. A

more positive and abrupt use of collective alsowill be necessary. The flare should be executedas close to the ground as possible.

CAUTION

THE FLARE AND THE ABRUPT USEOF COLLECTIVE WILL CAUSE THENOSE TO ROTATE LEFT, BUT DONOT CORRECT WITH THROTTLE.ALTHOUGH APPLICATION OFTHROTTLE WILL RESULT IN ROTA-TION TO THE RIGHT, ADDITION OFPOWER IS A VERY STRONGRESPONSE MEASURE AND IS TOOSENSITIVE FOR THE PILOT TOMANAGE PROPERLY ATTHIS TIME.DO NOTADD POWER ATTHIS TIME.SLIGHT ROTATION AT TIME OFIMPACT AT ZERO GROUND SPEEDSHOULD NOT CAUSE ANY REALPROBLEM.

MALFUNCTION DRILLS

Table 3-2. Malfunction caution lights

PANELWORDING

FAULTCONDITION

CORRECTIVEACTION

OIL PRESSURE

(ENGINE 1)

(ENGINE 2)

LC GENERATOR

Engine oil pressurebelow limit.

Shut down #1 engine.

Shut down #2 engine. BATTERY BUS 2 switch -OFF. BATTERY BUS 1 switch - ON.

Failure of DCGENERATOR.

(#1) Reset #1 Generator - Turn off if reset not pos-sible.

Rev. 3 3-11


PANELWORDING

Table 3-2. Malfunction caution lights (Cont)

FAULT CORRECTIVECONDITION ACTION

Reset #2 Generator - Turn off if reset not pos-sible. BATTERY BUS 2 switch - OFF. BATTERYBUS 1 switch - ON.

(#2)

PART SEP OFF(1 and 2)

FUEL BOOST(1 and 2)

FUEL FILTER(1 and 2)

FUEL LOW(1 and 2)

GOV. MANUAL(ENGINES 1 and 2)

Separator bypassdoor closed. Ice, anddust protectionsystem inoperative.

Applicable pumppressure is low orpump failure hasoccurred.

Filter is partiallyblocked.

Fuel remaining forindicated tank isapproximately 10minutes at cruisepower.

Governor in manualmode.

Check engine RPM warning breaker and PARTSEP breaker in. Move PART SEP switch to OVRDON position. If PART SEP OFF light remains illumi-nated, correct malfunction prior to next flight.

If practical, reduce flight altitude to 5,000 feet orbelow for remainder of flight due to possible fuelstarvation of engine if other boost pump fails. Ifeither fuel boost pump fails, the crossfeed valve isopened by a pressure switch allowing pump tofurnish pressure to both engine fuel systems. Theabove sequence is possible with the crossfeed inNORMAL. If this automatic function is not desired,the crossfeed switch should be positioned toOVERRIDE CLOSE and interconnect switchOPEN. Correct prior to next flight.

Continue flight, consult maintenance manual andcorrect before next flight.

The fuel interconnect switch in the normal position(CLOSED) separates the two lower fuel cells.When either LOW FUEL warning light is illumi-nated, the interconnect switch should be moved tothe OPEN position. This will allow the fuel quantityin the lower tanks to equalize. In the event a fuelboost failure has occurred, or occurs after the fuelinterconnect is opened, all fuel in the lower tankswill be available to the engines, through eitherboost pump.

Engine temperature and RPM must be controlledwith twist grip.

CHIP(ENGINES 1 and 2)

Metal particles inengine oil.

Reduce power and shut down engine as soon aspractical to preclude engine damage.

FUEL VALVE(1 and 2)

Fuel valve notproperly seated.

Recycle switch, check prior to next flight.

3-12



PANELWORDING

FAULTCONDITION

CORRECTIVEACTION

FUEL XFEED

GEN OVHT(1 and 2)

Crossfeed valvenot seated.

Generator over-heating.

Recycle switch. Check prior to next flight.

GEN switch - OFF, check electrical system priorto next flight.

CAUTION PANEL Caution panelinoperative.

Monitor aircraft instruments. Correct malfunctionprior to next flight.

INVERTER #1

EXTERNAL POWER

Failure of #1inverter.

Check #1 AC voltmeter to determine that #2inverter has assumed #1 inverter load automat-ically.

External power still Check external power disconnected. Check doorconnected to aircraft. closed.

DOOR LOCK

BATTERY

CHIP C BOX

CHIP XMSN

Cabin aft door(s) or Check doors closed and locked.baggage compart-ment door not locked.

Both switches in Reset battery switch. If neither battery switch willsame position. reset, leave switches off.

Metal particles in Reduce power. Land as soon as practical.combining gearboxoil.

Metal particles in oil. Reduce power, land as soon as practical.

CHIP 42/90 BOX

INVERTER #2

HEATER AIR LINE

Metal particles in oil. Land as soon as practical.

Failure of #2inverter.

Check #2 AC voltmeter to determine that #1inveter has assumed #2 inverter load automat-ically.

Heater mixing valve Turn off heater immediately.malfunction.

3-13



PANELWORDING

FAULTCONDITION

CORRECTIVEACTION

AFCS One or both AFCSsystems off. Dis-placement betweenactuators of HP1 andHP2 AFCS system atleast 50 percenttravel.

Actuator position panel - Check. Determine ifHP1 or HP2 has malfunctioned. Turn off affectedsystem only. Continue flight with hands on.

0FORCE TRIM Force trim

inoperativeCheck FORCE TRIM switch - ON: Circuitbreaker-in. During IFR flight if system remainsinoperative, land as soon as practical. I

NOTE

Pilot may at his discretion, increase cyclic fric-tion to provide additional cyclic stabilization.

ELECTRICAL POWER FAILURE

DC - FAILURE TO PRODUCE POWER

switch to EMERG LOAD position. The follow-ing equipment will remain operational:

If either generator has not failed, but thecircuit is opened, reset the generator bymoving the generator switch to RESETposition momentarily, then back to ON.

I For single generator operation. nonessentialbuses may be restored by moving the non-essential bus switch from the NORMAL to theMANUAL position. Monitor to ensure loadswithin limits.

IIf both generators fail, both Nonessentialbuses will be automatically dropped to provideapproximately 30 minutes flight with batterypower.

To obtain approximately 90 minutes flightwith battery power, place EMERG LOAD

ENG OIL TEMP INDICATOR

COMB. GEARBOX OIL TEMP. INDICATOR

ITT INDICATOR

XMISION OIL TEMP INDICATOR

CAUTION SYSTEM

INSTRUMENT SECONDARY LIGHTS

PILOT INTERCOM PANEL

FIRE DETECTION SYSTEM

FIRE EXTINGUISHER SYSTEM

HP1

FORCE TRIM

COCKPIT LIGHT

I,

3-14 Rev. 3


PILOTS ATTITUDE INDICATOR

STANDBY ATTITUDE INDICATOR

FUEL CONTROL FAILURE TO THE HIGHSIDE. WITH HIGH TOTAL POWERDEMAND

RATE OF TURN SYSTEM

PITOT HEAT

STATIC PORT HEAT

1 NAV RADIO (10 MINUTE LIMIT)

1 COMM RADIO (10 MINUTES RECEIVE, 5MINUTES TRANSMIT)

SEARCHLIGHT (2 MINUTES)

AC - FAILURE TO PRODUCE POWER

When the helicopter is operated at a highpower demand (more than single enginemaximum power), and either fuel control failsto the high side, the failed engine will go to itsmaximum power, while the unfailed enginewill reduce power due to overspeeding of theNII. A correction should be made to reduce thefuel flow of the failed engine by rolling thetwist grip toward idle until NI decreases,which reduces the power from that engine.This allows the NIl to return to within thegoverned range. This engine can be taken toidle and switched to manual at the discretionof the pilot.

If either inverter fails to produce power, checkthe appropriate AC circuit breakers to be in.

ENGINE FUELMALFUNCTION

CONTROL

Malfunctions of either fuel control will beevidenced by abnormal change in RPM orPOWER. Due to the twin engine capability ofthis helicopter, analysis of a fuel controlmalfunction can be made by the resultant NilRPM after the failure has occurred and thepower demand of the rotor at the time offailure.

WARNING

RETARD THROTTLE OF ENGINEWITH MALFUNCTIONING FUELCONTROL TO IDLE BEFORESWITCHING TO MANUAL FUELMODE. FAILURE TO DO SO COULDRESULT IN ENGINE POWERSURGE, OVERSPEEDING, ANDDAMAGE TO DRIVE TRAIN COM-PONENTS BEFORE MANUALTHROTTLE CONTROL OF RPM ISATTAINED.

FUEL CONTROL FAILURE TO THE LOWSIDE, WITH LOW TOTAL POWERDEMAND

When the helicopter is operated at a low powerdemand (less than single engine maximumpower), and either fuel control fails to the lowside, the unfailed engine will assume the totalpower demand with a resultant NIlapproximately 2 percent lower than thatselected prior to the failure.

After the failed engine has been identified, thatengines twist grip should be rolled off to flightidle, and the fuel control switch moved fromautomatic to manual. Power can be adjustedon this engine by opening the twist grip tometer fuel manually. Care must be taken tomake small adjustments to this engine ascompressor stall may result. The unfailedengine will continue to be governed about theselected RPM. but when using high or lowpower, the RPM must be monitored to preventinadvertent overspeed.

FUEL CONTROL FAILURE TO THE HIGHSIDE, WITH LOW TOTAL POWERDEMAND

When the helicopter is operated at a low powerdemand (less than single engine maximum

3-15


power), and either fuel control fails to the high back both twist grips to maintain 97 to 100%side, the failed engine will go to its maximum RPM. Further adjustment of the collective andpower. The unfailed engine will reduce power the twist grips simultaneously will allow fullto zero and the resultant Nil being power at the pilots discretion.considerably higher than that selected prior tofailure. After the failed engine has been AFCS MALFUNCTIONSidentified, the engines twist grip should berolled toward idle to reduce the fuel flow and INOPERATIVE ATTITUDE GYROpower to give the desired Nil reading. PILOTAdjustment of the collective and the twist gripwill allow full power to be utilized at the pilots AFCS light will illuminate. HP1 system willdiscretion. become inoperative.

The failed engine can be rolled to idle and INOPERATIVE ATTITUDE GYRO -switched to manual if desired by the pilot. COPILOT

FUEL CONTROL FAILURE TO THE LOW AFCS light will illuminate. HP2 system willSIDE, WITH HIGH TOTAL POWER become inoperative. If HP1 is functioningDEMAND correctly, no AFCS functions will be lost.

When the helicopter is operated at a high DC GEN NO. 1 OR NO. 2 FAILUREpower demand (more than single enginemaximum power), and either fuel control fails HP1 and HP2 AFCS functions are notto the low side, the unfailed engine will affected.attempt to assume the total power demand bygoing to its maximum power. The Nil will AC INV I FAILUREdecrease to a level dependent upon thedifference between the total power demand HP1 drops off line but may be recalled byand power available on the unfailed engine. depressing HP1 switch.The collective should be reduced sufficientlyto return the Nil to the operating range. AC INV 2 FAILURE

Further reductions of collective will show the HP2 drops off line but may be recalled byNil to remain within the operating limits as depressing HP2 switch.power is reduced, indicating the poweredengine is operating normally, and that the low AFCS WILL NOT ENGAGEengine has had a fuel control failure to the lowside. The engine with the failed fuel control INVERTERS - Check ON.can then be rolled to flight idle and switched tomanual at the pilots discretion. AFCS circuit breakers - Check in.

Nil ACTUATOR FAILURE TO FULL ATTITUDE GYROS - Wait until gyro flag onINCREASE attitude indicator has retracted.

Rotor and Nil RPM will increase to AFCS WILL NOT HOLD ATTITUDEapproximately 101%. If this failure occursduring takeoff or landing, no immediate FORCE TRIM switch - Check ON.corrective action is necessary to completeeither maneuver. As soon as practical, roll SAS/ATT switch - Check in ATT position.

3-16


HYDRAULIC FAILURE - SYSTEM NO. 1 ENGINE NO. 1

Yaw SAS automatically disengages. Pitch and 1. #1 Twist Grip - Closed.roll SAS/ATT modes will operate normally.

2. #1 Boost Pump - ON.HYDRAULIC FAILURE - SYSTEM NO. 2

HYDRAULIC FAILURE -SYSTEM 3. Fuel Crossfeed Switch - NORMAL.0D Pitch, roll, and yaw ATT/SAS modes willoperate normally. 4. #1 Fuel Switch - ON.

5. #1 Fuel Control Switch - MANUAL.REENGAGING AFCS AFTERDISENGAGE 6. Battery Bus 2 Switch - OFF.

Circuit breakers - IN. If a breaker has popped 7. Battey Bus 1 Switch - ON.and pops again after being reset, do notattempt further resetting. 8. Inverter Switches - ON.

HP1 or HP2 switch - ON. 9. #1 Starter - ENGAGE.

If there is any unusual control input, disengage After 12 percent NI is reached and when anyAFCS. engine oil pressure is seen, slowly open twist

grip until a rise is seen in ITT, indicating a light-off. Do not open twist grip farther until the NI

TOTAL SAS FAILURE and ITT is stabilized. Continue to open twistgrip slowly to complete start cycle. Turn

A flight may be dispatched with two pilots starter off after 55 percent NI is reached.during calm VMC day conditions to allow the Adjust engine to desired power level. Carehelicopter to fly to a maintenance facility must be taken to make small adjustment withprovided no passengers are aboard the twist grip as compressor stall may result.helicopter.

10. #1 Generator - ON.ENGINE RESTART

ENGINE RESTART 11. Battery Bus 1 Switch - OFF.The conditions which would warrant anattempt to restart the engine would probably 12. Battery Bus 2 Switch - ON.be a flameout. caused by a malfunction of theautomatic mode of the fuel control unit. The ENGINE NO. 2decision to attempt an engine restart duringflight is the pilots responsibility. If an engine 1. #2 Twist Grip - Closed.restart is to be made, proceed as follows:

2. #2 Boost Pump - ON.

CAUTION 3. Fuel Crossfeed Switch - NORMAL.

4. #2 Fuel Switch - ON.WHEN RESTARTING ENGINE INMANUAL FUEL CONTROL MODE, 5. #2 FUEL CONTROL SWITCH -CAREFULLY MONITOR ITT. MANUAL.

3-17


6. Battery Bus 1 Switch - OFF.

7. Battery Bus 2 Switch - ON.

8. Inverter Switches - ON.

9. #2 Starter - ENGAGE.

After 12 percent NI is reached and when anyengine oil pressure is seen, slowly open twistgrip until a rise is seen in ITT, indicating a light-off. Do not open twist grip farther until the NIand ITT is stabilized. Continue to open twistgrip slowly to complete start cycle. Turnstarter off after 55 percent NI is reached.Adjust engine to desired power level. Caremust be taken to make small adjustment withtwist grip as'compressor stall may result.

10. #2 Generator - ON.

HYDRAULIC MALFUNCTION

WARNING

THE HELICOPTER IS NOT CON-TROLLABLE WITH BOTH HYDRALICBOOST SYSTEMS INOPERATIVE.

HEATER MALFUNCTION

A malfunction in the bleed air heater unitcontrols will cause the heater to beinoperative.

Heater SELECTOR switch - OFF.

STICK CENTERING INDICATORSYSTEM FAILURE.

Indication:

This helicopter has two separate hydraulicboost systems (1 and 2). Both systems supplypower to each flight control system for themain rotor, with the tail rotor control systempowered by System 1 only.

If either the system pressure or temperaturegoes above the red line, the affected systemshould be turned off. Land as soon as possible.

CYC CTR caution lights fail to illuminatewhen cyclic is displaced 1.5 inches or morefrom centered position while rotor RPMwarning light is illuminated.

Procedure:

Maintain flat pitch NR between 97 to 100%for ground operations until shutdown.

3-18 Rev. 3


TABLE OF CONTENTS

PageNumberParagraph

Introduction .............................................................................Power Assurance Check Procedures .....................................................Height - Velocity .......................................................................One Engine Inoperative Cruise Speed ....... ...........................Flight Speed Over Water .................................................................Hover Ceiling In-Ground-Effect ..........................................................Hover Ceiling Out-of-Ground-Effect ......................................................Takeoff Distance Over 50 Foot Obstacle .................................................Landing Distance Over 50 Foot Obstacle .................................................Twin Engine Rate of Climb ..............................................................Single Engine Rate of Climb .............................................................Airspeed Calibration .....................................................................

4-34-34-34-34-34-3

4-134-134-134-134-134-13

LIST OF FIGURES

FigureNumber

PageNumberTitle

4-14-24-34-44-54-64-74-84-94-104-11

Power Assurance ..... .......................................................Height-Velocity Chart........................................................Density Altitude .............................................................Critical Wind Azimuth Chart .................................................Hover Ceiling In-Ground-Effect ..............................................Hover Ceiling Out-Of-Ground Effect .........................................Takeoff Distance Over 50 Foot Obstacle .....................................Landing Distance Over 50 Foot Obstacle .....................................Twin Engine Rate of Climb ..................................................Single Engine Rate of Climb ................................................Airspeed Calibration .........................................................

4-54-74-84-9

4-104-144-204-214-224-464-58

4-1/4-2

INTRODUCTION

The Model 412 performance data arecontained in this section. The data listed on thecharts were derived from actual flight testsand are intended to provide information to beused in conducting flight operations.

ground which should be avoided duringnormal operations. A safe landing cannot beassured in the event a single engine failureoccurs in the AVOID area of the chart. Thechart is only valid for smooth, level, firmsurfaces.

ONE ENGINE INOPERATIVEPOWER ASSURANCE CHECK CRUISE SPEEDPROCEDURES

The Power Assurance Check Chart indicatesthe minimum specification power and theresulting maximum ITT and Nll RPM for thePT6T-3B engine with installation losses.

The Power Assurance Check Chart assumesproper rigging of the engine controls andproper indications of pressure altitude andambient air temperature.

Perform the power assurance check at leastonce a day prior to operations. Further checksshould be made if unusual operatingconditions or indications arise. If engineperformance does not meet that shown in theengine power assurance chart, the perfor-mance information presented in Sections 1and 4 may not be attainable. Refer to enginemanufacturers manual for the steps to betaken to determine the cause of the enginepower loss.

Perform power assurance check as detailed onPower Assurance Check Chart.

HEIGHT - VELOCITY

The Height-Velocity Chart showscombinations of airspeed and height above the

Recommended One Engine Inoperative CruiseSpeed is 100 knots true airspeed.

FLIGHT SPEED OVER WATER

The true airspeed to be assumed for compliancewith the regulations governing flight over wateris 125 knots.

HOVER CEILING IN-GROUND-EFFECT

The Hover Ceiling In-Ground-Effect Chartsprovide the ceiling for hovering IGE at allpressure altitude/outside air temperature/gross weight combinations with heater on andoff.

Adequate directional control is available at thegross weights allowed by the Hover Ceiling In-Ground-Effect Charts in relative winds up to20 knots from any direction. Better directionalcontrol will be realized by avoiding relativewinds in the critical azimuths. Refer to CriticalWind Azimuth Chart. Downwind takeoff andlandings are not recommended.

Rev. 1 4-3/4-4


MAXIMUM

600

MODEL 412POWER ASSURANCE CHECK

PT6T-3B ENGINE

HEATER/ECU- OFF.

THROTTLES:ENGINE BEING CHECKED - FULL OPEN.OTHER ENGINE - FLIGHT IDLE.

Nil RPM - 97%.

COLLECTIVE PITCH - INCREASE UNTIL LIGHTON SKIDS OR HOVERING AND STABILIZEPOWER ONE MINUTE

RECORD:ENGINE TORQUE. ITT, AND NI RPM.

ENTER CHART AT INDICATED ENGINE TORQUE,MOVE UP TO INTERSECTPRESSURE ALTITUDE,PROCEED TO THE RIGHT TO INTERSECTOUTSIDE AIR TEMPERATURE. THEN MOVE UPTO READ VALUES FOR MAXIMUMALLOWABLE ITT AND NI RPM.

REPEAT CHECK USING OTHER ENGINE.

IF INDICATED ITT EXCEEDS MAX. ALLOWABLE,REPEAT CHECK, STABILIZING POWER FOURMINUTES.

IF ITT OR NI RPM AGAIN EXCEEDS MAX.ALLOWABLE, CAUSE SHOULD BEDETERMINED PRIOR TO FURTHER FLIGHT.

ALLOWABLE ITT - °C MAXIMUM ALLOWABLE NI RPM - PERCENT

I

40 50 60 70 80ENGINE TORQUE - PERCENT (INDICATED) 412099-1B

Figure 4-1. Power assurance chart

4-5/4-6

(11.01-

(10.0)-

(9.01 -

18.0)-


DENSITY ALTITUDE CHART

1 80EXAMPLE IF AMBIENT TEMP IS -15°CAND PRESSURE ALT IS 6.000 FEET. THE

1'76 DENSITY ALT IS 4.000 FEET AND IS 1 06

1

-1 721 70

-- 1 681 66

-1 641 62

-1 601 58

-1 56- 1 54-1 52

1 50-1 48

1 46-1 44

1 42-1 40

- 1 38- 1 36

1 34

-1 321 30

-1 281 26

1 241 22

-1 201 16

-1 1611 14

-1 12

1 10

-1 08(2.0Z -

(1.0)-

(0.5s-

(-0.51-

(-1.01-

1 06

- 1 04

412900-38

Figure 4-3. Density altitude


LONGITUDINALCYCLIC

CRITICALWINDAZIMUTH

(AFT CYCLIC MAYBE LIMITED) 105

412900-62B

Figure 4-4. Critical wind azimuth chart

4-9


HOVER CEILING

IN GROUND EFFECT

POWER: SEE NOTE BELOW SKID HEIGHT 4 FEET 1.3 m.)ENGINE RPM 100% HEATER ON OR OFFGENERATOR 150 AMPS (EA.) 0° TO 52°C

NOTE.

Figure 4-5. Hover ceiling in-ground-effect chart (Sheet 1 of 3)


HOVER CEILINGIN GROUND EFFECT

POWER: SEE NOTE BELOWENGINE RPM 100%GENERATOR 150 AMPS (EA.)

SKID HEIGHT 4 FEET (1.3 m.)HEATER ON OR OFF

-30 ° TO O°C

NOTE:THESE IGE HOVER CEILINGSARE BASED ON DENSITY ALT.LIMITS FOR TAKE-OFF ANDLANDING. THIS HELICOPTERCAN BE HOVERED IGE AT THEINDICATED GROSS WEIGHTSWITH LESS THAN TAKE-OFFPOWER.

GROSSLIMIT

N

11.6(5.26)-

I-30-20-10 0

OAT - °C8 9 10 11 12GROSS WEIGHT - LBS x 1000

I I I I I I(3.5) (4.0) (4.5) (5.0) (5.25)

412900-23-2 A


4-11

MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 160 AMPS (EA.)

14,000 FT.(4267 m.) DEN. ALT. LIMIT

MAX OAT HEATER ON (21°C)

0 10 20 30 40 50 60 8 9 10 11 12OAT - °C GROSS WEIGHT - LBS X 1000

(3.5) 14.0) (4.5) (5.0) (525)

GROSS WEIGHT - (kg) X 1000


HOVER CEILING

IN GROUND EFFECT

MAX

SKID HEIGHT 4 FEET (1.3 m.)HEATER ON OR OFF

0°

TO 52°C

OAT

412900-23-3 A


4-12


HOVER CEILING OUT-OF-GROUND-EFFECT

The Hover Ceiling Out-Of-Ground-EffectCharts provide ceiling for hovering out-of-ground effect at all density altitude/outside airtemperature/gross weight conditions withheater on and off.

TAKEOFF DISTANCE OVER 50FOOT OBSTACLE

The Takeoff Distance Over 50 Foot ObstacleCharts provide takeoff distances required toclear a 50 foot obstacle at all outside airtemperatures/pressure altitudes/grossweights, given an indicated airspeed of 45knots and a skid height of 4 feet (1.2 meters).Climb out speed is 45 knots.

LANDING DISTANCE OVER 50FOOT OBSTACLE

The Single Engine Landing Distance Over 50Foot Obstacle Chart provides the landingdistance required over a fifty foot obstacle for

all outside air temperatures/pressurealtitudes/gross weights given an airspeed of45 knots.

TWIN ENGINE RATE OF CLIMB

The Twin Engine Rate of Climb Chartsprovides the rate of climb that may be obtainedat all outside air temperatures/pressurealtitudes/gross weight combinations withheater on or off and at maximum continuouspower and 65 knots calibrated air speed.

SINGLE ENGINE RATE OF CLIMB

The Single Engine Rate of Climb Chartsprovide the rate of climb that may be obtainedat all outside air temperatures/pressurealtitudes/gross weight combinations withheater on or off and at maximum continuouspower.

AIRSPEED CALIBRATION

The Airspeed Calibration chart providescalibrated airspeed for all indicated airspeedsin various flight regimes.

4-13

HOVER CEILING

OUT-OF-GROUND-EFFECT

TAKEOFF POWER SKID HEIGHT 60 FT. (18.3 m.)ENGINE RPM 100% HEATER ON OR OFFGENERATOR 150 AMPS (EA.) 0° TO 52°C

14,000 FT.

412 FLIGHT MANUAL CAA APPROVED

OAT

8 9 10 11 12GROSS WEIGHT - LBS x 1000

I I I I I

(3.5) (4.0) (4.5) (6.0) (5.25)GROSS WEIGHT - (kg) x 1000

0 10 20 30 40 50 60

OAT - °C

412900-24-1B

Figure 4-6. Hover ceiling out-of-ground-effect chart (Sheet 1 of 6)

4-14

0

0

CAA APPROVED 412 FLIGHT MANUAL

HOVER CEILINGOUT-OF-GROUND-EFFECT

TAKEOFF POWER SKID HEIGHT 60 FT. (18.3 m.)ENGINE RPM 100% HEATER ON OR OFFGENERATOR 160 AMPS (EA.) -30 °

TO 0°C

Section 4

LIMIT

-30-20-10 0 8 9 10 11 12

OAT - °C GROSS WEIGHT - LBS x 1000I I I I I

(3.5) (4.0) (4.5) (5.0)(5.25)

GROSS WEIGHT - (kg) x 1000

412900-24-2B


4-15


14,000 FT.

- (4267 m.) DEN. ALT. LIMIT


HOVER CEILING


SKID HEIGHT 60 FT. (18.3 m.)

HEATER OFF0

°TO 62°C

0TORQUELIMIT

8 9 10 11GROSS WEIGHT - LBS x 1000

12

OAT - °CI I I I I I I I

(3.5) (4.0) (4.6) (6.0)(6.26)GROSS WEIGHT - (kg) x 1000 412900-24-3B


4-16


HOVER CEILING



SKID HEIGHT 60 FT. (18.3 m.)HEATER OFF-30

° TO 0°C


4-17




SKID HEIGHT 60 FT. (18.3 m.)HEATER ON0

°TO 20°C

TORQUE__LIMIT

8 9 10 11 12GROSS WEIGHT - LBS x 1000

(3.5) (4.0) (4.5) (5.0) (5.25)GROSS WEIGHT - (kg) x 1000

412900-24-5B

0 10 20

OAT - °C


CAA APPROV'ED 412 FLIGHT MANUAL


MAXIMUM CONTINUOUS POWER SKID HEIGHT 60 FT. (18.3 m.)ENGINE RPM 100% HEATER ONGENERATOR 150 AMPS (EA.) -30° TO O°C

14,000 FT.- (4267 m.) DEN. ALT. LIMIT --

Section 4

LIMIT

-30-20-10 0 8 9 10 11 12

OAT - °C GROSS WEIGHT - LBS x 1000

(3.5) (4.0) (4.5) (5.0) (5.25)GROSS WEIGHT - (kg) x 1000

412900-24-6B


4-19

TAKE-OFF DISTANCEOVER 50 FOOT OBSTACLE

HOVER POWER t 15% TORQUE INITIATED FROM 4 FT. (1.3 m.) SKID HEIGHTENGINE RPM 100% VTOCS = 45 KIASGENERATOR 150 AMPS (EA.) HEATER ON OR OFF

r-14,000 FT. (4267 m.) DEN. ALT. LIMIT -

MAXIMUI


0

0

-60-40-20 0 20 40 60 400 600 800 1000 1200 1400 w

OAT - °C (100) (110) (200) (260) (30) (350) (400)TAKE-OFF DISTANCE - FT.(m.)

412100-13A

Figure 4-7. Takeoff distance over 50 foot obstacle chart

4-20


SINGLE ENGINE LANDING DISTANCEOVER 50 FT. (16 m) OBSTACLE

MAXIMUM CONTINGENCY 45 KIASPOWER AS REQUIRED RATE OF DESCENT 500 FT/M (2.64 m/s)ENGINE RPM 97% HARD SURFACED RUNWAYGENERATOR 160 AMPS.(INOPERATIVE ENGINE SECURED)

-- 14,000 FT. (4267 m.) DEN. ALT. LIMIT--

-40 -20 0 20 40 60 200 400 600 800 1000 1200

Figure 4-8. Landing distance over 50 foot obstacle chart

4-21

20.000

18,000

16,000

14,000


TWIN ENGINE RATE OF CLIMBWITH ALL DOORS OPEN RATE OF

CLIMB WILL DECREASE 200 FT./MIN.

TAKE-OFF POWERENGINE RPM 100%GENERATOR 150 AMPS (EA.)

65 KCASHEATER OFF

UJLU

LUa

Figure 4-9. Twin engine rate of climb chart (Sheet 1 of 24)

4-22



TAKE-OFF POWERENGINE RPM 100% 65 KCASGENERATOR 160 AMPS (EA.) HEATER OFF

GROSS WEIGHT 8000 LBS (3629 kg)20.000 -6000

18,000 -5500

Figure 4-S. Twin engine rate of climb chart (Sheet 2 of 24)


4-23





GROSS WEIGHT 9000 LBS (4082 kg)20,000 -6000- 6000

18,000 - 5500

16,000 - 5000

8,000 OAT \ 0


4-24

20,000

18.000

16.000

14.000





GROSS WEIGHT 10.000 LBS (4536 kg)

65 KCASHEATER OFF


4-26

20.000

18,000

16.000 \

\

14.000

w 12,000Lu

I

0

I-

GENERATOR 150 AMPS (EA.)GROSS WEIGHT 11.000 LBS (4990 kg)

66 KCASHEATER OFF

-6000

-5500

- 6000

-4500


4-26

CAA APPROVED 412 FLIGHT MANUAL Sectio




GROSS WEIGHT 11.600 LBS (5262 kg)20000 -6000-6000


4-27

I-



CLIMB WILL DECREASE 200 FT./MIN.MAXIMUM CONTINUOUS POWERENGINE RPM 100%GENERATOR 150 AMPS (EA.)

GROSS WEIGHT 7000 LBS (3175 kg)

412100-10-7A


4-28

20,000






\200 C

65 KCASHEATER OFF

LUU.

UJ

a

uJ4LU

18,000

16.000

14,000

12.000

10,000

8.000

6,000

4.000

2,000

-6000

-5500

-5000

-4500

-4000 w2

-3500 -a

- 3000 5-1500 4

LU

412100-10-8A


4-29



MAXIMUM CONTINUOUS POWERENGINE RPM 100% 65 KCASGENERATOR 150 AMPS (EA.) HEATER OFF


OAT _____


20.000


20.000

18.000

16.000





GROSS WEIGHT 10,000 LBS (4536 kg)

65 KCASHEATER OFF

I-

UL

IUJ


4-31

Section 4

20.000

18.000 -

16,000 -

14.000

12,000 -

412 FLIGHT MANUAL CAA APPROVED





65 KCASHEATER OFF

LU

I-uJ

4


4-32

iALU

u.IUJ

rE






65 KCASHEATER OFF

20,000

18.000

16.000

14.000

12.000

10.000

8.000

6.000

4.000

2,000

-6000

- 5500

-5000

-4500

iu


4-33

20.000

18.000

16,000

14,000




TAKE-OFF POWERENGINE RPM 100% 65 KCASGENERATOR 150 AMPS (EA.) HEATER ON


I-

UJ

Qaw

u

12.000

10.000

8,000

6.000

-6000

-5500

-5000

-4500


4-34

20.000

18.000

16.000

14.000

Section 4




GROSS WEIGHT ROnn LBS 13629 kol

66 KCASHEATER ON


4-35




4-36

20.000

18.000

16,000

14.000




uJwuJ

tu


4-37

I-w

tU.

UJ

0.





GROSS WEIGHT 11,000 LBS (4990 kg)

OAT

66 KCASHEATER ON

-6000

-5500

-5000

-4500

LU

-4000 w2I

- 3500 w


4-38




TAKE-OFF POWERENGINE RPM 100% 65 KCASGENERATOR 150 AMPS (EA.) HEATER ON

GROSS WEIGHT 11.600 LBS (5262 kg)20.000 -6

-6000

18.000 -5500

OAT

I. -1500

4.000-1000

2.000-500

00 200 400 600 800 1000 1200 1400 1600

RATE OF CLIMB - FEET/MINUTE

(0) (1.0) (2.0) (3.0) (4.0) (5.0) (6.0) (7.0) (8.0)RATE OF CLIMB - (METERS/SECOND)

412100-10-18A


4-39




GROSS WEIGHT 7000 LBS (3175 kg)20.000

18.000

16.000

14,000


I

I

65 KCASHEATER ON

s 12.000UJ

Iu


4-40

20.000

18,000

16.000

14.000

i-UJLu

I

ur

65 KCASHEATER ON

-6000

-5500

-5000

-4500


4-41

Section 4

20.001

18.001

16,001

14,004

12.001LUu.

L 10.001

^ 8,00(

412100-10-21A


4-42




MAXIMUM CONTINUOUS POWERENGINE RPM 100% 65 KCASGENERATOR 150 AMPS (EA.) HEATER ON

GROSS WEIGHT 10,000 LBS (4536 kg)20.000 6000


4-43




MAXIMUM CONTINUOUS POWERENGINE RPM 100% 66 KCASGENERATOR 150 AMPS (EA.) HEATER ON

GROSS WEIGHT 11.000 LBS (4990 kg) -620.000 - 6000


4-44

LU

IUJU.

UJ

onUJ


4-45

MAXENGIGENI

20.000

18,000

16,000

14,000

I-Lu 12,000

412100-12-7A

Figure 4-10. Single engine rate of climb (Sheet 1 of 12)

4-46

20,000



SINGLE ENGINE RATE OF CLIMBWITH ALL DOORS OPEN RATE OF


MAXIMUM CONTINUOUS POWER 65 KCASENGINE RPM 97% HEATER OFFGENERATOR 150 AMPS (INOPERATIVE ENGINE SECURED)


6000

550055OO05500

4000

30001500

10005001500

1000



MAXIMUM CONTINUOUS POWER 65 KCASENGINE RPM 97% HEATER OFFGENERATOR 150 AMPS (INOPERATIVE ENGINE SECURED)



20,000

0


4-48


CLIMB WILL DECREASE 200 FT./MIN.MAXIMUM CONTINUOUS POWER 66 KCASENGINE RPM 97% HEATER OFFGENERATOR 150 AMPS (INOPERATIVE ENGINE SECURED)

GROSS WEIGHT 10,000 LBS (4536 kg)20,000 -6000

TWIN ENGINE OAT



4-49



MAXIMUM CONTINUOUS POWER 65 KCASENGINE RPM 97% HEATER OFFGENERATOR 150 AMPS ,(INOPERATIVE ENGINE SECURED)

GROSS WEIGHT 11.000 LBS (4990 kg)20,000 -6000

- 550018.000

TWIN ENGINE OAT - 500016.000 M.C.P. ABSOLUTE - \\ \\ -20°C

CEILING -30°C-4500

14.000 \



4-60



MAXIMUM CONTINUOUS POWER 65 KCASENGINE RPM 97% HEATER OFFGENERATOR 150 AMPS JINOPERATIVE ENGINE SECURED)


18,000 -5500

TWIN ENGINE \\5



4-51


CLIMB WILL DECREASE 200 FT./MIN.INTERMEDIATE CONTINGENCY POWER 65 KCASENGINE RPM 97% HEATER OFFGENERATOR 150 AMPS (INOPERATIVE ENGINE SECURED)

GROSS WEIGHT 7000 LBS (3175 kg)20,000

14.000

12.000

10,000

000

CAA APPROVED

-6000

-5500

-5000

-4500

I- 4000

-3500

- 3000

-2500

- 2000

-1500

-1000

-500

0)

RATE OF CLIMB - (METERS/SECOND)

412100-12-1B


4-52



INTERMEDIATE CONTINGENCY POWER 65 KCASENGINE RPM 97% HEATER OFFGENERATOR 150 AMPS (INOPERATIVE ENGINE SECURED)



4-53






4-64


CLIMB WILL DECREASE 200 FT./MIN.INTERMEDIATE CONTINGENCY POWER 65 KCASENGINE RPM 97% HEATER OFFGENERATOR 150 AMPS (INOPERATIVE ENGINE SECURED)

GROSS WEIGHT 10.000 LBS (4536 kg)20.000 \ -6000

18,'20°C - 5500

412100-12-4B



4-55




GROSS WEIGHT 11.000 LBS (4990 kg)20.000 - 6000

18.000 -5500OAT

16,000 TWIN ENGINE - 0C

M.C.P. ABSOLUTE - 4500CEILING\



4-56




GROSS WEIGHT 11.600 LBS (5262 kg)20.000

- 6000

18.000 -5500

OAT



4-57


PILOT & COPILOT AIRSPEEDSYSTEM CALIBRATION

CLIMB, LEVEL FLIGHT. AUTOROTATION

SKID GEAR KIAS - ERROR = KCAS

160 NOTE. AIRSPEED INSTRUMENT PART NO.12-075-009-105 INSTALLED.

140LEVEL FLIGHT

120

0 20 40 60 80 100 120 140 160

INDICATED AIRSPEED - KNOTS412100-14

Figure 4-11. Airspeed calibration

4-58

412 FLIGHT MANUAL Section 5

A_TABLE OF CONTENTS

PageNumberParagraph

Pilot Preflight Check.....................................................................Exterior Check ..........................................................................Interior Check ...........................................................................Prestart Check ..........................................................................Engine Starting ........................................................................Engine Runup and System Check .......................................................Before Takeoff ..........................................................................Power Assurance Check .................................................................Takeoff .................................................................................In-Flight Operation ......................................................................Descent and Landing ...................................................................After Landing............................................................................Engine Shutdown .......................................................................After Exiting Helicopter .................................................................

5-35-35-55-55-75-85-95-95-9

5-105-105-105-105-10

5-1/5-2

CAA APPROVED 412 FLIGHT MANUAL Section

Section 2 of this manual contains theapproved procedures for the operationof this helicopter. The following pilotschecklist is an abbreviated form of thenormal procedures and is provided forthe convenience of the operator.

PILOT PREFLIGHT CHECK

A preflight check by the pilot is required.

Weight and CG - Compute.

Publications - Check.

BAT switch - BUS 1 and BUS 2.

Fuel Sump Drain Buttons (left and right) -Depress.

Boost Pump Switches - ON.

Fuel Switches - ON.

Fuel Filter (left and right) - Drain samples.

Fuel Switches - OFF.

Boost Pump Switches - OFF.

BAT Switches - OFF.

Portable Fire Extinguishers - Installed andsecured.

EXTERIOR CHECK

1. CABIN NOSE AREA

Cabin nose area - Condition - all glassclean.

Remote hydraulic filter bypass indictor-Check green.

Static port(s) (left and right) -Unobstructed.

Pitot tube(s) - Cover(s) removed;unobstructed.


Cabin nose ventilators - Unobstructed.

Battery vent and drain tubes -Unobstructed.

Searchlight and landing light - Stowed.

Antenna - Condition and security.


2. FUSELAGE - CABIN LEFT SIDE

Copilot door - Condition and operation;glass clean. Check security of emer-gency release handles.


5-3



No. 2 Hydraulic level - Check.


No. 1 engine air intake - Coverremoved; unobstructed.

3. FUSELAGE - AFT LEFT SIDE

Drain lines - Clean and unobstructed.



Nil governor spring - Check condition.


Combining gearbox filter - Checkbypass indicator retracted.



Engine exhaust ejector tubes - Coversremoved; unobstructed.

4. AFT FUSELAGE


Tail rotor driveshaft covers - Securedfor flight.

Elevator - Condition and security.Check for spring condition by movingelevator toward the leading edge downposition.

CAUTION

DO NOT BEND TRAILING EDGETAB.

Tail rotor 90 ° gearbox - Verify actualpresence of oil in sight gage. Visuallycheck oil level, filler cap, and chipdetector plugs.

Tail rotor - Condition and freemovement on flapping axis.

Tail skid - Condition and security.

Tail rotor 42 ° gearbox - Verify actualpresence of oil in sight gage. Visuallycheck oil level, filler cap, and chipdetector plug.

Elevator - Condition and security.


Baggage compartment - Cargosecured; door secured.


5. FUSELAGE - AFT RIGHT SIDE


Combining gearbox oil level - Verifyactual presence of oil in sight gage.Visually check oil level.




Fuel filler - Visually check quantity;secure cap.

0

5-4


6. FUSELAGE - CABIN RIGHT SIDE

Transmission oil level - Verify actualpresence of oil in sight gage. Visuallycheck oil level.


No. 2 engine air intake - Coverremoved; unobstructed.

No. 1 Hydraulic level - Check.

Landing gear Condition: handlingwheels removed.


Pilot door - Condition and operation;glass clean. Check security ofemergency release handles.

7. CABIN TOPSwashplate, support assembly, andcollective lever - Check condition.

Hub and sleeve assembly - Checkcondition.

Main rotor pitch links - Security andcondition.

Main rotor hub - Check generalcondition.

Pitch horns - Security and condition.

Elastomeric bearings, lead-lag dampers- Check general condition.

Blade retention bolts - Security andproper latching.

Droop Restraints Security andcondition.

Rotor blades - Visually check conditionand cleanliness.

Main driveshaft and coupling - Checkcondition and security where visible;coupling for grease leakage andappearance of overheating.

Transmission oil filler cap - Secured.

No. 1 and No. 2 hydraulic fluid reservoirs- Visually check fluid levels; capssecured.

Antenna(s) - Condition and security.

Combining gearbox oil filler cap -Secured.

Anticollision light - Condition andsecurity.

No. 1 and No. 2 engine air intakes -Unobstructed; check particle separatordoors closed.

Engine and transmission cowling -Secured.

Fresh air inlet screen - Unobstructed.

Rotor brake reservoir cap - Security.

INTERIOR CHECK

Cabin interior - Cleanliness and security ofequipment.

Hand held fire extinguishers - Installed andsecured.

Passenger seats - Check for belts.

Cargo (if applicable) - Check security.

Protective breathing equipment (if installed) -Condition and security.

PRESTART CHECK

Passenger doors - Secured.

Seat and pedals - Adjust.

Rev. 3 5-5


Seat belt and shoulder harness - Fasten and Wiper select (both) - OFF.adjust; check inertia reel lock.

Cargo release - OFF.Flight controls - Position for start; friction asdesired. Vent blower - OFF.

Collective control head switches - OFF. Aft outlet - OFF.

Transmission chip detector indicators - Heater switch - OFF.Check; reset if required.

Circuit breakers - In.Lower pedestal circuit breakers - In.

All lights - OFF.Radios - OFF.

Master caution switch - Spring loaded toCompass slaving switch(es) - MAG. NORMAL.

Fuel interconnect - NORM. Emergency load switch - NORMAL.

Boost pumps - OFF. Non-essential bus switch - NORMAL.

Fuel crossfeed - NORM. Inverters - OFF.

Fuel switches - OFF. Generators - OFF.

Particle separators - NORM.

Governors - AUTO.External power - Connect (as desired).

Hydraulic switches - ON. Check for 27 ± 1 Vdc.

Step switch - OFF.

Rotor RPM audio - Spring loaded to AUDIO. Battery switches (BUS 1 and BUS 2) - ON.

Force trim - ON. Master caution switch (overhead) - TEST.

Instruments - Static check. Rotor brake lights - Test.

Altimeter - Set. Engine fire warning light - Test.

Clock - Set. Baggage fire warning light - Test.

Fire extinguisher switch - OFF. All press to test lights - Test.

Fire pull handles - In (forward). Caution panel lights - Test and reset.

Aft dome lights - OFF. Inverters 1 and 2- ON; check 104- 122 Vac.

Pitot heater - OFF. Fuel quantity gage - Test.

5-6


ENGINE STARTING Gas producer Check 61 + 1% NI RPM atflight idle.

Twist grips - Full closed; friction as desired.Engine, transmission, and gearbox oil

RPM INCR-DECR switch - DECR for 8 pressures - Check.seconds.

NO.1 ENGINE No. 1 PART SEP OFF light - Extinguished.NO. 1 ENGINE START

No. 1 twist grip- Increase to 85% NII M;No. 1 boost pump - ON. friction as desired.

No. 1 fuel switch - ON. Check pressure. If above start was completed usingexternal power, proceed to No. 2 engine

Rotor - Clear. start. If battery was used, proceed asfollows:

No. 1 engine starter - Engage.

NI RPM check 71% minimum.No. 1 engine oil pressure - Indicating.

No. 1 generator - ON.No. 1 twist grip - Open to flight idle at 12%NI RPM. N1~ RPM No. 1 ammeter - Check at or below 150

amps.ITT - Monitor. Maximum during start is10900 C, not to exceed two seconds above NO. 2 ENGINE START960°C.

No. 2 boost pump - ON.Collective pitch - Lower as rotor RPMincreases.

No. 2 fuel switch - ON; check pressure.

F ~CAUTION No. 2 engine starter - ENGAGE.

No. 2 engine oil pressure - Indicating.

IF STICK CENTERING INDICA- No. 2 twist grip - Open to flight idle at 12%TOR SYSTEM IS INOPERATIVE. NI RPM.NR FOR GROUND OPERATIONSHALL BE 97% OR ABOVE. ITT - Monitor. Observe ITT limitations.

ON SIDE SLOPES GREATER No. 2 engine starter - Disengage at 55% NITHAN FIVE DEGREES. DISRE- RPM.0) GARD CYC CTR CAUTIONLIGHTS AND POSITION CYCLIC Engine tachometer and torquemeter -AS REQUIRED. Verify engagement of second engine.

Cyclic - Position as necessary to extinguish Engine oil pressures - Check.CYC CTR caution lights.

No. 2 PART SEP OFF light - Extinguished.No. 1 engine starter - Disengage at 55% NIRPM. NI RPM - Check 71%

Rev. 3 5-7


If external power was used -Disconnect.Generator 1 and 2 switches - ON.

No. 2 generator - ON.

Twist grips (both) - Flight idle.

Radios - ON as required.

Caution panel lights Extinguished.

ENGINE RUNUP AND SYSTEM CHECK

Engine oil temperatures and pressures -Within limits.

Transmission oil temperatures and pressures- Within limits.

Gearbox oil temperature and pressure -Within limits.

Flight controls - Friction off: collective lockremoved.

Force trim - Off.

Hydraulic system 1 and 2 - Chock.

Force trim - ON.

Inverter No. 2 switch - OFF; check thatinverter No. 1 has assumed load. Returninverter No. 2 switch - ON.

CAUTION

DURING RPM INCREASE. ANYABNORMAL INCREASE IN 1PER REV VIBRATION MAYINDICATE ONE OR MORE MAINROTOR DROOP RESTRAINTSFAILED TO DISENGAGE FROMSTATIC POSITION. VERIFYPROPER OPERATION PRIOR TOFLIGHT.

Governor switches (1 and 2) - Individually toMANUAL then return to AUTO.

No. 1 twist grip - Full open. Check Nil RPMstabilizes to 95 i 1%.

No. 2 twist grip Full open. Check Nil RPMstabilizes at 97 + 1% (both engines).

RPM INCR-DECR switch - Full INCR. CheckNil RPM does not exceed 101.5%. Set at100%.

STICK CENTERING INDICATOR SYSTEMCHECKS.

0

IDC Voltmeters - Check 27 + 1 Vdc.

AC voltmeters - Check 104 to 122 Vac.

Ammeters - Check within limits.

Emergency load switch - EMERG LOAD.I Check that nonessential loads are dropped.

Emergency Load Switch - NORMAL.

Inverter No. 1 switch - OFF; check thatinverter No. 2 has assumed load. Returninverter No. 1 switch - ON.

CAUTION

CYCLIC DISPLACEMENT OFMORE THAN 1.5 INCHES FROMCENTER IS NOT REQUIRED TOCHECK THE SYSTEM. IF THECYC CTR CAUTION LIGHTS DONOT ILLUMINATE WITHIN A 1.5INCH DISPLACEMENT. THESYSTEM IS INOPERATIVE.

0

5-8 Rev. 3


Cyclic - Displace forward. Observe CYC CTRcaution lights illuminate.






AFCS CHECK


HP1 and HP2 switches - ON. Observe ATTlight on, actuator position indicators (APIs)centered, and caution panel AFCS light out.

Move cyclic forward, aft, right, left. Observethe APIs do not move.

SYS 2 switch - Press and hold.

Move cyclic forward, aft, right, left. Observethat APIs do not move.


ATT Trim Switch, right for 2 seconds, then aftfor 2 seconds. Observe APIs move right, up.

SYS 2 switch - Depress Observe SYS 2actuators agree.

Cyclic Force Trim release button - Depress.Observe APIs move to center.

SYS 2 Switch - Release. Observe SYS 1actuators agree.

SAS/ATT switch - Depress. Observe SASlight on.



Move pedals, right, left. Observe yaw APImoves right, left.

SYS 2 switch - Depress.




FORCE TRIM CHECK

Force Trim - Check operation. ObserveFORCE TRIM caution light when force trimswitch is off.

FUEL CROSSFEED VALVE CHECK

Fuel crossfeed valve - Check as follows:


Fuel crossfeed test switch - TEST BUS 1and hold.

Rev. 3 5-8A/5-8B


No. 1 boost pump - OFF. Check fuel pressuredecreases, then returns to normal. Return toON.






Fuel crossfeed switch - OVRD CLOSE.

No. 1 Boost pump- OFF. Check fuel pressuredrops to zero. Return switch to ON. RepeatforNo. 2 boost pump.


HEATER OPERATION CHECK

Heater - Check and set as desired.

GROUND OPERATION CHECK

NOTE

For prolonged ground operationAFCS shall not be operated in theATT mode.

iCAUTION

IF STICK CENTERING INDICA-TOR SYSTEM IS INOPERATIVE.NR FOR GROUND OPERATIONSHALL BE 97% OR ABOVE.

ON SIDE SLOPES GREATERTHAN FIVE DEGREES. DISRE-GARD CYC CTR CAUTIONLIGHTS AND POSITION CYCLICAS REQUIRED.


NOTE

At RPM between 95 and 105% NR,CYC CTR caution lights areinhibited.

BEFORE TAKEOFF

Instruments - Normal ranges.

Flight instruments - Check operation and set.

Position lights - ON as required.

Anticollision light - ON.

Pitot heater - As required.

Radio(s) - Check functioning.

Flight controls - Adjust friction as desired.

Twist grips - Check full open. Adjust friction.

Nil RPM - 100% (both engines).

Hydraulic systems - Check both on.

Force trim - As desired.

Step - As desired.

Passenger seat belts - Fastened.

I

CAUTION

MINIMUM NR FOR GROUNDOPERATION, WITH STICKCENTERING INDICATORSYSTEM INOPERATIVE. IS 97%.

NR - 77% or above.

Rev. 3 5-9


All doors - Secured.

All caution and warning lights - Extinguished.

POWER ASSURANCE CHECK

Perform power assurance check before firstflight of the day or as desired. (Refer to Section4.)

TAKEOFF

CAUTION

DURING LIFT-OFF TO HOVER.ANY ABNORMAL INCREASE IN1 PER REV VIBRATION MAYINDICATE ONE OR MORE MAINROTOR DROOP RESTRAINTSFAILED TO DISENGAGE FROMSTATIC POSITION. VERIFYPROPER OPERATION PRIOR TOFLIGHT.

Nil RPM - 100%.

FORCE TRIM release button Depress tocenter actuators.

Hover power - Check torque at 4 foot (1.2meter) skid height.

AFCS MODE - Select ATT or SAS.

IN-FLIGHT OPERATION

Nil RPM - 100%.

Airspeed - Within limits for gross weight andflight altitude.

Engine, gearbox, and transmissioninstruments - Within limitations.

If AFCS is in ATT mode, depress FORCE TRIMrelease button to maneuver.

DESCENT AND LANDING

Flight controls - Friction as desired.

Twist grips - Full open.

Nil RPM - 100%.

AFCS Control - ATT or SAS.

Force trim - ON in ATT mode, as desired inSAS mode.


Flight path - Stay clear of AVOID areas ofheight-velocity chart.

AFTER LANDING

FORCE TRIM release button Depress.

HELIPILOT CONTROLLER - Depress HP1and HP2.

Collective pitch - Down; install down lock.

Cyclic control and pedals - Centered; frictionas desired.

Force trim - ON.

Twist grips - Flight idle.

ITT - Stabilize for one minute at flight idle.

Engine instruments - Within limits.

Radios - OFF.

ENGINE SHUTDOWN

Idle stop release - ENG 1.

No. 1 twist grip - Full closed. Check ITT andNI RPM decreasing.

No. 1 fuel - OFF.

0

0

0

5-10 Rev. 3


No. 1 boost pump - OFF.

Idle stop release - ENG 2.

No. 2 twist grip Full closed. Check ITT andNI RPM decreasing.

No. 2 fuel - OFF.

No. 2 boost pump - OFF.

Generators - OFF.

Inverters - OFF.

Rotor brake - As desired below 40% Nr.

Pilot - Remain at controls until rotor stops.

Lighting and miscellaneous switches - OFF.

Battery switches OFF.

AFTER EXITING HELICOPTER

Main rotor blades - Tiedowns installed.

Pitot tube, engine inlet, exhaust covers --Installed.

Rev. 3 5-11/5-12

MANUFACTURER'S 412 FLIGHT MANUALDATA

TABLE OF CONTENTS

Paragraph

W eight Empty Center of Gravity .........................................................Gross W eight Center of Gravity ..........................................................Cockpit and Cabin Loading ........................................................ .....Fuel Loading ............................................................................Baggage Compartment Loading ..........................................................Weight and Balance Diagrams and Loading Tables ........................................Pilot and Passenger Table of M oments ...................................................Fuel Loading Tables......................................................................Baggage Loading Table ..................................................................Internal Cargo Loading Table .............................................................Sample Loading Problem (English) .......................................................Sample Loading Problem (Metric) ........................................................Required Equipment List .................................................................

Section 6

PageNumber

6-36-36-36-36-36-56-56-56-56-5

6-136-156-17

LIST OF FIGURES

FigureNumber

PageNumberTitle

6-1 Helicopter Station Diagram .................................................. 6-4

LIST OF TABLES

TableNumber Title

6-1 Pilot and Passenger Table of Moments (English) ..............................6-2 Pilot and Passenger Table of Moments (Metric) ...............................6-3 Fuel Loading Table (English) .................................................6-4 Fuel Loading Table (Metric) ..................................................6-6 Baggage Loading Table (English) .............................................6-6 Baggage Loading Table (Metric) ..............................................6-7 Internal Cargo Loading Table English) .......................................6-8 Internal Cargo Loading Table (Metric) ........................................

PageNumber

6-66-76-86-9

6-106-106-116-12

6-1/6-2

MANUFACTURER'SDATA


WEIGHT EMPTY CENTER OFGRAVITY

The cabin deck cargo loading limit is 100pounds per square foot (4.9 kg/100 sq cm).

The empty weight consists of the basichelicopter with required equipment, optionalequipment kits, transmission and gearbox oils,hydraulic fluid, unusable fuel, undrainableengine oil, and fixed ballast. The empty weightcenter of gravity shall be adjusted within thelimits of the applicable Weight Empty Centerof Gravity chart in the Maintenance Manual,Volume 1, Chapter 8.

GROSS WEIGHT CENTER OFGRAVITYIt shall be the pilots responsibility to ensurethat the helicopter is properly loaded so thatthe entire flight is conducted within the limitsof the Gross Weight of Gravity chart inSection 1. The gross weight center of gravitymay be calculated from the helicopter ActualWeight Record (historical records) and theLoading Tables in this section or in appropriateFlight Manual Supplements to assure safeloading.

COCKPIT AND CABIN LOADING

A minimum crew weight of 170 pounds (77.1kg) in the cockpit is required. Except for thetwo aft passenger seats, crew and passengersmay be loaded in any sequence withoutexceeding the gross weight center of gravitylimits approved for flight.

NOTE

The two aft outboard facing seatsshould not be occupied unless at leasttwo passengers are seated in theforward and/or aft facing seats.

FUEL LOADING

At the beginning of any flight with full fuel onboard, the helicopter center of gravity willmove forward due to the fact that the CG ofthe fuel on board moves forward as it isconsumed. This occurs because fuel isconsumed from the upper rear fuel cells first.The maximum forward CG condition of thefuel on board occurs when 72.6 U.S. gallons(274.8 liters) remain. The CG then begins tomove rearward as fuel is consumed from thelower fuel cells. With normal crew andpassenger loading, gross weight CG willremain within limits at any fuel quantity.

BAGGAGE COMPARTMENTLOADINGThe baggage compartment is accessible fromthe right side of the tailboom and containsapproximately 30 cubic feet (0.86 cubicmeters) of space. The baggage compartmenthas a load limit of 400 pounds (181 kg), not toexceed 100 pounds per square foot (4.9kg/100 sq cm). These are structurallimitations only. and do not infer that CG willremain within approved limits. When weight isloaded into the baggage compartment.indiscriminate crew, passenger and fuelloading can no longer be assumed, and thepilot must compute gross weight CG to assureloading within approved limits. Loading of thecompartment should be from front to rear, andthe load shall be secured to tiedown fittings toprevent shifting of CG during flight.

6-3

Section 6 412 FLIGHT MANUAL MANUFACTURER'SDATA

FUSELAGESTATIONS

0 23 102 129 166 177 243

REF /4DATUM

PILOT SEAT

(2) COPILOT OR PASSENGER SEAT

FUELTANKSSEATS ^

LATERAL LOCATION (INCHES FROM GL) OF HELICOPTER

LONGITUDINAL LOCATION (INCHES AFT OF REF DATUM )OF PERSONNEL

EXTERNAL CARGO

412900-7

Figure 6-1. Helicopter station diagram

6-4

MANUFACTURER'SDATA

WEIGHT ANDDIAGRAMS ANDTABLES


BALANCE Table 6-6 provides metric arms and momentsLOADING for weights from 10 to 180 kilograms, in ten

kilogram increments, in the baggage com-partment. Moments are in kilogram-

millimaarc innPILOT AND PASSENGER TABLE OFMOMENTS

Table 6-1 lists moments for individualpersonnel weights from 100 pounds to 220pounds in ten pound increments, in each seatstation. Moments are shown in inch-pounds.

Table 6-2. lists moments for individualpersonnel weights from 50 to 110 kilograms,in five kilogram increments, in each seatstation. Moments are shown in kilogram-millimeter + 100.

FUEL LOADING TABLES

Table 6-3 lists fuel quantities and weights,their center of gravity, and their moments.Quantities are given from 10 to 220 gallons inten gallon increments. Moments are in inch-pounds.

Table 6-4 is a metric fuel loading table givingfuel quantities and weights, center of gravityand moments. Data is provided for quantitiesfrom 40 to 840 liters in 40 liter increments.Moments are in kilograms-millimeters - 100.

BAGGAGE LOADING TABLE

Table 6-5 provides arms and moments forweights from 20 to 400 pounds in the baggagecompartment. Moments are in inch-pounds.

INTERNAL CARGO LOADING TABLE

Table 6-7 provides internal cargo weights andtheir moments at various flight stations.Weights from 50 to 1500 pounds are given infifty pound increments. Moments are in inch-pounds.

Table 6-8 provides internal cargo weights andtheir moments at various flight stations.Weights from 25 to 700 kilograms are given intwenty-five kilogram increments. Momentsare in kilogram-millimeters + 100.

ICAUTION

MAXIMUM CABIN FLOOR LOAD-ING ALLOWED IS 100 POUNDS PERSQUARE FOOT (1 KILOGRAM PER200 SQUARE MILLIMETERS).

WARNING

AIRCRAFT CENTER OF GRAVITYMUST BE COMPUTED FOR ALLCARGO CONFIGURATIONS BE-FORE FLIGHT.

6-5


Table 6-1. Pilot and passenger table of moments (English)

PILOT AND PASSENGER TABLE OF MOMENTS (IN-LB)

Passenger Passenger PASSENGER LITTER PATIENTPilot and (4-Man Seat (5-Man Seat FACING OUTBOARD Lateral Longitudinal

Weight Copilot' Facing Aft) Facing Fwd) Fwd Seat Aft Seat Loaded Loaded

11700 13900 15600 11700 1200012870 15290 17160 12870 1320014040 16680 18720 14040 1440015210 18070 20280 15210 1560016380 19460 21840 16380 1680017550 20850 23400 17550 1800018720 22240 24960 18720 1920019890 23630 26520 19890 2040021060 25020 28080 21060 2160022230 26410 29640 22230 2280023400 27800 31200 23400 2400024570 29190 32760 24570 2520025740 30580 34320 25740 26400

MANUFACTURER'S 412 FLIGHT MANUAL Section 6DATA

Table 6-2. Pilot and passenger table of moments (Metric)

PILOT AND PASSENGER TABLE OF MOMENTS(kg - mm)

100

Passenger Passenger PASSENGER UTTER PATIENTPilot and (4-Man Seat (5-Man Seat FACING OUTBOARD Lateral Longitudinal

*Left Forward Seat

412900-6

6-7


Table 6-3. Fuel loading table (English)

USABLE FUEL LOADING TABLE (ENGLISH)

Jet B. JP-4 (6.5 Lbs/Gal) Jet A. A-1, JP-5 (6.8 Lbs/Gal)

U.S. WeightGal. (Lbs.)

U.S. Weight

CG Moment Gal. (Lbs.) CG Moment

10203040506070

*72.68090

100110120130140160160170180190200210220

66 143.6130 143.6195 140.2260 134.8326 131.6390 129.4455 127.9472 127.6520 128.3585 130.6650 134.6715 137.8780 140.4846 142.6910 144.6975 146.1

1040 147.61105 148.41170 149.91235 150.91300 151.91365 162.71430 153.6

93341866827348350554277150480581866022766706764118747198512

109477120508131547142435153519164460175439186310197430208404219648

10203040506070

*72.68090

100110120130140160160170180190200210220

68 143.6136 143.6204 140.2272 134.8340 131.6408 129.4476 127.9494 127.6544 128.3612 130.6680 134.6748 137.8816 140.4884 142.6962 144.6

1020 146.11088 147.61156 148.41224 149.91292 150.91360 151.91428 152.71496 153.6

976519530286013666644744527956088062994697957992791528

103074114566126058137659149022160589172013183478194963206584218056229786

Most critical fuel amount for most forward CG condition.

412900-33A

6-8

MANUFACTURER'SDATA


Table 6-4. Fuel loading table (Metric)

USABLE FUEL LOADING TABLE (METRIC)

Jet B JP-4 (.779 kg/1)

MomentWeight CG kg/mm

Liters (kg) (mm) 100

40 31.2 3647 1137.980 62.3 3647 2272.1

120 93.5 3541 3310.8160 124.6 3399 4235.2200 155.8 3322 5175.7240 187.0 3272 6118.6274.8 214.1 3241 6939.0280 218.1 3246 7079.5320 249.3 3277 8169.6360 280.4 3368 9443.9400 311.6 3470 10812.5440 342.8 3541 12138.5480 373.9 3609 13494.1520 405.1 3665 14846.9560 436.2 3708 16174.3600 467.4 3744 17499.5640 498.6 3777 18832.1680 529.7 3805 20155.1720 560.9 3833 21499.3760 592.0 3858 22839.4800 623.3 3881 24186.4840 654.4 3904 25547.8

Jet A, JP-5 (.815 kg/l)

MomentWeight CG kg/mm

Liters (kg) (mm) 100

40 32.6 3647 1188.980 65.2 3647 2377.8

120 97.8 3541 3463.1160 130.4 3399 4432.3200 163.0 3322 5414.9240 195.6 3272 6400.0274.8 224.0 3241 7259.8280 228.2 3246 7407.4320 260.8 3277 8546.4360 293.4 3368 9881.7400 326.0 3470 11312.2440 358.6 3541 12698.0480 391.2 3609 14118.4520 423.8 3665 15532.3560 456.4 3708 16923.3600 489.0 3744 18308.2640 521.6 3777 19700.8680 554.2 3805 21087.3720 586.8 3833 22492.0760 619.4 3858 23896.5800 652.0 3881 25304.5840 684.6 3904 26726.8

'Most critical fuel amount for most forward CG condition.Weights given are nominal weights at 15°C.

412900-34A

6-9


Table 6-5. Baggage loading table (English) Table 6-6. Baggage loading table (Metric)

BAGGAGE COMPARTMENT BAGGAGE COMPARTMENT

Weight Approximate CG Moment(Lbs) (F.S.) Moment Weight Approximate CG (kg/mm)

(kg) (mm) 100

20 245 490040 247 9880 10 6223 622.360 249 14940 20 6280 1256.080 251 20080 30 6336 1900.8

100 253 25300 40 6393 2557.250 6450 3225.0

120 255 30600 60 6506 3903.6140 257 35980 70 6563 4594.1160 259 41440 80 6620 5296.0180 261 46980 90 6677 6009.3200 263 52600 100 6733 6733.0

110 6790 7469.0220 265 58300 120 6847 8216.4240 267 64080 130 6903 8973.9260 269 69940 140 6960 9744.0280 271 75880 150 7017 10525.5300 273 81900 160 7073 11316.8

170 7130 12121.0320 275 88000 180 7187 12936.6340 277 94180360 279 100440 LOAD BAGGAGE FROM FORWARD END380 281 106780380 281 106780 OF COMPARTMENT400 283 113200

180 KILOGRAM MAXIMUMLOAD BAGGAGE

FROM FORWARD END OF COMPARTMENT 412900-30400 POUND MAXIMUM

412900-29

6-10

MANUFACTURER'SDATA


Table 6-7. Internal cargo loading table (English)

INTERNAL CARGO LOADING TABLE (ENGLISH)

MOMENTS In-Lb

WeightPounds F.S. 75.0

50 3750100 7500150 11250200 15000250 18750

F.S. 90.0 F.S. 105.0 F.S. 120.0 F.S. 135.0 F.S. 150.0

4600 5250 6000 6750 75009000 10500 12000 13500 15000

13500 15750 18000 20250 2250018000 21000 24000 27000 3000022500 26250 30000 33750 37500

300350400450500

550600650700750

800850900950

1000

10501100115012001250

13001350140014501500

2250026250300003375037500

4125045000487505250056250

6000063750675007125075000

7875082500862509000093750

97500101250105000108750112500

2700031500360004050045000

4950054000585006300067500

7200076500810008550090000

9450099000

103500108000112500

117000121500126000130500135000

3150036750420004725052500

5775063000682507350078750

84000892509450099750

105000

110250115500120750126000131250

136500141750147000152250157500

36000 40500 4500042000 47250 5250048000 54000 6000054000 60750 6750060000 67500 75000

66000 74250 8250072000 81000 9000078000 87750 9750084000 94500 10500090000 101250 112500

96000 108000 120000102000 114750 127500108000 121500 135000114000 128250 142500120000 135000 150000

126000 141750 157500132000 148500 165000138000 155250 172500144000 162000 180000150000 168750 187500

156000 175500 195000162000 182250 202500168000 189000 210000174000 195750 217500180000 202500 225000

412900-15

6-11


Table 6-8. Internal cargo loading table (Metric)

INTERNAL CARGO LOADING TABLE (METRIC)

MOMENTS (kg - mm/100)

Weight(kg) 1900 mm 2300 mm 2700 mm 3100 mm 3400 mm 3800 mm

25 475.0 575.0 675.0 775.0 850.0 950.050 950.0 1150.0 1350.0 1550.0 1700.0 1900.075 1425.0 1725.0 2025.0 2325.0 2550.0 2850.0

100 1900.0 2300.0 2700.0 3100.0 3400.0 3800.0

125 2375.0 2875.0 3375.0 3875.0 4250.0 4750.0150 2850.0 3450.0 4050.0 4650.0 5100.0 5700.0175 3325.0 4025.0 4725.0 5425.0 5950.0 6650.0200 3800.0 4600.0 5400.0 6200.0 6800.0 7600.0

225 4275.0 5175.0 6075.0 6975.0 7650.0 8550.0250 4750.0 5750.0 6750.0 7750.0 8500.0 9500.0275 5225.0 6325.0 7425.0 8525.0 9350.0 10450.0300 5700.0 6900.0 8100.0 9300.0 10200.0 11400.0

325 6175.0 7475.0 8775.0 10075.0 11050.0 12350.0350 6650.0 8050.0 9450.0 10850.0 11900.0 13300.0375 7125.0 8625.0 10125.0 11625.0 12750.0 14250.0400 7600.0 9200.0 10800.0 12400.0 13600.0 15200.0

425 8075.0 9775.0 11475.0 13175.0 14450.0 16150.0450 8550.0 10350.0 12150.0 13950.0 15300.0 17100.0475 9025.0 10925.0 12825.0 14725.0 16150.0 18050.0500 9500.0 11500.0 13500.0 15500.0 17000.0 19000.0

525 9975.0 12075.0 14175.0 16275.0 17850.0 19950.0550 10450.0 12650.0 14850.0 17050.0 18700.0 20900.0575 10925.0 13225.0 15525.0 17825.0 19550.0 21850.0600 11400.0 13800.0 16200.0 18600.0 20400.0 22800.0

625 11875.0 14376.0 16875.0 19375.0 21250.0 23750.0650 12350.0 14950.0 17550.0 20150.0 22100.0 24700.0675 12825.0 16525.0 18225.0 20925.0 22950.0 25650.0700 13300.0 16100.0 18900.0 21700.0 23800.0 26600.0

412900-16

6-12

MANUFACTURER'SDATA


SAMPLE LOADING PROBLEM trip that will require approximately 150

W0 The helicopter is chartered to transport nine both trips.passengers and 180 pounds of baggage on a

LONGITUDINAL LATERAL

FIRST LEG WEIGHT CG MOMENT CG MOMENTLBS IN IN/LBS IN IN/LBS

Weight Empty

+ Oil+ Pilot+ Passengers (5 man seat)+ Passengers (4 man seat)+ Baggage

Basic Operating Weight+ Payload

+ Takeoff Fuel (211 U.S. Gal.)Takeoff Weight

6167 144.0 888048 +0.2

25190850680180

41468930

994505916046980

0+22.0

000

+1233

0+4180

000

+5413

0+5413

8092 136.8 1106714 +0.7

13749466

209947139.1 1316661

0+0.6


+ Critical Forward Fuel(72.6 U.S. Gal.)

8092

472

1106714 +5413

60227 0 0

Most Forward Condition


+ Landing Fuel (60 U.S. Gal.)Landing Weight

8564 136.3 1166941 +0.6 +5413

8092

3908482

1106714

50480136.4 1157194

+5413

0+0.6

0+5413

6-13


SECOND LEG

Weight Empty

+ Oil+ Pilot

Basic Operating Weight

+ Takeoff Fuel (211 U.S. Gal.)

Takeoff Weight


+ Critical Forward Fuel(72.6 U.S. Gal.)



+ Landing Fuel (60 U.S. Gal.)Landing Weight

WEIGHTLBS

6167

25190

6382

1374

7756

6382

472

6854

6382

3906772

LONGITUDINAL

CG MOMENTIN IN/LBS

144.0 888048

4146

141.2 901124

209947

143.3 1111071

901124

60227

LATERAL

CG MOMENTIN IN/LBS

+0.2 +123


SAMPLE LOADING PROBLEM(METRIC)

At the beginning of any flight with full fuel onboard, the CG of the helicopter will moveforward as fuel is burned off. This occursbecause fuel is burned from the upper rear fuelcells first. A maximum forward center ofgravity condition occurs when 274.8 liters

(214.1 kg) of fuel is on board. The CG thenbegins to move rearward as fuel is burned offfrom the lower fuel cells. Helicopter ischartered to transport nine passengers and 80kg of baggage for a trip that will requireapproximately 560 liters of fuel. The 90 kgpilot will return alone. Determine extreme CGconditions for both trips.

LONGITUDINAL LATERAL

FIRST LEGWEIGHT CG MOMENT

(kg) (mm) kg-mm/100

2797.0 3658 102314.3

CG(mm)

MOMENTkg-mm/100

Weight Empty +5 +139

+ Oil+ Pilot+ Passengers (5 man seat)+ Passengers (4 man seat)+ Baggage

11.390.0

375.0300.0

80.0

485.31074.6

11145.06630.05296.0

0+559

000

0+503

000


+ Takeoff Fuel (800 liters)

Takeoff Weight

3653.3 3475 126945.2 +13 +643

623.3 24190.3 0 0

4276.6 3534 151135.5 +15 +643


+ Critical Forward Fuel(274.8 liters)

3653.3

214.1

126945.2 +643

6939.0 0 0



+ Landing Fuel (240 liters)

3867.4 3462 133884.2 +17 +643

3653.3

187.0

126945.2 +643

6118.6 0 0

6-15


SECOND LEG

Weight Empty

+ Oil+ Pilot


+ Takeoff Fuel (800 liters)

Takeoff Weight


+ Critical Forward Fuel(274.8 liters)



+ Landing Fuel (240 liters)

Landing Weight

LONGITUDINAL

WEIGHT CG MOMENT(kg) (mm) kg-mm

/100

2797.0 3658 102314.3

11.3 485.390.0 1074.6

2898.3 3584 103874.2

623.3 24190.3

3521.6 3637 128064.5

2898.3 103874.2

214.1 6939.0

3112.4 3560 110813.2

2898.3 103874.2

187.0 6118.6

3085.3 3565 109992.8

LATERAL

CG MOMENT(mm) kg-mm

/100

+5 +139

0 0+559 +503

+22 +643

0 0

+18 +643

+643

0 0

+21 +643

+643

0 0

+21 +643

6-16

MANUFACTURER'SDATA


REQUIRED EQUIPMENT LIST

List of basic equipment required for flight ispresented. Weights and arms listed for each

item were included in calculating the emptyweight and center of gravity.

UNITWEIGHTLBS/kg

LONGITUDINALARM

IN/mm

LATERAL ARM(- LEFT. + RIGHT)

IN/mmREQUIRED EQUIPMENT

INDICATORSAttitudeAirspeedVertical SpeedAltimeterTriple TachometerXMSN Oil Press & TempGearbox Oil Press & TempEngine Oil Press & TempFuel PressureGas Producer TachometerTurbine Inlet TemperatureHydraulic Oil Press & TempDual Torque PressureFuel QuantityStandby CompassHorizontal SituationClockFree Air TemperatureDual DC AmmeterDual AC/DC VoltmeterFire Warning -

Engine No. 1Engine No. 2Baggage Compartment

Low Fuel WRN -Master Caution Pnl

Starter-Generator, L.H.Starter-Generator, R.H.BatteryStarter Toggle SwitchFuel Igniter SwitchAnti-Collision Light, UpperAnti-Collision Light, LowerLanding LightSearchlight

7.5/ 3.4 21.0/1.1/ 0.5 23.0/1.8/ 0.8 23.0/1.8/ 0.8 23.0/2.5/ 1.1 23.0/0.7/ 0.3 23.0/0.7/ 0.3 23.0/

(2) 0.4/ 0.2 23.0/(2) 0.6/ 0.3 23.0/(2) 1.0/ 0.5 23.0/(2) 0.6/ 0.3 23.0/(2) 0.4/ 0.2 23.0/

3.0/ 1.4 23.0/0.6/ 0.3 23.0/0.8/ 0.4 39.0/6.9/ 3.1 21.0/0.5/ 0.2 23.0/0.2/ 0.1 34.0/1.0/ 0.5 25.0/

(2) 1.0/ 0.5 25.0/

0.4/ 0.2 22.3/0.4/ 0.2 22.3/0.3/ 0.1 22.0/

533584584584584584584584584584584584584584991533584864635635

566516559

+17.0/+432+12.5/+318+21.4/+544+21.4/+544

+9.0/+229+1.3/+41+1.3/+41+4.8/+122+4.8/+122+4.8/+122+4.8/+122+4.8/+122

+12.5/+318+1.3/+41

+17.5/+445+17.0/+432+25.0/+635

+3.0/+76+1.3/+41+4.8/+122

-1.7/-43+4.7/+119-1.8/-46

-3.4/-86

-8.0/-203+18.0/+457

+7.9/+201+10.0/+254

+3.0/+760/00/0

-4.1/-1040/0

5.0/ 2.3

30.0/13.630.0/13.680.0/36.3

0.4/ 0.2(2) 0.2/ 0.1

2.0/ 0.92.0/ 0.98.1/ 3.75.4/ 2.4

24.0/ 610

159.0/159.0/

-5.7/38.0/33.0/

218.0/65.4/83.0/

9.0/

40394039-145965838

553716612108

229

6-17


UNITWEIGHTLBS/kg

LONGITUDINALARM

IN/mm

LATERAL ARM(- LEFT, + RIGHT)

IN/mmREQUIRED EQUIPMENT

Position Lights -Forward Lower (2) 0.3/ 0.1Forward Upper (2) 0.3/ 0.1Aft (2) 0.3/ 0.1

Circuit Breaker Panels (2) 7.4/ 3.4Non-Essential Bus Switch 0.1/NEGEssential Bus

Right Side Ovhd Cont Pnl 2.9/ 1.3Left Side Ovhd Cont Pnl 2.4/ 1.1

Low Fuel Wrn XMTR (2) 0.1/NEGVHF NO. 1 Radio -

Transceiver and Mount 4.3/ 2.0Control 1.5/ 0.7Antenna 0.5/ 0.2

Windshield Wiper -Blade and Arm (2) 1.6/ 0.7Motor (2) 4.2/ 1.9

Fire Extinguisher Hand Type, L.H. 8.0/ 3.6Fire Extinguisher. Hand Type, R.H. 8.0/ 3.6Safety Belt & Harness-Pilot 2.7/ 1.2

66.8/ 1697109.2/ 2774431.9/10970

56.8/ 144341.2/ 1046

42.8/ 108741.4/ 1052

143.0/ 3632

9.5/ 24139.0/ 991

205.0/ 5207

34.0/ 86441.0/ 104169.0/ 175353.0/ 134647.0/ 1194

0/00/00/00/0

+4.7/+119

+3.2/+81-3.4/-86

0/0

+0.8/+20-3.0/-76

0/0

0/00/0

-42.0/-1067+34.0/+864+22.0/+559

0

Flight Manual 1.7/ 0.8

6-18



Helicopter General ....................................................................... 7-3Airframe ................................................................................ 7-3Principal Dimensions ................................................................ 7-3Stations. Waterlines, and Buttock Lines .................................................. 7-3Rotor System ........................................................................... 7-3Transmission ............................................................................ 7-3Powerplant System ............................................................ .......... 7-3Fuel System ................................................................... .......... 7-5Electrical System . ................... ......................................... 7-5Hydraulic System ........................................................................ 7-9Flight Control System .................................................................. 7-9Instrument Panel .............................................................. .......... 7-9Pitot-Static System ...................................................................... 7-16Heating - Ventilating System ........................................................... 7-16Windshield Wipers ............................................................. .......... 7-16Cabin Lights ............................................................................. 7-16Fire Detection - Protection System ...................................................... 7-16Automatic Flight Control System (AFCS) ................................................. 7-16Intercommunications System ............................................................ 7-17

LIST OF FIGURES


7-1 Principal Dimensions ........................................................ 7-47-2 DC Electrical System ........................................................ 7-67-3 AC Electrical System ........................................................ 7-87-4 Instrument Panel ............................................................ 7-117-5 Caution Panel............................................................... 7-137-6 Miscellaneous System Switches and Panels .................................. 7-147-7 Overhead Console ........................................................... 7-15

7-1/7-2

MANUFACTURER'S 412 FLIGIDATA

HELICOPTER GENERAL

The Bell Helicopter Textron Model 412 is afifteen-place helicopter with a single fourbladed main rotor system and a tail rotor toprovide directional control.

AIRFRAME

HT MANUAL Section 7

Buttock Lines (B.L.) - Buttock lines arevertical planes perpendicular to, and measuredto the left and right along the lateral axis of thehelicopter. Buttock line (0) is the plane at thelongitudinal centerline of the helicopter.

ROTOR SYSTEM

The airframe is primarily a semi-monocoquestructure with metal and fiberglass covering.Two longitudinal main beams and the pylonstructure provide primary support.

PRINCIPAL DIMENSIONS

Figure 7-1 shows the principal dimensions ofthe helicopter. All height dimensions must beconsidered approximate due to variations inloading and alighting gear deflection.

STATIONS, WATERLINES, ANDBUTTOCK LINES

Locations on and within the helicopter can bedetermined in relation to fuselage stations,waterlines, and buttock lines, measured ininches from known reference points.

Fuselage Stations (F.S. or STA.) - Fuselagestations are vertical planes perpendicular to,and measured along, the longitudinal axis ofthe helicopter. Station (0) is the ReferenceDatum plane and is 20 inches (508 milli-meters) aft of the nose of the helicopter.

Waterlines (W.L.) - Waterlines are horizontalplanes perpendicular to, and measured along,the vertical axis of the helicopter. Waterline (0)is a plane usually below the lowest point on thefuselage of the helicopter.

The main rotor system consists of fourcomposite blades mounted to flex beam typeyokes to provide a soft-in-plane arrangement.Elastomeric bearings help dampen outvibrations and provide some lead lag for themain rotor blades.

TRANSMISSION

The transmission is mounted in the pylonsupport structure with four vibration isolatingmounts. Two stages of planetary reductiongears and spiral bevel gears are used to reduceinput RPM to the speeds required for mainrotor and tail rotor drive. Both hydraulicpumps are driven by the transmission.

An instrument on the panel allows the flightcrew to monitor transmission oil temperatureand transmission oil pressure. Caution lightsare provided to warn of high transmission oiltemperature, low transmission oil pressure,and metal particles in transmission oil. Aremote transmission chip indicator is on theright side of the pedestal by the pilots knees.

POWERPLANT SYSTEM

The powerplant, a Pratt and Whitney PT6T-3B, consists of two identical free turbine

7-3

412 FLIGHT MANU AL MANUFACTURER'SDATA

NOTE

Dimensions are given in English units withmetrics in parenthesis for standardconfiguration and 11,600 pound (5262kilogram) gross weight.

56 FT. 2 IN.45 FT. 11 IN. (17.1 m)

(14 m)

Figure 7-1. Principle dimensions

7-4


power sections connected to a combiningreduction gearbox. Each power section has itsown lubrication system, starter-generator,fuel control N1 tachometer generator, and NIItachometer generator. The combining gear-box has a separate lubrication system.

Instruments on the panel provide an indicationof NI RPM, Nil RPM, torque, interturbinetemperature, oil temperature, and oil pressurefor each power section. An instrument forcombining gearbox oil temperature and oilpressure is provided. Caution lights provide awarning for either engine NI or NIl RPMabnormally low, either engine oil pressurebelow limit, metal particles in the oil of eitherengine, combining gearbox oil pressure toolow, combining gearbox oil temperature toohigh, and metal particles in combining gearboxoil.

FUEL SYSTEM

Five crashworthy fuel cells with a usablecapacity of 211 U.S. gallons (798.7 liters)contain fuel for the helicopter. Two lower cellsare mounted under the aft cabin floor. Thethree aft fuel cells which are behind the aftcabin bulkhead, gravity feed to the two lowercells.

An interconnect valve prevents an out of CGcondition resulting from uneven fuel flow.Crossfeed valves and boost pumps are used toensure that fuel will be supplied to bothengines at all times. Electric drain valves aremounted in the lower cell sump plates.

A selector switch and fuel quantity gage on theinstrument panel allows the flight crew to readthe quantity of either lower cell or the total ofall cells combined. Fuel pressure gagesindicate fuel pressure at each engine.

Caution lights give warning of boost pumpfailure, impending fuel filter bypass, low fuelquantity, fuel valve not completely open orclosed, or fuel crossfeed valve not completelyopen or closed.

ELECTRICAL SYSTEM

DC POWER SYSTEM

The primary electrical system is a 28-voltdirect current, negative ground system. 28Vdc power is supplied by two 30-volt, 200-ampere starter-generators, one mounted oneach engine. The output voltage of eachgenerator is monitored and regulated by a DCControl Unit. The DC control units provideovervoltage and reverse current protectionand control paralleled generator operation sothat the two DC generators share total loadrequirements within ± 20 amperes. Eachgenerator supplies power to a main DC busand to two interconnected nonessential DCbuses. Each main DC bus in turn, serves as afeeder for the two essential DC buses and twoemergency buses. See figure 7-2. Electricalseparation between main buses and betweengenerators is accomplished through the use ofcircuit breakers and isolation diodes. In theevent that one generator or engine should fail,both nonessential buses are automaticallydropped, and all essential DC loads aresupplied by the remaining starter-generator.An override switch is available so that thepilot, at his discretion, can manually restorepower to the nonessential buses. In the eventthat the pilot has manually restored power tothe nonessential buses and the secondgenerator fails, both nonessential buses areagain automatically dropped. This arrange-ment allows automatic DC load shedding for30 minute flight with battery only. TheEMERG LOAD switch may be actuated toprovide 90 minutes flight with battery poweronly.

The electric power distribution system islocated in the roof and in the nose of theaircraft. The generator control units, con-tactors, buses and feeder protection devicesare located under the lower nose shelf, and thebattery sits on top of this shelf. Othercontactors, feeder protection devices, and thedistribution buses are located in the roof.System control switches and distribution

7-5


NO. ESNTL DC BUS

BATTERY

412075-57

Figure 7-2. DC electrical system

MANUFACTURER'SDATA


circuit breakers are located in the overheadconsole.

Control of the DC system is via the followingswitches and circuit breakers:

No. 1 Essential Bus Right CB PanelFeeders (2)

No. 2 Essential Bus Left CB PanelFeeders (2)

Feeders (2)

Nonessential Bus Right Aux CB Panel

Battery Bus 2 Ovhd Console Off-OnControl Pnl (Magnetic) AC POWER SYSTEM

Generator 1 Ovhd Console Reset-Off-OnControl Pnl

Generator 2 Ovhd Console Reset-Off-OnControl Pnl

Noness Bus Ovhd Console Manual-Control Pnl Normal

The secondary or AC power system consists oftwo 450 VA, 115/26-volt, 400 Hz, singlephase, solid state inverters and associatedcontrols. Inverter 1 is energized by essentialDC bus No. 1. It is controlled by inverter 1switch located on the electrical power andlighting control panel in the overhead console.Inverter 2 is energized by essential DC bus No.2. It is controlled by inverter 2 switch locatedon the electrical power and lighting controlpanel in the overhead console.

Start Pit Collective Eng 1 - Eng 2Stick

CIRCUITBREAKERS

No. 1 Bus Battery

No. 2 Bus Battery

No. 1 Gen Field

No. 2 Gen Field

Gen 1 Reset

Gen 2 Reset

Eng 1 Start Relay

Eng 2 Start Relay

No. 1 Essential BusFeeders (2)

LOCATION

Pedestal HourmeterPanel

Pedestal HourmeterPanel

Left CB Panel

Right CB Panel

Left CB Panel

Right CB Panel

Left CB Panel

Right CB Panel

Left CB Panel

There are three additional components essen-tial to the control and operation of the ACpower system. AC voltage sensor relay No. 1,AC voltage sensor relay No. 2, and the AC buscontrol relay. The AC voltage sensor relaysmonitor each inverter 115V output andmaintains that power to the buses whenvoltage is 104-125 Vac. In the event voltage isout of this range, the voltage sensor relay willde-energize after one second, removing thatpower from the buses.

Should either inverter fail, the remaininginverter will assume all AC loads.

Inverter No. 1, inverter No. 2. and AC voltagesensor relays are located on lower side oflower nose shelf. The bus control relay islocated in the roof aft of overhead console.

Inv 1 Pwr and Inv 2 Pwr circuit breakersprotect DC lines providing power to therespective inverters.

7-7


Indication of failed inverters is provided by Pilot 26V Coplt 115Vinverter 1 and inverter 2 segments in the Bus Feeder Bus Feedermaster caution panel.

Pilot 115V AFCSA simplified single line schematic of the AC Bus Feeder Bus 3 26Vpower system is presented in figure 7-3.

Coplt 26V AFCSThe following circuit breakers control the AC Bus Feeder Bus 3 115Vpower. Location of these circuit breakers is inthe overhead console.

Figure 7-3. AC electrical system


HYDRAULIC SYSTEM

Two separate hydraulic systems are used toassist cyclic, collective, and anti-torque flightcontrols. Each system contains a reservoir,pump, integrated valve and filter assembly,accumulators and check valves.

Each integrated valve and filter assemblycontains a system pressure filter and a systemreturn filter. In the event any one of thesefilters becomes partially clogged, a button onthe housing will pop out to give a visibleindication of an impending bypass. This buttonwill also activate a switch, causing a remotehydraulic filter bypass indicator in the rightcabin nose compartment, to switch fromgreen to red. The integrated valve and filterassemblies are visible through smalltransparent windows in the pylon structure inthe aft cabin.

The pumps, which are driven by the trans-mission, have a different rated capacity. TheSystem 1 pump delivers a greater volume offluid to operate the anti-torque flight controlcyclinder.

Each system has an instrument to allow theflight crew to read that systems fluidtemperature and pressure. A caution lightwarns of high temperature or low pressure.

FLIGHT CONTROL SYSTEM

Normal helicopter type dual flight controls areprovided to control attitude, altitude, anddirection. Control inputs from the cyclic stick,collective stick, and anti-torque pedals aretransmitted by push-pull tubes and bellcranksto the hydraulic flight control cylinders. The

two cyclic flight control cylinders are con-nected to the swashplate. The collective flightcontrol cylinder is connected to the collectivelever at the mast. The anti-torque flight controlcylinder is in the aft fuselage compartment andis connected between bellcranks to assist indirectional flight control.

Fore and aft and lateral cyclic inputs arecombined in a mixing lever assembly toprovide positive cyclic control for any stickinput.

Hydraulically boosted flight control cylindersare used to help overcome the resistance of theelastometric bearings in the main rotorsystem.

INSTRUMENT PANEL

The instrument panel, which consists of threeseparate sections, extends across the front ofthe flight compartment. It is slightly tilted toprovide better viewing of the instruments bythe flight crew.

The flight instruments are mounted on thesection in front of the pilots seat. The engineinstruments and the caution panel aremounted on the center section of the panel.The copilots instruments are mounted on thesection in front of the left front seat. See figure7-4 and 7-5.

The pedestal between the two front seatsmounts avionics control heads and essentialsystem switches. See figure 7-6.

The overhead console is centered on the cabinceiling and mounts circuit breakers, electricalsystem switches, and non-essential systemswitches. See figure 7-7.

7-9/7-10

L-L/L L-L

laued lueunJlsul '--L aenB!i

13NVd NOllnVo

©

1i313 3H9J 30VOO

lin

SMll 1VNOII0.v dO

3S1V313 OOUVO SVOol


OIL PRESSURE OIL PRESSUREO) DC GENERATOR RESET DC GENERATOR

Figure 7-5. Caution panel

7-13


AFCS ACTUATOR POSITION

Figure 7-6. Miscellaneous system switches and panels

7-14


Figure 7-7. Overhead panel

7-15

Section 7 412 FLIGHT MANUAL MANUFACTURER'S

PITOT-STATIC SYSTEM

The pitot system consists of electrically heatedpitot tube(s) connected to the airspeedindicator(s) with tubing.

The static system consists of static ports andthe tubing necessary to connect them to theairspeed indicator(s), altimeter(s), and verticalspeed indicator(s). The static ports are justforward of the crew doors. IMC configuredhelicopters are equipped with heated staticports.

HEATING - VENTILATINGSYSTEM

The cabin heating system, which includes thewindshield defrost system, uses bleed air fromthe engine compressor sections as the sourceof heat. A mixing valve which is controlled by athermostat, mixes heated air with outside airto obtain the desired temperature.

When windshield defrost is selected, heatedair is diverted from the door post and pedestalheater outlets to the windshield nozzles.

The ventilating system delivers outside air tonozzles by the instrument panel and also to thewindshield nozzles to defog the windshieldand provide fresh air ventilation. The overheadventilation system delivers outside air throughoverhead nozzles to the crew and passengercompartments.

WINDSHIELD WIPERS

Electrically powered windshield wipers aremounted at the top of both windshields.Selector switches on the overhead consolecontrol the wipers.

CABIN LIGHTS

Two multipurpose utility lights are mountedoverhead in the crew compartment. Either

DATA

white or red light can be selected and the lightmay be adjusted from spot beam to flood typelight. Three dome lights with intensityillumination adjustments are mounted in thepassenger compartment. These dome lightsmay also provide either red or white light. Twolights in the baggage compartment areautomaticially switched on when the door isopened.

FIRE DETECTION - PROTECTIONSYSTEM

A set of heat sensing elements is mounted tothe cowling and forward firewall for eachpower section. A fire or overheat condition willcause the FIRE PULL handle for the affectedpower section to illuminate. A smoke detectoris mounted at the forward end of the baggagecompartment ceiling. Smoke in the baggagecompartment will cause a warning light on theinstrument panel to flash intermittently.

A fire extinguisher bottle for each powersection is mounted in the aft fuselage. Thesebottles are connected in such a way as to alloweither bottle to be discharged onto eitherengine. Pulling the FIRE PULL handle of theaffected power section closes the by-passdoor in the air management system, closes thefuel shut-off valve, and arms both fire bottles.The fire extinguisher selector switch may thenbe used to discharge the fire bottles asselected.

Additionally, two portable fire extinguishersare mounted in the cabin, one on the cabinfloor to the right of the pilots seat, and theother just aft of the forward passenger seat.

AUTOMATIC FLIGHT CONTROLSYSTEM (AFCS)

The dual AFCS System consists of AFCS 1, athree-axis system (pitch, roll, and yaw) andAFCS 2, which has the pitch and roll channels.Each system incorporates independent gyroreference and linear actuators.

7-16

MANUFACTURER'SDATA


The system operates in two basic modes: (1)Stability Augmentation Mode and (2) AttitudeHold Mode. Auto trim is provided in ATT modeto reduce pilot workload in trim. With singleHP operating the auto trim function isinoperative.

INTERCOMMUNICATIONSSYTSTEM

The intercommunications control panel maybe used by the flight crew to select ICS,

COMM 1 or COMM 2 to allow them tocommunicate with each other or with otherradio transceivers.

If the aft intercommunications system isinstalled, the flight crew may communicatewith passengers by selecting AFT INT inresponse to illumination of the AFT INT CALLlights on the instruments panel. Passengersmay also use the aft intercommunicationssystem to communicate with each other, or tomonitor other communication or navigationsystems being used by the flight crew.

7-17/7-18

MANUFACTURER'S 412 FLIGHT MANUALDATA

*TABLE OF CONTENTS

Paragraph

Servicing Data ....................................................................Fuel ..................................................................................Engine Oil ............................ .... ......... ...........................Oil - Approved Oils and Vendors ............................... .......................Transmission Oil.........................................................................90° and 42 ° Gearbox Oil ................................................................Hydraulic Fluid ................................................... .....................Fuel System Servicing ...................................................... ..........Towing..................................................................................Covers and Tiedowns ....................................................................Plug - Engine Inlet......................................................................Cover - Engine Exhaust.................................................................Cover - Pitot Tube ......................................................................Tie Down - Main Rotor .................................................................Tie Down - Tail Rotor ..................................................................

Section 8

PageNumber

8-38-38-38-38-48-58-58-58-58-58-58-58-58-58-5

LIST OF FIGURES

FigureNumber Title

PageNumber

8-68-1 T ow ing .................................................................

8-1/8-2

MANUFACTURER'SDATA


SERVICING DATA OIL - APPROVED OILS AND VENDORS

FUEL

Fuel conforming to PWA 522 or the followingmilitary and commercial specifications areapproved for use in PT6T-3B engines.

NOTE

ASTM D-1655, Jet A, Jet A-1, Jet B, MIL-T-5624, JP-4, JP-5, NATO F-40, NATO F-44,D.E.R.D. 2454, or D.E.R.D. 2452.

This list of approved engine oils wasupdated by Pratt and Whitney EngineService Bulletin No. 5001, Rev. 10.

The term engine includes the combining gearbox. The same oil shall be used in all powerplant components due to oil seal leakage.

Refer to fuel limitations in Section 2.

ENGINE OIL

Oil conforming to the following listed militaryand commercial specifications are approvedfor use in PT6T-3B engines.

PWA 521, MIL-L-7808E, (and subsequent),MIL-L-23699, NATO 0-148, and NATO 0-156.

Engine accessory - 6.4 quarts (6 liters)gearbox (each)

Combining gearbox - 5 quarts (4.7 liters)

NOTE

Type and brand of oil must be enteredin aircraft and engine log books toprevent inadvertent mixing of oils.

MIL-7808E AND SUBS.. NATO 0-148, ANDPWA 521, TYPE 1 (3 centistokes) for use at allambient temperatures.

CAUTION

DO NOT MIX BRANDS OR TYPES OFOIL. SHOULD OILS BECOMEMIXED, DRAIN AND FLUSHSYSTEM AND REFILL.

Stauffer Jet I Stauffer Chemical Co.299 Park Ave.New York, N.Y. 10017

BP Aero Turbine BP (North America) Ltd,Oil 15 620 Fifth Avenue

New York, N.Y. 10020

BP Oil Limited1245 Sherbrooks St. WestMontreal,Quebec H3G1G7

8-3


Mobil Oil Corp.150 East 42nd St.New York, N.Y. 10017

Esso Turbo Oil2389

Exxon International Co.1251 Ave. of AmericasNew York, N.Y. 10020

Mobil Jet Oil IIMobil RM254A

Imperial Oil Ltd.111 St. Clair Ave. WestToronto, Ont. M5W 1 K3

Stauffer Jet II Stauffer Chemical Co.299 Park Ave.New York, N.Y. 10017

Exxon Turbo Oil2389

Mobil Avrex STurbo 256

Exxon Co.. U.S.A.P.O. Box 2180Houston, Texas 77001

Mobil Oil Corp.150 East 42nd StreetNew York, N.Y. 10017

Castrol 5000 Castrol Oil Canada Ltd.P.O. Box 3New Toronto Postal StationToronto, Ontario M8W 1 P2

MIL-L-23699, NATO 0-156, and PWA 521,TYPE II (5 centistokes) for use above -40°C(-40°F) only.

CAUTION

Monsanto Monsanto Co.Skylube 450 800 N. Lindbergh Bldg.

St. Louis, Missouri 63166

Chevron Jet Chevron InternationalEngine Oil 5 Oil Co., Inc.

555 Market St.San Francisco, CA 94120

BP Enerjet 51

DO NOT MIX BRANDS OR TYPES OFOIL. SHOULD OILS BECOMEMIXED, DRAIN AND FLUSH THESYSTEM AND REFILL.

Esso Turbo Oil2380

Exxon International Co.1251 Ave. of AmericasNew York, N.Y. 10020

BP (North America) Ltd.620 Fifth AvenueNew York, N.Y. 10020

BP Oil Limited1245 Sherbrooke St. W.Montreal,Quebec H3G 1G7

Royal Lubricants Co., Inc.P.O: Box 298East Hanover, N.J. 07926

Shell InternationalPetroleum Co.Shell CentreLondon, England 7 NA

Imperial Oil Ltd.111 St. Clair Ave. W.Toronto,Ontario, M5W 1 K3

Royco TurbineOil 555

Aero ShellTurbine Oil 555

Exxon Turbo Oil2380

Aero ShellTurbine Oil 500

Exxon Co., U.S.A.P.O. Box 2180Houston, Texas, 77001

Shell Oil CompanyOne Shell PlazaP.O. Box 2463Houston, Texas 77001

Shell Canada Ltd.505 University Ave.Toronto, Ontario M5G 1X4

TRANSMISSION OIL

Oils conforming to MIL-L-7808E andsubsequent, NATO 0-148, MIL-L-23699,NATO 0-156. and also Aero Shell Turbine Oil555, or Royco Turbine Oil 555, are approvedfor use in the transmission. Oils conforming toMIL-L-7808E end NATO 0-148 may be usedat all ambient temperatures. Aero Shell

Reservoir capacity - 5.3 pints (2.5 liters).(each)

FUEL SYSTEM SERVICING

The fuel system contains five interconnectedcrashworthy fuel cells which are servicedthrough a single filler port on the right side ofthe aft fuselage. The capacity of these cells is211 U.S. gallons (1400 pounds at 15°C).

NOTE

If fueling to a total of less than 600pounds, open interconnect valve priorto fueling. Close interconnect valveprior to engine start.

<MANUFACTURER'S 412 FLIGHT MANUAL Section 8

DATA

Turbine Oil 555. Royco Turbine Oil 555, andoils conforming to MIL-L-23699, and NATO

0-156, may only be used at ambienttemperatures above -22°F (-30°C).

NOTE

Do not mix brands of oil.

TOWING

The helicopter may be towed at walkingspeeds for very short distances using groundhandling wheels and a standard tow bar. Referto figure 8-1.

COVERS AND TIEDOWNS

90 ° AND 42 ° GEARBOX OIL

Oils conforming to MIL-L-7808E and sub-sequent and NATO 0-148 may be used at anyambient temperatures in the 90° gearbox andthe 42 ° gearbox.

Protective covers and tiedowns are furnishedas loose equipment and are used for parkingthe helicopter. Additional equipment such asropes, cables, clevises, ramp tiedown or deadman tiedowns will be required during mooring.

PLUG-ENGINE INLETAero Shell 555 or Royco Turbine Oil 555, andoils conforming to MIL-L-23699 and NATO 0-156 may be used in the 90 ° gearbox and 42 °

gearbox at ambient temperatures above -22°F(-30°C).

NOTE

Do not mix types or brands of oils.

HYDRAULIC FLUID

Hydraulic fluid conforming to MIL-H-5606 isapproved for use in the hydraulic systems.

The engine inlet plugs are foam covered withcloth. Each plug is attached with a redstreamer stenciled in white letters REMOVEBEFORE FLIGHT. Press inlet plugs in engineair inlet.

COVER - ENGINE EXHAUST

The engine exhaust cover is installed on eachtail pipe and tied with a nylon cord in the cover.Each cover has a streamer on each sidestenciled in white letters REMOVE BEFOREFLIGHT.

COVER - PITOT TUBE

The pitot tube covers are flame resistant andare attached with a red streamer stenciled inwhite letters REMOVE BEFORE FLIGHT.Cover pitot tubes and tie cord to secure to pitottubes.

TIE DOWN - MAIN ROTOR

Tiedown main rotor blades whenever any of thefollowing conditions exist:

Thunderstorms are in the local area orforecasted.

Winds in excess of 20 knots or a gust spread of15 knots exists or is forecasted.

Rev. 3 8-5

Section 8 412 FLIGHT MANUAL MANUFACTURER'S

Helicopter is parked within 150 feet ofhovering or taxiing aircraft that are in excessof 11,600 pounds gross weight.

Helicopter to be parked overnight.

The main rotor tiedowns are socks which fit overthe end of each blade with cords which attach tomooring points on the fuselage. The tiedowncords are manufactured to specified lengths forforward and aft mooring points, as identified bystreamers adjacent to the brass rings to whichthe snap hooks attach.

DATA

When secure, the tiedowns should be free ofslack or under slight tension, but not undersufficient tension to flex the main rotor bladesappreciably. The cords should never beshortened from their design lengths, asexcessive loads could be induced in the mainrotor yokes.

TIE DOWN - TAIL ROTOR

The tail rotor tie down is a strap which is usedto secure the tail rotor blade to the vertical fin.

0

1. Tow bar2. Tow ring3. Ground handling wheels 0

412900-4AFigure 8-1. Towing

8-6 Rev. 3

MANUFACTURER'SDATA


LIST OF TABLES

TableNumber Title

9-1 Celsius to Fahrenheit Conversion ............................................9-2 Gallons to Liters Conversion .................................................9-3 Inches to Millimeters Conversion.............................................9-4 Feet to Meters Conversion ...................................................9-5 Pounds to Kilograms Conversion .............................................9-6 Velocity Conversion .........................................................9-7 Standard Atmosphere .......................................................

PageNumber

9-49-59-69-69-79-89-9

9-1/9-2

MANUFACTURER'SDATA

0 Sektiti 9


CONVERSION TABLES

The tables contained on the following pagesare intended to provide useful information thatis normally located in various and numerous

other sources. The prime intent of furnishingthis data is to assist in flight planning,operations, and for purposes other than flight,transposing available information to the typedesired.

9-3


Table 9-1. Celsius to fahrenheit conversion

CELSIUS - FAHRENHEITCONVERSION TABLE

C

-62.2-66.7-61.1-46.6-40.0-34.4-31.7-28.9-26.1-23.3-20.6-17.8-15.0-12.2- 9.4- 6.7- 3.9- 1.1

1.74.47.2

10.012.815.618.321.123.926.729.432.236.037.840.643.346.148.951.754.457.260.052.866.658.3

C F C

-80 -112.0 71.1-70 - 94.0 73.9-60 - 76.0 76.7-60 - 68.0 79.4-40 - 40.0 82.2-30 - 22.0 85.0-26 - 13.0 87.8-20 - 4.0 90.6-16 + 5.0 93.3-10 14.0 96.1- 5 23.0 98.9

0 32.0 101.75 41.0 104.4

10 50.0 107.216 69.0 110.020 58.0 112.825 77.0 115.630 85.0 118.336 95.0 121.140 104.0 126.745 113.0 132.260 122.0 137.856 131.0 143.360 140.0 148.965 149.0 154.4

C F C

160 320.0 260.0

MANUFACTURER'SDATA


Table 9-2. Gallons to liters conversion

GALLONS - LITERS CONVERSION TABLE

U.S IMPERIALGALLON GALLON LITER

10

20

30

40

60

60

70

80

90

100

110

120

130

140

160

160

8.33 37.85

16.66 76.71

24.98 113.56

33.31 151.42

41.63 189.27

49.96 227.13

58.28 264.98

66.61 302.83

74.94 340.69

83.26 378.54

91.59 416.35

99.92 454.20

108.24 492.05

116.57 529.90

124.90 567.75

133.22 605.60

U.S. IMPERIALGALLON GALLON LITER

170 141.55 643.45

180 149.86 681.30

190 158.20 719.16

200 166.52 757.18

210 174.84 795.03

220 183.18 832.89

230 191.50 870.74

240 199.84 908.60

250 208.14 946.45

260 216.48 984.45

270 224.82 1022.16

280 233.14 1060.01

290 241.66 1097.87

300 249.80 1135.62

310 258.12 1173.47

320 266.44 1211.33

0

0 412900-46

9-5


Table 9-3. Inches to millimeters conversion

INCHES TO MILLIMETERSCONVERSION TABLE

2 3 4 5 6 7 8

mm mm mm mm mm mm mm

0 1Inches

mm mm

0 --- 25.4

10 254.0 279.4

20 508.0 533.4

30 762.0 787.4

40 1016.0 1041.4

50 1270.0 1295.4

60 1524.0 1649.4

70 1778.0 1803.4

80 2032.0 2057.4

90 2286.0 2311.4

100 2640.0 2565.4

50.8 76.2 101.6 127.0 152.4

304.8 330.2 365.6 381.0 406.4

558.8 584.2 609.6 636.0 660.4

812.8 838.2 863.6 889.0 914.4

1066.8 1092.2 1117.6 1143.0 1168.4

1320.8 1346.2 1371.6 1397.0 1422.4

1674.8 1600.2 1625.6 1651.0 1676.4

1828.8 1854.2 1879.6 1905.0 1930.4

2082.8 2108.2 2133.6 2159.0 2184.4

2336.8 2362.2 2387.6 2413.0 2438.4

2590.8 2616.2 2641.6 2667.0 2692.4

177.8

431.8

686.8

939.8

1193.8

1447.8

1701.8

1955.8

2209.8

2463.8

2717.8

203.2

457.2

711.2

965.2

1219.2

1473.2

1727.2

1981.2

2236.2

2489.2

2743.2

mm

228.6

482.6

736.6

990.6

1244.6

1498.6

1752.6

2006.6

2260.6

2614.6

2768.6

222900-6B

Table 9-4. Feet to meters conversion

FEET TO METERSCONVERSION TABLE

0 1 2 3 4 5 6Feet Meter Mete rs Meter s Meter s Mete rs Meter s Mete rs

0 ------ 0.305 0.610 0.914 1.219 1.524 1.829

10 3.048 3.363 3.668 3.962 4.267 4.672 4.877

20 6.096 6.401 6.706 7.010 7.315 7.620 7.926

30 9.144 9.449 9.763 10.068 10.363 10.668 10.972

40 12.192 12.496 12.801 13.106 13.411 13.716 14.020

50 16.230 16.544 15.849 16.164 16.459 16.763 17.068

60 18.287 18.592 18.897 19.202 19.607 19.811 20.116

70 21.335 21.640 21.946 22.260 22.665 22.859 23.164

80 24.383 24.688 24.993 26.298 26.602 25.907 26.212

90 27.431 27.736 28.041 28.346 28.651 28.955 29.260

100 30.479 30.784 31.089 31.394 31.698 32.003 32.308

7

Meters

2.134

5.182

8.229

11.277

14.326

17.373

20.421

23.469

26.617

29.666

32.613

8 9

Meters Meters

2.438 2.743

5.486 6.791

8.634 8.839

11.682 11.887

14.630 14.936

17.678 17.983

20.726 21.031

23.774 24.070

26.822 27.126

29.870 30.174

32.918 33.222

L206900-53B

9-6

MANUFACTURER'SDATA


Table 9-5. Pounds to kilogram conversion

POUNDS TO KILOGRAMSCONVERSION TABLE

0Pounds Kilo-

gramKilo-grams

1 2 3 4 5 6 7

Kilo- Kilo- Kilo- Kilo- Kilo- Kilo- Kilo-grams grams grams grams grams grams grams

0

10

20

30

40

50

60

70

80

90

100

4.536

9.072

13.608

18.144

22.680

27.216

31.751

36.287

40.823

45.359

0.454 0.907

4.990 5.443

9.525 9.979

14.061 14.515

18.597 19.051

23.133 23.687

27.669 28.123

32.205 32.659

36.741 37.195

41.277 41.730

45.813 46.266

1.361

6.897

10.433

14.969

19.504

24.040

28.576

33.112

37.648

42.184

46.720

1.814 2.268

6.360 6.804

10.886 11.340

15.422 15.876

19.958 20.412

24.494 24.948

29.030 29.484

33.566 34.019

38.102 38.555

42.638 43.091

47.174 47.627

2.722

7.257

11.793

16.329

20.865

25.401

29.937

34.473

39.009

43.545

48.081

3.175

7.711

12.247

16.783

21.319

25.865

30.391

34.927

39.463

43.998

48.534

8

Kilo-grams

3.629

8.165

12.701

17.237

21.722

26.308

30.844

35.380

39.916

44.453

48.988

9

Kilo-grams

4.082

8.618

13.154

17.690

22.226

26.762

31.298

35.834

40.370

44.906

49.442

L206900-54A

9-7


Table 9-6. Velocity conversion

VELOCITY CONVERSION TABLE

KNOTS MPH km/HR METERS/SEC

5101520253035404550556065707580859095

100105110115120125130135140145150

5.811.517.323.028.834.540.346.051.857.563.369.074.880.686.392.197.8

103.6109.3115.1120.8126.6132.3138.1143.8149.6155.4161.1166.9172.6

9.318.527.837.046.355.664.874.183.392.6

101.9111.1120.4129.6138.9148.1157.4166.7175.9185.2194.4203.7213.0222.2231.5240.7250.0259.3268.5277.8

2.65.17.7

10.312.915.418.020.623.125.728.330.933.436.038.641.243.746.348.951.454.056.669.261.764.366.969.472.074.677.2222900-2A

9-8

MANUFACTURER'SDATA


Table 9-7. Standard atmosphere

STANDARD S L CONDITIONS: CONVERSION FACTORS:TEMPERATURE 15°C (59°F) 1 IN. Hg 70.727 LB/SQ FTPRESSURE 29.921 IN. Hg 2116.216 LB/SQ FT 1 IN. Hg 0.49116 LB/SQ IN.DENSITY 0.0023769 SLUGS/CU FT 1 KNOT 1.151 M.P.H.SPEED OF SOUND 1116.89 FT/SEC 661.7 KNOTS 1 KNOT 1.688 FT/SECALTITUDE DENSITY -1/2 TEMPERATURE SPEED OF PRESSURE PRESSURE

FEET RATIO -F SOUND IN. Hg RATIO0 KNOTS0 1.0000 1.0000 15.000 59.000 661.7 29.921 1.0000

1000 0.9711 1.0148 13.019 55.434 659.5 28.856 0.96442000 0 9428 1.0299 11.038 51.868 657.2 27.821 0.92983000 0.9151 1.0454 9.056 48.302 654.9 26.817 0.89624000 0.8881 1.0611 7.076 44.735 652.6 25.842 0.86375000 0.8617 1.0773 5.094 41.169 650.3 24.896 0.8320

6000 0.8359 1.0938 3.113 37.603 648.7 23.978 0.80147000 0.8106 1.1107 1.132 34.037 645.6 23.088 0.77168000 0.7860 1.1279 -0.850 30.471 643.3 22.225 0.74289000 0.7620 1.1456 -2.831 26.905 640.9 21.388 0.7148

10.000 0.7385 1.1637 -4.812 23.338 638.6 20.577 0.6877

11,000 0.7155 1.1822 .6.793 19.772 636.2 19.791 0.661412.000 0.6932 1.2011 -8.774 16.206 633.9 19.029 0.636013,000 0.6713 1.2205 -10.756 12 640 631.5 18.292 0.611314,000 0.6500 1.2403 .12.737 9.074 629.0 17.577 0.587515.000 0.6292 1.2606 -14.718 5.508 626.6 16.886 0.5643

16,000 0.6090 1.2815 -16.699 1.941 624.2 16.216 0.542017,000 0.5892 1.3028 -18.680 -1.625 621.8 15.569 0.520318,000 0.5699 1.3246 -20.662 -5.191 619.4 14.942 0.499419.000 0.5511 1.3470 -22.643 -8.757 617.0 14.336 0.479120.000 0.5328 1.3700 -24.624 -12.323 614.6 13.750 0.4595

21.000 0.5150 1.3935 -26.605 -15.899 612.1 13.184 0.440622.000 04976 1.4176 -28.587 -19.456 609.6 12.636 0.422323.000 0.4806 1.4424 -30.568 -23.022 607.1 12.107 0.404624.000 0.4642 1.4678 -22.549 -26.588 604.6 11.597 0.387425.000 0.4481 1.4938 -34.530 -30.154 602.1 11.103 0.3711

L206900-45B

9-9/9-10

MANUFACTURER'SDATA


OPTIONAL EQUIPMENT optional equipment listed in this sectionrequires a Flight Manual Supplement.

FLIGHT MANUAL SUPPLEMENTS RE-QUIRED WHEN OPTIONAL EQUIPMENTITEMS ARE INSTALLED.

The following items may be installed on thebasic helicopter by authorized personnel. The

NAME OFEQUIPMENT

BHT-412-FMS-CAA-1Winterization Heater

BHT-412-FMS-CAA-2Emergency Floats

BHT-412-FMS-CAA-3Heated Windshield

BHT-412-FMS-CAA-4Auxiliary Fuel

BHT-412-FMS-CAA-5Group A Operations

BHT-412-FMS-CAA-6Flight Director

BHT-412-FMS-CAA-7Internal Hoist

BHT-412-FMS-CAA-8Litter Kit

BHT-412-FMS-CAA-9External Cargo

Operation

KIT NUMBER

212-706-008

412-706-004

412-706-010

412-706-007

412-706-111

214-706-003

412-706-006

212-706-103

DATE CAACERTIFIED

Oct. 20. 1981

Oct. 20, 1981

Oct. 20. 1981

Oct. 20, 1981

Oct. 20, 1981

Oct. 20, 1981

Jan. 29, 1982

Jan. 29. 1982

Oct. 20, 1981

CURRENT REVISION

10-1

SSection 10 412 FLIGHT MANUAL MANUFAC'

Table 10-1. Approved supplements

This table provides a list of Agencies that have approved Flight Manual Supplements for the

optional equipment or type of Operation listed.

APPROVING AGENCYPUBLICATION

FAA DOT DOT CAA CTA DGAC JCAB LBA(USA) (CAN.) (AUS.) (U.K.) (BRAZIL) FRANCE) (JAPAN) (GER.)

412 FLIGHT MANUAL X X2 X3 X X3 X'

212 -706-008WINTERIZATION X X X ' X X4 X X

HEATER

412-706-004 X

EMERGENCY FLOATS

412-706-010HEATED WINDSHIELD X

412-706-007 X X3

X' X' X' X'

AUXILIARY FUEL

CATEGORY AX

GROUP A

412-706-111 X X' X' X' X' X'FLIGHT DIRECTOR

214-706-003 X4

INTERNAL HOIST

412-706-006 X X' X' X X' X'LITTER KIT

212-706-103 XEXTERNAL CARGO X

212-899-333NIGHTSUN XSEARCHLIGHT

1. FAA Approved publication accepted.2. FAA Approved publication approved with addendum.3. FAA Approved publication approved with supplement.4. FAA Approved publication accepted with appropriate signature page.

TURER'SDATA

412100-22

0

10-2

BHT-41 2-FMS-CAA-1

FLIGHT MANUAL

SUPPLEMENT FORWINTERIZATION HEATER OPERATIONS

(212-706-008)

CERTIFIEDOCTOBER 20, 1981

This supplement shall be attached to the CAA Model 412 RightManual when the 212-706-008 Winterization Heater has beeninstalled.

The information contained herein supplements the information ofthe basic Flight Manual; for Limitations. Procedures andPerformance Data not contained in this supplement, consult thebasic Flight Manual.

Bell Helicopter II :i I 7 .lIA Subsidiary of Textron Inc

POST OFFICE BOX 4u2 FORT WORTH. TEXAS 76101

Log of Pages 412 FLIGHT MANUAL CAA APPROVEDSUPPLEMENT

WINTERIZATION HEATER

LOG OF PAGES

Original ..... 0......... October 20, 1981

RevisionNo.Page

RevisionNo.Page

Title ................................ 0A ................................... 0i/ ii .................................. 01 - 1 8 .............................. 0

APPROVED: October 20. 1981

for:

APPROVED:

CHIEF

CIVIL AVIATION AUTHORITYAIRWORTHINESS DIVISIONBRABAZON HOUSEREDHILLSURREY. ENGLAND


CAA APPROVEDSUPPLEMENT

412 FLIGHT MANUAL Introduction


INTRODUCTION

The Winterization Heater kit is installed to provideincreased cabin heating capacity. The kit basicallyconsists of a larger mixing valve, a larger noisesuppressor, extra outlets, ducts, and hardwarenecessary for installation. Operation of theWinterization Heater is identical to the basic heater.




NOTEThe contents of this supplement shallbe used in conjunction with the basicflight manual for helicoptersequipped with Winterization HeaterKit.

WEIGHT/CG LIMITATIONS

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

Section 2


Section 2

412 FLIGHT MANUAL CAA APPROVEDSUPPLEMENT

PRESTART CHECK

Battery switch - ON.

Heater circuit breaker switch - In.

Heater switch - ON.

Check "Heater Air Line" light illuminates.

Heater switch - OFF.

Heater switch - ON.

Increase thermostat setting and observeheated air-flow.

Return thermostat to full cold and observeheater airflow shut off. If heater airflowshutoff is observed, reset thermostat todesired temperature if heater operation isdesired.

HEATER OPERATION CHECK

Operation check may be accomplished atthis time or at any time heater operation isdesired.

100% (N11) rpm and at least 75% N1 on bothengines.

Thermostat - Full cold.

WARNING

TURN HEATER OFF WHEN:

1. THE HEATER AIRFLOWDOES NOT SHUT OFF WHENTHERMOSTAT IS TURNEDTO FULL COLD.

2. THE "HEATER AIR LINE"LIGHT ILLUMINATES.

3. THE HEATER CIRCUITBREAKER TRIPS.

NOTE

If heater is on for takeoff, refer toappropriate performance chart inSection IV.

DO NOT OPERATE HEATERABOVE 21 C OAT.


412 FLIGHT MANUAL Sections 3 & 4


No change

Figures 4-1 through 4-3 present performancewith Winterization Kit on.

Refer to figure 4-1 for out-of-ground-effect,maximum continuous power, hoverperformance. For all others, refer to basicFlight Manual - heater on charts.

Refer to figure 4-2 for takeoff performance.

Refer to figure 4-3 for climb performance.

3

14,000 FT. DEN. ALT.

Section 4 412 FLIGHT MANUAL CAA APPROVEDSUPPLEMENT


HOVER HOVERING CEILING

OUT-OF-GROUND EFFECT

MAXIMUM CONTINUOUS POWER SKID HEIGHT 60 FEETENGINE RPM 100% WINTERIZATION HEATER ONGENERATOR 150 AMPS (EA) -30 TO 20°C

-30-20-10 0 10 20 8 9 10 11 12

OAT - °C GROSS WEIGHT - LBS x 1000

Figure 4-1. 412900-35B

MIN.OAT




TAKEOFF TAKE-OFF DISTANCEOVER 50 FT. OBSTACLE

INITIATED FROM 4 FT SKID HEIGHTWINTERIZATION HEATER ON

45 KIAS AT ROTATION

-40-20 0 20 200 400 600 800 1000 1200TAKE-OFF DISTANCE - FEET

ENGLISH

Figure 4-2. (Sheet 1 of 2) 412900-36-1B

5



TAKEOFF TAKEOFF DISTANCE

OVER 15m OBSTACLE

HOVER POWER + 15% TORQUE INITIATED FROM 1.3m SKID HEIGHTENGINE RPM 100% WINTERIZATION HEATER ONGENERATOR 150 AMPS (EA.) 45 KIAS AT ROTATION

-40-20 0 20 100 150 200 250 300OAT - °C TAKEOFF DISTANCE - METERS

METRIC

412900-68

Figure 4-2. (Sheet 2 of 2)

CLIMB

20,000

18,000

16,000

WINTERIZATION HEATER ON




LIMIT


TAKE-OFF POWER 65 KCASENGINE RPM 100% WINTERIZATION HEATER ONGENERATOR 150 AMPS (EA.)

GROSS WEIGHT 7000 LB. (3175.2 kg)

-6000

-5500

-5000

-4500w

-4000

-3500

-3000

-2500w

-2000

-1500

-1000

-500

0 400 800 1200 1600 2000 2400 2800 3200


7

20,000

18.000

16,000

14.000

12,000

8.000

6.000

4,000

2,000

0

Section 4


CLIMB (Cont)





-6000

-5500

-5000

-1000

-500WINTERIZATION HEATER ON

0 400 800 1200 1600 2000 2400 2800 3200

RATE OF CLIMB - FT/MIN (m/s) 412900-36-9C


20,000

18,000

16,000

-14,000

u



CLIMB (Cont)

TAK


-500

400 800 1200 1600 2000 2400 2800 3200

(2) (4) (6) (8) (10) (12) (14) (16)


9

20,000

18.000

16,000

14,000

.

12,000


CLIMB (Cont)




Figure 4-3. (Sheet4of 12)

20,000

18,000

16,000 -

14,000I-

12,000U

10,000

8.000

6,000

4,000

2,000

00 400




CLIMB (Cont)

E


AKE-OFF POWER 65 KCASNGINE RPM 100% WINTERIZATION HEATER ON

GROSS WEIGHT 11,000 LB. (4989.6 kg)

-6000

-5500

-5000

u

-4000

LU.-3500

-500



11

20,000

18,000

16,000OAT

-6000

-5500

-5000

-4500

-4000

-3500

-3000

-2500

-2000

-1500

200

(1)

20,00

18,00

16,000


TWIN ENGINE RATE OF CLIMBMAXIMUM CONTINUOUS POWER 65 KCASENGINE RPM 100% WINTERIZATION HEATER ONGENERATOR 150 AMPS (EA.)



13



CLIMB (Cont)


MAXIMUM CONTINUOUS POWER 65 KCASENGINE RPM 100% WINTERIZATION HEATER ONGENERATOR 160 AMPS (EA.)

GROSS WEIGHT 8000 LB. (3628.8 kg).

-1500

4000

2000 -500

00 400 800 1200 1600 2000 2400 2800 3200






CL


ENGINE RPM 100% WINTERIZATION HEATER ON


-1500

I

4,000

2,000

0

-1000

-500

200 400 600 800 1000 1200 1400 1600

(1) (2) (3) (4) (5) (6) (7) (8)RATE OF CLIMB - FT/MIN (m/s) 412900-36-4C


15



CLIMB (Cont)TWIN ENGINE RATE OF CLIMB


UJ LU



CLIMB (Cont




16000



GROSS WEIGHT 11,000 LB. (4989.6 kg)

-5500

-5000

-1500

-1000

-500

4,000

2,000

0

WINTERIZATION HEATER ON

0 200 400 600 800 1000 1200 1400 1600



17



CLIMB (Cont)



GROSS WEIGHT 11,600 LB. (5261.8 kg)20,000

-6000

18,000 -5500

-600016,000

6,000

-1500

4,000WINTERIZATION HEATER ON -1000

2.000



BHT-412-FMS-CAA-2

SUPPLEMENT FOREMERGENCY FLOAT KIT

(412-706-004)


supplement consult the basic Flight Manual.


EMERGENCY FLOAT KIT

LOG OF PAGES

Original..... ........ October 20, 1981

RevisionNo.

RevisionNo .Page

Title ...........................A.............................1 - 4 ...................

APPROVED:

Page

000

October 20, 1981

APPROVED:

CHIEF

CIVIL AVIATION AUTHORITYAIRWORTHINESS DIVISIONBRABAZON HOUSEREDHILLSURREY, ENGLAND




EMERGENCY FLOAT KIT


Autorotation = 105 knots to 10,000 feet

80 knots above 10,000feet

Inflation of Emergency Float Kit duringforward flight is prohibited. Forward flightafter inflation of Emergency Float Kit isprohibited.

SEVERE NOSE UP PITCHINGWILL OCCUR IF THEEMERGENCY FLOAT KIT ISINFLATED IN FORWARDFLIGHT OR DESCENT.REFER TO INADVERTENTEMERGENCY FLOAT KITINFLATION IN FLIGHT,SECTION 3, OF THISSUPPLEMENT.

Maximum forward speed for ditching is 33knots in calm water, and 15 knots in roughwater, with lowest possible sink rate uponwater contact. Flight operations withEmergency Float Kit inflated are not intended.

ALTITUDE LIMITATIONS

Maximum pressure altitude for inflation ofEmergency FloatKitis 1000feet. Helicopteroperation above 10,000 feet is permittedprovided the FLOATS switch is in the OFFposition, and FLOATS caution light isextinguished.

Inflation of Emergency Float Kit above 5,000feet and below 10,000 feet pressure altituderequires different pressure limits for nitrogenbottle. Refer to Section 2., EXTERIORINSPECTION, of this supplement.

CENTER OF GRAVITY

The Emergency Float Kit does NOTchange the CG limits of the helicopter.

TYPES OF OPERATION

The Emergency Float Kit is installed forassistance during emergency ditching, and isapproved for VFR and IFR operation.

It is mandatory to have the FLOATS switchOFF and FLOATS caution light extinguishedwhen operating over land.

It is mandatory to have the EmergencyFloat Kit safety pin removed prior to flightover water.

WARNING

CREW AND PASSENGERDOORS SHALL REMAINCLOSED DURING DITCHING.

1

Sections 1 & 2 412 FLIGHT MANUAL CAA APPROVEDSUPPLEMENT

EMERGENCY FLOAT KIT

PLACARDS

FLOAT INFLATION OR OPERATION INFORWARD FLIGHT IS PROHIBITED

(Located above pilot airspeed indicator.)

REMOVE BEFORE FLIGHT

(Located on nitrogen bottle.)

REDUCE FILL PRESSURE 100 PSIPER 1,000 FEET ABOVE S.L.

(Located on nitrogen bottle.)

EXTERIOR INSPECTION

Emergency Float Kit - Stowed.

Emergency Float Kit, covers andsupports - Clean and secured.

Nitrogen bottle - Secured and pressurewithin allowable limits for ambienttemperature as shown on chart decal,located by nitrogen bottle.

NOTE

Ascertain Emergency Float Kit hashad periodic inflation and inspection.

Emergency Float Kit safety pin -Remove for over water flight.

BEFORE TAKEOFF - OVERWATER OPERATION

Passenger step - Retracted.

EMER INFLATION - PULL handle -Down and safetied.

FLOATS switch - ARMED.

FLOATS caution light - Illuminated(amber).

NOTE

It is advisable to have FLOATSswitch - ARMED, FLOATS cautionlight - Illuminated (amber) duringtakeoff and landing. FLOATSswitch - OFF and FLOATS cautionlight extinguished when operatingover land or reaching safe altitude.

BEFORE LANDING - OVERWATER OPERATION


FLOATS caution light - Illuminated(amber).

BEFORE LEAVING THEHELICOPTER

Emergency Float Kit safety pin - Install.

CAA APPROVED 412 FLIGHT MANUAL Section 3SUPPLEMENT

EMERGENCY FLOAT KIT

Section 3

INADVERTENT EMERGENCYFLOAT KIT INFLATION IN FLIGHT

In event of unintended inflation, reduce WHEN THE EMERGENCY FLOATairspeed, adjust sink rate to 200 fpm or less, KIT IS INFLATED, EGRESSand land immediately. THROUGH CREW DOORS MAY

BE ACCOMPLISHED BYJETTISONING THE CREWDOORS. PASSENGER EGRESSIS ACCOMPLISHED THROUGHEMERGENCY - OVER WATER WINDOWS, MARKED,EMERGENCY PUSH HERE,

Establish an autorotative glide speed LOCATED IN REAR DOORS.of 65 to 70 knots for all gross weights.

NOTEAt 100 feet altitude execute a moderatecyclic flare to reduce airspeed. Adjust Further flight after a water landingcollective and cyclic pitch sufficient to is prohibited.perform a touchdown with nose up attitudeand a water speed as low as possible. ELECTRICAL ACTUATION MODE


WARNING FLOATS caution light - Illuminated(amber).

MANUAL ACTUATION MODE

IF THE EMERGENCY FLOAT EMER INFLATION - PULL handle - Pull.KIT DOES NOT OPERATEIMMEDIATELY UPON WATER EMERGENCY - WATERCONTACT PULL EMER LANDING (AUTOROTATION)INFLATION - PULL HANDLE. WITH ELECTRICAL FAILURE

Establish an autorotative glide speed of 65to 70 knots for all gross weights.

After water landing, inspect for damageand determine if helicopter should be At 100 feet altitude execute a moderateabandoned. cyclic flare to reduce airspeed. Adjust

3

Sections 3, 4, & 5 412 FLIGHT MANUAL CAA APPROVEDSUPPLEMENT

EMERGENCY FLOAT KIT

collective and cyclic pitch sufficient to ELECTRICAL FAILUREperform a touchdown with nose up attitudeand a water speed as low as possible.Pull the EMER INFLATION - PULL If the FLOATS caution light illuminateshandle when water contact is imminent. with FLOATS switch OFF - Pull circuit

breaker.After water landing, inspect for damageand determine if helicopter should be If the FLOATS caution light remainsabandoned. illuminated after pulling circuit breaker -

Land as soon as practical.WARNING

Inflation may be made manually by pulling theWHEN THE EMERGENCY FLOAT EMER INFLATION - PULL handle.KIT IS INFLATED, EGRESSTHROUGH CREW DOORS MAYBE ACCOMPLISHED BY Certification of the EmergencyJETTISONING THE CREW Floats Kit is based on both theDOORS. PASSENGER EGRESS electrical and manual systemIS ACCOMPLISHED THROUGH operating.WINDOWS. MARKED.EMERGENCY PUSH HERE FAILURE TO INFLATE AFTERLOCATED IN REAR DOORS. WATER CONTACT WITH FLOATS

SWITCH IN ARMED POSITIONNOTE

Further flight after a water landing Pull the EMER INFLATION - PULLis prohibited. handle to inflate the Emergency Float Kit.

Section 4

No Change.

Section 5

No Change.

4

BHT-412-FMS-CAA-3

MODEL 412

FLIGHT MANUAL

SUPPLEMENT FORHEATED WINDSHIELD

(412-706-010)


This supplement shall be attached to the CAA Model 412Flight Manual when the 412-706-010 Heated Windshieldhas been installed.

The information contained herein supplements theinformation of the basic Flight Manual; for Limitations,Procedures, and Performance Data not contained in thissupplement, consult the basic Flight Manual.

Bell HelicopterA Subsidiary of Textron Inc

POST OFFICE BOX 482 · FORT WORTH, TEXAS 76101


HEATED WINDSHIELD

LOG OF PAGES

Original .............. October 20, 1981

RevisionNo.Page

RevisionNo.Page

Title ................................ 0A ................................... 01 - 3/4 ............................ 0

APPROVED: October 20, 1981

APPROVED:

CHIEF




1


HEATED WINDSHIELD

PLACARDS AND DECALS

CAUTION

STAND-BY COMPASS UNRELIABLEWITH WINDSHIELD HEAT ON.

WSHLD HEAT

LH RH

INDICATOR

ON

HOT

ON

HOT

GREEN

YELLOW

1


HEATED WINDSHIELD

ENGINE PRE-START CHECK

WSHLD HEAT LH - OFF.

WSHLD HEAT RH - OFF.

WINDSHIELD HEAT circuit breakers - In.

Batteries - ON.

WINDSHIELD HEAT Segment - PRESSTO TEST.

- Both "ON" lights illuminated(green).

- Both "HOT" lights illuminated(yellow).

NOTE

The bright or dim intensity of theheated windshield lights is controlledby the MASTER CAUTION PANELBRT/DIM switch. During daylightoperations, place MASTERCAUTION BRT/DIM switch in BRTposition.

BEFORE TAKE-OFF

WSHLD HEAT LH - ON (if desired)left-hand segment illuminates ON (green).

WSHLD HEAT RH - ON (if desired)right-hand segment illuminates ON (green).

NOTE

The ON (green) left-hand and right-hand windshield heat segments willilluminate and extinguish as thewindshield heat cycle occurs.



HEATED WINDSHIELD

3

DC GENERATOR FAILURE

NON ESS BUS - MANUAL.

NOTE

DC power for the heated windshieldis supplied by the nonessential bus.

Windshield heat right-hand illuminates HOT(yellow) - WSHLD HEAT RH - OFF.

LH WINDSHIELD HEAT circuitbreakers trip - WSHLD HEAT - OFF.

Windshield heat left-hand illuminates HOT(yellow) - WSHLD HEAT LH - OFF.

RH WINDSHIELD HEAT circuitbreakers trip - WSHLD HEAT - OFF.

4

No Change.

3/4

BHT-41 2-FMS-CAA-4

MODEL 412

FLIGHT MANUAL

SUPPLEMENT FORAUXILIARY FUEL OPERATIONS

(412-706-007)


This supplement shall be attached to the CAAModel 412 Flight Manual when the 412-706-007Auxiliary Fuel Kit has been installed.

The information contained herein supplementstheinformation of the basic Flight Manual. ForLimitations, Procedures, and Performance Datanot contained in this supplement, consult the basicFlight Manual.


POST OFFICE BOX 482 . FORT WORTH, TEXAS 76101


AUXILIARY FUEL OPERATIONS

LOG OF PAGES

Original ..... 0........ October 20, 1981

RevisionNo.

RevisionNo.Page

Title ...........................A ..............................1 - 14 ........................

Page

000

APPROVED: October 20, 1981

APPROVED:

CHIEF




412 FLIGHT MANUAL Sections 1, 2, & 3


1

NOTE

The contents of this supplementshall be used in conjunction with thebasic flight manual for helicoptersequipped with the auxiliary fuel kit.


Actual weight changes shall be determinedafter kit is installed and ballast readjusted,if necessary, to return empty weight CGwithin allowable limits.

2

No Change.

3

No Change.

Sections 4, 5 & 6 412 FLIGHT MANUAL CAA APPROVEDSUPPLEMENT


No Change.

SERVICING DATA

FUEL DATA:

Total usable capacity with 412-706-007(both) tanks is 374.7 U.S. gallons (table

6-5).

Total usable fuel capacity with412-706-007 (right) tank is 293 U.S.gallons (table 6-3), 1109.1 liters (table6-6).



AUXILIARY FUEL OPERATIONSTable 6-1. Usable fuel loading table (Sheet 1 of 2)

163 U.S. GALLON AUXILIARY TANKS INSTALLED

Jet B. JP-4ENGLISH

U.S. GAL.

10203040506070

*72.68090

100110120130140150160170180190200210220230240250260270280290300310320330340350360370380390

WEIGHT6.5 LB/GAL

65130195260325390455472520585650715780845910975

104011051170123513001365143014951560162516901755182018851950201520802145221022752340240524702535

CG

143.6143.6140.2134.8131.6129.4127.9127.6128.3130.4133.6136.2138.2139.8141.0142.0143.0143.7144.5145.1145.8146.3146.9147.1147.7148.1148.4148.7149.0149.3149.6149.9150.1150.4150.5150.7150.9151.0151.2151.4

LONGITUDINALMOMENT

93341866827348350554277150480581866022766706762848684093783

107796118131128310138450148720158789169065179199189540199700210067219915230412240663250796260969271180281431291720302049312208322608332605342843353106363155373464383799

LATERAL MOMENTIS ZERO

* Most Critical Fuel Amount for Most Forward CG Condition.

3


AUXILIARY FUEL OPERATIONSTable 6-1. Usable fuel loading (Sheet 2 of 2)

163 U.S. GALLON AUXILIARY TANKS INSTALLED

ENGLISH

WEIGHTU.S. GAL. 6.8 LB/GAL

10 6820 13630 20440 27250 34060 40870 476

*72.6 49480 54490 612

100 680110 748120 816130 884140 952150 1020160 1088170 1156180 1224190 1292200 1360210 1428220 1496230 1564240 1632250 1700260 1768270 1836280 1904290 1972300 2040310 2108320 2176330 2244340 2312350 2380360 2448370 2516380 2584390 2652

CG

143.6143.6140.2134.8131.6129.4127.9127.6128.3130.4133.6136.2138.2139.8141.0142.0143.0143.7144.5145.1145.8146.3146.9147.1147.7148.1148.4148.7149.0149.3149.6149.9150.1150.4150.5150.7150.9151.0151.2151.4

Jet A, JP-5

LONGITUDINALMOMENT

976519530286013666644744627956088062994697957980590848

101878112771123583134232144840155584166117176868187469198288208916219762230064241046261770262371273013283696294420305184315989326618337498347956358666369403379916390701401513






Table 6-2. Usable fuel loading table (Sheet 1 of 2)

82 U.S. GALLON AUXILIARY FUEL TANK ON LEFT SIDE OF CABIN

ENGLISHWEIGHT

U.S. GAL. 6.6 LB/GAL

Jet B. JP-4

LONGITUDINALARM MOMENT

LATERALARM MOMENT

10203040506070

*72.68090

100110120130140150160170180190200210220230240250260270280290300310

65130195260325390455472520585650715780845910975

1040110511701236130013651430149515601625169017551820188519502015

143.6143.6140.2134.8131.6129.4127.9127.6128.3131.5134.6136.8138.6140.2141.7143.0144.2146.2146.1146.9147.7148.3148.8149.4149.8150.3150.6151.0161.3151.6151.9152.2

93341866827348360564277150480581866022766706769288749097812

108108118469128947139425149968160446170937181422192010202430212784223353233688244238264514265006276366286766296205306683

000000000

-0.5-1.0-1.8-2.5-3.2-3.9-4.4-4.9-5.3-6.7-6.1-6.3-6.6-6.8-7.0-7.2-7.4-7.6-7.8-7.9-8.0-8.0-8.1

000000000

-293-660

-1287-1950-2704-3649-4290-5096-5857-6669-7534-8190-9009-9724

-10466-11232-12026-12844-13689-14378-15080-15600-16322


NOTE

Minus (-) lateral arm/moment denotes left lateral shift.




82 U.S. GALLON AUXILIARY FUEL TANK ON LEFT SIDE OF CABIN

ENGLISH Jet A, JP-5

U.S. GAL.

10203040606070

*72.68090

100110120130140150160170180190200210220230240250260270280290300310

WEIGHT6.8 LB/GAL

68136204272340408476494544612680748816884952

10201088115612241292136014281496166416321700176818361904197220402108


LATERALARM MOMENT

143.6143.6140.2134.8131.6129.4127.9127.6128.3131.5134.6136.8138.6140.2141.7143.0144.2145.2146.1146.9147.7148.3148.8149.4149.8150.3150.6151.0151.3151.6151.9152.2

97651953028601366644744527956088062994697968047891528

102326113098123937134898145860156890167851178826189795200872211772222606233662244474255510266261277236288076298955309876320838

000000000

-0.5-1.0-1.8-2.5-3.2-3.9-4.4-4.9-5.3-5.7-6.1-6.3-6.6-6.8-7.0-7.2-7.4-7.6-7.8-7.9-8.0-8.0-8.1

000000000

-306-608

-1346-2040-2829-3713-4488-5331-6127-6977-7881-8668-9425

-10173-10948-11750-12680-13437-14321-15042-15776-16320-17075


NOTE





82 U.S. GALLON AUXILIARY FUEL TANK ON RIGHT SIDE OF CABIN

ENGLISH Jet B, JP-4

WEIGHT LONGITUDINAL LATERALU.S. GAL. 6.5 LB/GAL ARM MOMENT ARM MOMENT

10 65 143.6 9334 0 020 130 143.6 18668 0 030 195 140.2 27348 0 040 260 134.8 35055 0 050 325 131.6 42771 0 060 390 129.4 50480 0 070 455 127.9 58186 0 0

*72.6 472 127.6 60227 0 080 520 128.3 66706 0 090 585 131.5 76928 0.5 293

100 650 134.6 87490 1.0 650110 715 136.8 97812 1.8 1287120 780 138.6 108108 2.5 1950130 845 140.2 118469 3.2 2704140 910 141.7 128947 3.9 3549150 975 143.0 139425 4.4 4290160 1040 144.2 149968 4.9 5096170 1105 145.2 160446 5.3 5857180 1170 146.1 170937 5.7 6669190 1235 146.9 181422 6.1 7534200 1300 147.7 192010 6.3 8190210 1365 148.3 202430 6.6 9009220 1430 148.8 212784 6.8 9724230 1495 149.4 223353 7.0 10465240 1560 149.8 233688 7.2 11232250 1625 150.3 244238 7.4 12025260 1690 150.6 254514 7.6 12844270 1755 151.0 265006 7.8 13689280 1820 151.3 276366 7.9 14378290 1885 151.6 285766 8.0 15080300 1950 151.9 296205 8.0 15600310 2015 152.2 306683 8.1 16322


NOTE

Lateral arm/moment denotes right lateral shift.

7




82 U.S. GALLON AUXILIARY FUEL TANK ON RIGHT SIDE OF CABIN

ENGLISH Jet A, JP-5

WEIGHT LONGITUDINAL LATERALU.S. GAL. 6.8 LB/GAL ARM MOMENT ARM MOMENT

10 68 143.6 9765 0 020 136 143.6 19530 0 030 204 140.2 28601 0 040 272 134.8 36666 0 050 340 131.6 44744 0 060 408 129.4 52795 0 070 476 127.9 60880 0 0

*72.6 494 127.6 62994 0 080 544 128.3 69795 0 090 612 131.5 80478 0.5 306

100 680 134.6 91528 1.0 608110 748 136.8 102326 1.8 1346120 816 138.6 113098 2.5 2040130 884 140.2 123937 3.2 2829140 952 141.7 134898 3.9 3713150 1020 143.0 145860 4.4 4488160 1088 144.2 156890 4.9 5331170 1156 145.2 167851 5.3 6127180 1224 146.1 178826 5.7 6977190 1292 146.9 189795 6.1 7881200 1360 147.7 200872 6.3 8568210 1428 148.3 211772 6.6 9425220 1496 148.8 222605 6.8 10173230 1564 149.4 233662 7.0 10948240 1632 149.8 244474 7.2 11750250 1700 150.3 255510 7.4 12580260 1768 150.6 266261 7.6 13437270 1836 151.0 277236 7.8 14321280 1904 151.3 288075 7.9 15042290 1972 151.6 298955 8.0 15776300 2040 151.9 309876 8.0 16320310 2108 152.2 320838 8.1 17075

Most Critical Fuel Amount for Most Forward CG Condition.

NOTE






635.9 LITERS AUXILIARY TANKS INSTALLED

Jet A, JP-4METRIC

WEIGHTLITERS 0.779 kg/I

4080

120160200240

*274.8280320360400440480520560600640680720760800840880920960

1000104010801120116012001240128013201360140014401480

31.262.393.5

124.6155.8187.0214.1218.1249.3280.4311.6342.8373.9405.1436.2467.4498.6529.7560.9592.0623.2654.4685.5716.7747.8779.0810.2841.3872.5903.6934.8966.0997.1

1028.31059.41090.61121.81152.9

CG

36473647354133993322327232413246327733603432349335383571360236273650366836883703371937313744375437643774378237903797380538103815382338283833383538403846

LONGITUDINALMOMENT

1137.92272.13310.84235.25175.76118.66939.07079.58169.69421.4

10694.111974.013228.614466.115711.916952.618198.919429.420686.021921.823176.824415.725665.126904.928147.229399.530641.831885.333128.834382.035615.936852.938119.139363.340606.841824.543077.144340.5



9



Table 6-4. Usable loading table (Sheet 2 of 2)

635.9 LITERS AUXILIARY TANKS INSTALLED

Jet A, JP-5METRIC


40 32.680 65.2

120 97.8160 130.4200 163.0240 195.6

*274.8 224.0280 228.2320 260.8360 293.4400 326.0440 358.6480 391.2520 423.8560 456.4600 489.0640 521.6680 554.2720 586.8760 619.4800 652.0840 684.6880 717.2920 749.8960 782.4

1000 815.01040 847.61080 880.21120 912.81160 945.41200 978.01240 1010.61280 1043.21320 1075.81360 1108.41400 1141.01440 1173.61480 1206.2

LONGITUDINALMOMENT

LATERAL MOMENTIS ZEROCG

36473647354133993322327232413246327733603432349335383571360236273650366836883703371937313744375437643774378237903797380538103815382338283833383538403846

1188.92377.83463.14432.35414.96400.07259.87407.48546.49858.2

11188.312525.913840.715133.916439.517736.019038.420328.121641.222936.424247.925542.426852.028147.529449.530758.132056.233359.634659.035972.537261.838554.439881.541181.642485.043757.445066.246390.5






318 LITERS AUXILIARY FUEL TANK ON LEFT SIDE OF CABIN

Jet B. JP-4METRIC

LITERS

4080

120160200240

'274.8280320360400440480520560600640680720760800840880920960

100010401080112011601180

WEIGHT0.779 kg/1

31.262.393.5

124.6155.8187.0214.1218.1249.3280.4311.6342.8373.9405.1436.2467.4498.6529.7560.9592.0623.2654.4685.5716.7747.8779.0810.2841.3872.5903.6919.2


LATERALARM MOMENT

3647364735413399332232723241324632773381345235053548358936273658368637113734375237693785379738103820383038403848385638633866

1137.92272.13310.84235.25175.76118.66939.07079.58169.69480.3

10756.412015.113266.014539.015821.017097.518378.419657.220944.022211.823488.424769.026028.427306.328566.029835.731111.732373.233643.634906.135536.3

000000000

-18-38-56-76-94

-109-122-135-145-155-160-168-174-180-186-191-195-198-201-206-208-210

000000000

-50.5-118.4-192.0-284.2-380.8-475.5-570.2-673.1-768.1-869.4-947.2

-1047.0-1138.7-1233.9-1333.1-1428.3-1519.1-1604.2-1691.0-1797.4-1879.5-1930.3


NOTE


11




318 LITERS AUXILIARY FUEL TANK ON LEFT SIDE OF CABIN

Jet A, JP-5METRIC



LATERALARM MOMENT

4080

120160200240

*274.8280320360400440480520560600640680720760800840880920960

100010401080112011601180

32.665.297.8

130.4163.0195.6224.0228.2260.8293.4326.0358.6391.2423.8456.4489.0521.6554.2586.8619.4652.0684.6717.2749.8782.4815.0847.6880.2912.8945.4961.7

3647364735413399332232723241324632773381345235053548358936273658368637113734375237693785379738103820383038403848385638633866

1188.92377.83463.14432.35414.96400.07259.87407.48546.49919.9

11253.512568.913879.815210.216553.617887.619226.220566.421911.123239.924573.925912.127232.128567.429887.731214.532547.833870.135197.636520.837179.3

000000000

-18-38-56-76-94

-109-122-135-145-155-160-168-174-180-186-191-195-198-201-206-208-210

000000000

-52.8-123.9-200.8-297.3-398.4-497.5-596.6-704.2-803.6-909.5-991.0

-1095.4-1191.2-1291.0-1394.6-1494.4-1589.3-1678.2-1769.2-1880.4-1966.4-2019.6


NOTE


412 FLIGHT MANUAL Secton 6CAA APPROVEDSUPPLEMENT



318 LITERS AUXILIARY FUEL TANK ON RIGHT SIDE OF CABIN

Jet B. JP-4METRIC

LITERS

4080

120160200240274.8280320360400440480520560600640680720760800840880920960

100010401080112011601180

WEIGHT0.779 kg/1

31.262.393.5

124.6155.8187.0214.1218.1249.3280.4311.6342.8373.9405.1436.2467.4498.6529.7560.9592.0623.2654.4685.5716.7747.8779.0810.2841.3872.5903.6919.2


LATERALARM MOMENT

3647364735413399332232723241324632773381345235053548358936273658368637113734375237693785379738103820383038403848385638633866

1137.92272.13310.84235.25175.76118.66939.07079.58169.69480.3

10756.412015.113266.014539.015821.017097.518378.419657.220944.022211.823488.424769.026028.427306.328566.029835.731111.732373.233643.634906.135536.3

000000000

1838567694

109122135145155160168174180186191195198201206208210

000000000

50.5118.4192.0284.2380.8475.5570.2673.1768.1869.4947.2

1047.01138.71233.91333.11428.31519.11604.21691.01797.41879.51930.3


NOTE


13




318 LITERS AUXILIARY FUEL TANK ON RIGHT SIDE OF CABIN

Jet A, JP-5METRIC

WEIGHT LONGITUDINAL LATERALLITERS 0.815 kg/I ARM MOMENT ARM MOMENT

40 32.6 3647 1188.9 0 080 65.2 3647 2377.8 0 0

120 97.8 3541 3463.1 0 0160 130.4 3399 4432.3 0 0200 163.0 3322 5414.9 0 0240 195.6 3272 6400.0 0 0

*274.8 224.0 3241 7259.8 0 0280 228.2 3246 7407.4 0 0320 260.8 3277 8546.4 0 0360 293.4 3381 9919.9 18 52.8400 326.0 3452 11253.5 38 123.9440 358.6 3505 12568.9 56 200.8480 391.2 3548 13879.8 76 297.3520 423.8 3589 15210.2 94 398.4560 456.4 3627 16553.6 109 497.5600 489.0 3658 17887.6 122 596.6640 521.6 3686 19226.2 135 704.2680 554.2 3711 20566.4 145 803.6720 586.8 3734 21911.1 155 909.5760 619.4 3752 23239.9 160 991.0800 652.0 3769 24573.9 168 1095.4840 684.6 3785 25912.1 174 1191.2880 717.2 3797 27232.1 180 1291.0920 749.8 3810 28567.4 186 1394.6960 782.4 3820 29887.7 191 1494.4

1000 815.0 3830 31214.5 195 1589.31040 847.6 3840 32547.8 198 1678.21080 880.2 3848 33870.1 201 1769.21120 912.8 3856 35197.6 206 1880.41160 945.4 3863 36520.8 208 1966.41180 961.7 3866 37179.3 210 2019.6

Most Critical Fuel Amount for Most Forward CG Condition.

NOTE


BHT-412-FMS-CAA-5

412

FLIGHT MANUAL

SUPPLEMENT FORGROUP A OPERATIONS

CAA APPROVEDOCTOBER 20, 1981

This supplement shall be attached to the CAA Model 412Flight Manual.

The information contained herein supplements theinformation of the basic Flight Manual; for Limitations,

-Procedures and Performance Data not contained in thissupplement, consult the basic Flight Manual.


GROUP A OPERATIONS

LOG OF PAGES

Original ..... 0 ........ October 20, 1981

RevisionNo.

RevisionNo.Page

Title ...........................A ..............................i- ii...........................1 - 26 ........................

0000

APPROVED: October 20. 1981


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



GROUP A OPERATIONS

INTRODUCTION

DEFINITIONS:

GROUP "A" TAKEOFF

GROUP "A" LANDING

CRITICAL DECISION POINT

LANDING DECISION POINT

TAKEOFF SPACE

REJECTED TAKEOFF AREA

ABBREVIATIONS:

CDP

LDP

VTOSS (V2)

Vy

- Operation of the helicopter in such a manner thatif one engine fails at any time after the start of thetakeoff, the helicopter can -

1. Return to, and safely stop on the takeoff area;or

2. Climb out from point of failure and maintainsingle engine forward flight.

Operation of the helicopter in such a mannerthat if one engine fails at any time in the approach,the helicopter can -

1. Land and stop safely on the intended landing area; or

2. Climb out from point of failure and attainsingle engine forward flight.

- That point on takeoff profile after which, if a single enginefailure is experienced, the helicopter can climb out andmaintain single engine forward flight.

- That poiit on the landing profile after which the helicopteris committed to landing.

- The horizontal distance necessary to achieveVtoss and/or a height of 50 feet (15.2 meters),whichever is higher.

- The horizontal distance necessary to accelerate with allpower units operating from a starting point to CDP, tosuffer a power unit failure, and to reject the takeoff.

- Critical Decision Point

- Landing Decision Point

- Takeoff Safety Speed

- Best Rate of Climb Speed (65 KIAS)

Introduction

GROUP A OPERATIONS


INTRODUCTION (Cont)

ABBREVIATIONS: (Cont)

GROC

NROC

- Gross Rate of Climb

- Net Rate of Climb

CAA APPROVED 41SUPPLEMENT


GROUP A OPERATIONS

ATTENTION CROSSWIND LIMITATIONS

Mandatory compliance with the operatinglimitations in this section is required by law.

TAKEOFF AND LANDING WEIGHTVS ALTITUDE LIMITATIONS

Refer to Gross Weight - Altitude - AmbientAir Temperature Limits Charts. Chartsdesignated Part A may be used for grossweights to 10.000 pounds (4536 kg). Part Bcharts may be used for gross weights to10,800 pounds (4899 kg). Part C charts maybe used for gross weights to 11,600 pounds(5262 kg).

Interpolation of data between charts fordifferent parts is not permitted. Testing hasnot been conducted in areas between Parts A,B. and C.

ALTITUDE LIMIT FOR TAKEOFFAND LANDING

4000 feet (1219 meters) pressure altitude.

The crosswind limit for takeoff and landing is20 knots. Refer to the Headwind ComponentChart.

Takeoff or landing downwind or withquartering tailwinds is prohibited.

MAXIMUM TAKEOFF SPACEREQUIRED

The takeoff space required is obtained fromthe appropriate Takeoff Space RequiredChart, using the headwind component fromthe unfactored Headwind Component Chart.

The minimum width of takeoff and rejectedtakeoff area is 100 feet (30.5 meters).

CONFIGURATION

Standard landing gear or high skid gearwith orwithout emergency floats (floats stowed).

1

PART A W.A.T. LIMITS CHART

VTOSS IS 40 KIAS G.W. TO 10.000 LBS (4536 kg)


GROUP A OPERATIONS

4000

2000

GROSS WEIGHT

PART A WEIGHT- ALTITUDE - TEMPERATURE FOR TAKE-OFF AND LANDING

40 KIAS VTOSS G.W. TO 10,000 LB (4536 kg)

412100-16-1C

PART A. Gross weight - altitude - ambient air temperature limits

6000



GROUP A OPERATIONS

PART B W.A.T. LIMITS CHART


PART B WEIGHT- ALTITUDE -TEMPERATURE FOR TAKE-OFF AND LANDING


412100-16-2C

PART B. Gross weight - altitude - ambient air temperature limits

3


GROUP A OPERATIONS

PART C W.A.T LIMITS CHART

VTOSS IS 55 KIAS G.W. TO 11,600 LBS (5262 kg)

5000

4000

2000

-1000

Kg X 100

PART C WEIGHT - - ALTITUDE - TEMPERATURE FOR TAKE-OFF AND LANDING

55 KIAS VToss G.W. TO 11,600 LB (5262 kg)

412100-16-3C

PART C. Gross weight - altitude - ambient air temperature limits

CAA APPROVED 4SUPPLEMENT

2


GROUP A OPERATIONS

STANDARD TYPE TAKEOFF

1. Collective - Flat pitch.

2. N11 RPM - 100%.

3. Altimeter - Set, note indication withcollective full down.

4. Instruments - Normal OperatingRange.

5. Area - Clear.

9. Maintain pitch attitude as the helicoptermoves forward to achieve the correctCritical Decision Point (CDP) shown onthe takeoff flight path profile diagram.

NOTE

CDP height is determined byreference to the pilots barometricaltimeter. Indicated altitude withcollective full down on the takeoffsurface is used as a ground levelreference.

6. Hover at approximately 4 feet (1.2meters) skid height and note torque.

7. Adjust ADI pitch bar to indicate level.

8. Initiate a takeoff from hover using atransmission torque of 10% abovethat required to hover and tendegrees nose down attitude.

NOTE

Do not exceed transmission torque,ITT, or N1 limits.

10. After attaining CDP, accelerate thehelicopter to 65 KIAS and continuethe climb.

STANDARD TYPE LANDING

NOTE

A standard type landing is initiatedfrom a Landing Decision Point(LDP)of 40 KIAS and an altitude of 100feet (30.5 meters) above therunway, either in level flight or witha rate of descent of not more than500 feet per minute.

5


GROUP A OPERATIONS

ENGINE OUT PROCEDURES NOTE

DURING TAKEOFF AT/OR PRIOR TOCRITICAL DECISION POINT (CDP)

An engine failure prior to reaching CDP willnecessitate a landing back to the takeoffsurface. If height permits, a positivedeceleration to reduce forward airspeed isrequired. As the helicopter descends, itshould be leveled and the collective shouldbe used as required to cushion the landing.Some forward ground speed is normallyrequired at touchdown.

DURING TAKEOFF AFTER CRITICALDECISION POINT (CDP)

In the event of an engine failure at orfollowing CDP, airspeed should be increasedto the takeoff safety speed (VTOSS), ormaintained, whichever is higher. Climb outto 500 feet (152 meters) above the takeoffsurface and accelerate to 65 KIAS. Reducepower to Intermediate Contingency limits.

During takeoff, after passing CDP. itis permissible, during the transitionfrom two engine to single engineflight following an engine failure, todroop the rotor speed to as lowas 91%. Rotor speed should beregained to normal operating rangeat or before attaining appropriatebest rate of climb speed.

DURING LANDING PRIOR TOLANDING DECISION POINT (LDP)

Execute the same procedures as for singleengine failure after CDP or proceed tothe LDP and use the procedure below.

DURING LANDING AT/OR AFTER THELANDING DECISION POINT (LDP)

The helicopter is committed to land with anemergency at/or after the LDP. The landingis accomplished using up to the maximumpower of the remaining engine whilemaintaining rotor speed within limits.



GROUP A OPERATIONS

TAKE-OFF FLIGHT PATH PROFILEMAXIMUM CONTINGENCYPOWER RATING AFTER POWERFAILURE, THEN REDUCE TO INTERMEDIATECONTINGENCY AT 500 FT (152m) AGL.

412100-15

Takeoff flight path profile

7

6000

5000

4000

3000

0

2000

Section 3

GROUP A OPERATIONS


MAX GW1600 LB(5262 kg)

1000

000

78 80 82 84 86 88 90 92 94 96 98 100 102 104 106 108 110 112 114 116LB X00

36 37 38 39 40 41 42 4 41 44 5 46 41 48 419 50 5'1 52 Kg X 100

GROSS WEIGHT

ENROUTE WEIGHT - ALTITUDE - TEMPERATURE - OEI - INTERMEDIATE CONTINGENCYPOWER - VY = 65 KIAS 7,500 TO 11.600 LB (3402 TO 5262 Kg)

412100-17A

Single engine enroute weight - altitude - temperature chart



GROUP A OPERATIONS

2000(10 16)

INTER CONTINGENCY POWERENGINE RPM 97%

GENERATOR 150 AMPS

65 KIAS

HEATER OFFINOPERATIVE ENGINE

412900-58A

Single engine enroute net rate of climb

9


GROUP A OPERATIONS

PERFORMANCE DATA

The performance data presented in this sectionare based on the engine manufacturersminimum specification power for thePT6T-3B engine with installation losses.

An engine power assurance check chart ispresented in the basic rotorcraft flight manualwhich is also based on a minimumspecification engine with installation lossesand proper rigging of engine controls.

If engine performance does not meet thatshown in the Power Assurance Chart, stepsshould be taken to ascertain the causes ofengine power loss.

The minimum runway length for standardtakeoff and landing procedures varies withwind, gross weight, pressure altitude, andtemperature. The headwind component fromthe Headwind Component Chart is applied tothe Part A. Part B, or Part C Takeoff SpaceRequired Chart or Landing Space RequiredChart.

TAKEOFF PERFORMANCE

Takeoff Safety Speed (VTOSS) varies whenoperating under Parts A, B, or C. Refer to theapplicable WAT limit chart for the appropriateVTOSS.

REJECTED TAKEOFF AREAREQUIRED

Rejected Takeoff Area required is spacerequired to takeoff, climb to CDP, encounter

an engine failure at CDP, return to thetakeoff surface, and stop safely.

Rejected Takeoff Area required is obtainedfrom the appropriate Rejected TakeoffArea Required Chart.

TAKEOFF SPACE REQUIRED

Takeoff Space Required is space required totakeoff, climb to CDP, encounter an enginefailure, accelerate to VTOSS, and climb to 50feet (15.2 meters) above the takeoff space.Takeoff space required is obtained from theappropriate Takeoff Space Required Chart.

TAKEOFF NET FLIGHT PATH

The takeoff net flight path begins at theend of the takeoff distance, at 50 feet (16.2meters) or higher above the takeoff space andat VTOSS.

Takeoff Net Flight Path Charts providedata for 50 to 500 feet (15.2 to 152 meters)above takeoff surface and 500 to 1000 feet(152 to 305 meters) above the takeoff surface.

These charts provide altitude gain for each 100feet (30.5 meters) horizontal distancetraveled.

LANDING PERFORMANCE

LANDING SPACE REQUIRED

Landing distance is the distance necessaryto come to a stop from the LDP with oneengine inoperative.



GROUP A OPERATIONS

LANDING PERFORMANCE (Cont)

CORRECTED LANDING DISTANCEFROM LDP

Corrected landing distance from LDP islanding distance corrected for wind factor. Theheadwind component is obtained from theHeadwind Component Chart end is applied tothe Landing Space Required Chart to obtaincorrected landing distance.

6000(1829)


GROUP A OPERATIONS

NET GRADIENT-%

ENROUTE NET GRADIENT OF CLIMB-ONE ENGINE INOPERATIVE

INTER CONTINGENCY POWER 65 KIAS

ENGINE RPM 97% HEATER OFF

GENERATOR 150 AMPS INOPERATIVE ENGINE

24

412900-53A

OEI enroute net climb gradient chart



35-

30-

GROUP A OPERATIONS

40

35

30

25HEADWINDCOMPONENT

15

10

EXAMPLE

7. PROCEED HORIZONTALLY TO THE HEADWINDCOMPONENT SCALE AND READ HEADWIND COMPONENT ....... 17 KNOTS

8. TAILWINDS HAVE NOT BEEN DEMONSTRATED

412900-52

Unfactored headwind component chart

13


GROUP A OPERATIONS

PART A VTOSS = 40 KIAS

10

20

30200 600 1000(61) (183) (305)

TAKE -OFF SPACE REQUIRED -FT. (m.)

TAKE-OFF SPACE REQUIRED - 7,500 TO 10,000 LB GW. (3402 TO 4536 Kg) V2 =40 KIAS412900-54-1

PART A. Takeoff space required chart

0



GROUP A OPERATIONSPART B VTOSS = 45 KIAS CDP 35 KIAS AT 20 FT (6.1m)

I

10 20

OAT -°C

EXAMPLE: OATPRESSURE ALTITUDEWIND

FOLLOW ARROWS FROMTO READ TAKE-OFF SPACEREQUIRED 625 FT. (191 m.) AT)

=25°C= 2000 FT. (609.6 m.)= 20 KTS.

z

30200 600 1000(61) (183) (305)

TAKE - OFF SPACE REQUIRED - FT. (m.)

1400(427)

TAKE-OFF SPACE REQUIRED - 7,500 TO 10,800 LB GW. (3402 TO 4899 Kg) V2 = 45 KIAS

PART B. Takeoff space required chart412900-54-2

15


GROUP A OPERATIONS

PART C VTOSS 55 KIAS CDP = 45 KIAS AT 35 FT (10.7 m)

0

I

-30 -20 -10 0 50

30200(61)

600 1000 1400 1800(183) (305) (427) (549)

TAKE - OFF SPACE REQUIRED - FT. (m.)

TAKE-OFF SPACE REQUIRED - 7,500 TO 11,600 LB GW. (3402 TO 5262 Kg) V2 = 55 KIAS412900-54-3

PART C. Takeoff space required chart

GROUP A OPERATIONS

OAT- C

PART A. Rejected takeoff area required chart

Section 4

GROUP A OPERATIONS

PART B VTOSS = 45 KIAS


CDP = 35 KIAS AT 20 FT (6.1m)

/

I

I

0

412900-55-2

PART B. Rejected takeoff area required chart



GROUP A OPERATIONS

PART C VTOSS = 55 KIAS CDP = 45 KIAS AT 35 FT (10.7m)

412900-55-3

PART C. Rejected takeoff area required chart

PART A


GROUP A OPERATIONS

0

300 2 4

40 KNOTS - MAXIMUM CONTINGENCY POWER50 TO 500 FEET (15 TO 152 METERS) ABOVE SURFACE

412900-57-1A

PART A. Takeoff net flight path (Sheet 1 of 2)

20

PART A



GROUP A OPERATIONS

VTOSS = 40 KIAS

40 KNOTS - INTERMEDIATE CONTINGENCY POWER500 TO 1000 FEET (152 TO 305 METERS) ABOVE SURFACE

412900-57-2A

PART A. Takeoff net flight path (Sheet 2 of 2)

21


GROUP A OPERATIONS


412900-57-3A

PART B. Takeoff net flight path (Sheet 1 of 2)

22

CAA APPROVED 412 FLIGHT MANUALSUPPLEMENT

Section 4

GROUP A OPERATIONS

4000 PART B

PART B. Takeoff net flight path (Sheet 2 of 2)

23

MEAN HEIGHT GAINED IN 100 FEET HORIZONTAL DISTANCE - FEET (METERS)


41290--57-5A

PART C. Takeoff net flight path (Sheet 1 of 2)

Section 4

GROUP A OPERATIONS


PART C

0



GROUP A OPERATIONS

VTOSS = 55 KIASOAT


55 KNOTS - INTERMEDIATE CONTINGENCY POWER500 TO 1000 FEET (152 TO 305 METERS) ABOVE SURFACE

412900-57-6A

PART C. Takeoff net flight path (Sheet 2 of 2)

25


GROUP A OPERATIONS

20 50

z

LANDING SPACE REQUIRED-FT

LANDING SPACE REQUIRED - 7,500 TO 11.600 LB (3402 TO 5262 kg) 412900-56-3ADECISION POINT 100 FEET (30 METERS) @ 40 KIAS - RATE OFDESCENT500 FT/MIN.

Landing space required chart

BHT-412-FMS-CAA-6

SUPPLEMENT FORFLIGHT DIRECTOR

(412-706-111)


This supplement shall be attached to the CAA Model 412Flight Manual when the 412-706-111 Flight Director hasbeen installed.

The information contained herein supplements theinformation of the basic Flight Manual; for Limitations,Procedures, and Performance Data not contained in thissupplement, consult the basic Flight Manual.


FLIGHT DIRECTOR

LOG OF PAGES

Original..... ........ October 20, 1981

RevisionNo.

RevisionNo.Page Page

Title ...........................A .............................1 - 7/8........................

000

APPROVED:

CHIEF

October 20, 1981





FLIGHT DIRECTOR

FLIGHT DIRECTOR LIMITATIONSNOTE

The contents of this supplementshall be used in conjunction with thebasic flight manual for helicoptersequipped with the Flight Director.

TYPE OF OPERATION

The Flight Director may be used duringVFR or IFR non-icing conditions.During VOR approaches, except for VORscollocated at the airport, the Flight Directorshall not be coupled in VOR APR modeprior to VOR station passage inbound.

Maximum approach gradient is 5 degrees.Flight Director modes may not becommanded from the copilot position.

NOTEFlight Director bars are repeatedon copilot ADI.

WEIGHT/CG LIMITATIONSActual weight change shall be determinedafter kit is installed and ballast readjusted,if necessary, to return empty weightCG within allowable limits.

AIRSPEED LIMITATIONSMinimum airspeed for coupled operation offlight director is 60 KIAS.

ENGINE PRESTART CHECK

PILOT INSTR LT knob - OFF (dayoperation).

AUX SYS PITOT and STATIC switches -NORMAL.

SYSTEMS CHECKS

FLIGHT DIRECTOR CHECK


HP1 and HP2 buttons - ON.

Flight director SBY button - Depress andhold; check DCPL light and all mode selectorand helipilot controller lights illuminate andFD fail flag on ADI appears: then releasebutton.

HSI heading marker - Set to aircraftheading.

Flight director HDG button - Depress;check HDG and CPL lights illuminate,SBY light extinguishes.

ADI roll command bar - Check centered.

1


FLIGHT DIRECTOR

HSI heading marker - Move right: checkADI roll command bar moves right and rollactuator position indicator (API) movesright; check cyclic stick moves right inapproximately 2 seconds.

HSI heading marker - Reset to aircraftheading.

Flight director VS button - Depress:check VS light illuminates.

ADI pitch command bar-Check centered.

Cyclic ATTD TRIM switch - Move aft;checkADI pitch command bar moves up andpitch API moves up; check cyclic stickmoves aft in approximately 2 seconds.

Cyclic NAV STBY button - Depressmomentarily and release. Check HDG, VS.and CPL lights extinguish. SBY lightilluminates; check all APIs center, pitch androll command bars retract from view.

Cyclic FORCE TRIM release button -Depress and hold until desired climboutattitude is attained, then release.

Flight director - Select modes as desiredafter reaching 60 KIAS.

IN-FLIGHT OPERATION

Flight director - Select modes as desired.

DESCENT AND APPROACH

Flight director - Select mode for type ofapproach to be flown.

Collective pitch - Adjust to maintaindesired approach speed.

GO-AROUND

Collective GO-AROUND button - Depressat Missed Approach Point.

HSI heading marker - Set to takeoffheading.

NOTE

For prolonged ground operation,AFCS shall be operated in SASmode only.

Collective pitch - Adjust to desired climbpower setting.

Airspeed - Adjust to desired climb speed.

Flight director - Select modes as desired.

LANDINGTAKEOFF

SAS/ATT button - ATT or SAS as desiredduring hover and takeoff; ATT prior toentering Instrument MeteorologicalConditions (IMC).

NOTE

It is recommended that the cyclicFORCE TRIM release button bedepressed before liftoff to trimactuators to center positions.

Cyclic NAV STBY button - Depress at orabove 60 KIAS to decouple flight director.

AFCS - SAS or ATT mode as desired.

NOTE

It is recommended that the cyclicFORCE TRIM release button bedepressed before touchdown to trimactuators to center positions.

For prolonged ground operation,AFCS shall be operated in SAS modeonly.



FLIGHT DIRECTOR

Table 3-1. Caution lights

CAUTION LIGHTWORDING

FAULTCONDITION CORRECTIVE ACTION

DCPL Flight directornot coupled.

Ensure that HP1 and HP2 are engaged in ATT mode.Engage flight director modes as desired.Depress CPL button if CPL light not illuminated.

Table 3-2. Warning flags

FLAG FLAGWORDING LOCATION

ATT

FD

ADI

ADI

FAULT CONDITION

Vertical gyro not turningat full speed/attitudeinformation unreliable.(Flight director may ormay not decouple.)

Flight director not coupleddue to flight directorfailure. (Pitch and rollcommand bars may or maynot retract from view.)

CORRECTIVE ACTION

If only pilots ATT flag isdisplayed pilot shall monitorstandby attitude indicatorand Flight Director.

If only the copilots ATT flag isdisplayed, the copilot shallmonitor the standby ADI.Flight Director is functionaland Flight Directorindications repeated oncopilots ADI are valid. CheckPILOT and CPLT ATTD SYScircuit breakers - in. If flagdoes not retract, continueflight in ATT or SAS mode.

Check FLT DIR (AC and DC)circuit breakers in.Check desired mode(s)engaged. If flag does notretract from view, continueflight in ATT or SAS mode.(ATT mode for IMCconditions.)

3

Sections 3 & 4 412 FLIGHT MANUAL CAA APPROVED

FLIGHT DIRECTOR

Table 3-2. Warning flags (Cont)

FLAGWORDING

GS(No legend)

NAV(No legend)

OFF

FLAGLOCATION

HSI

HSI

HSI

FAULT CONDITION

Glideslope signal unreliable.(ADI pitch command barretracts from view.AFCS holds pitch attitudepresent at time ofsignal failure.)

VOR or localizer signalunreliable. (ADI rollcommand bar retracts fromview. HSI course deviationbar and No. 1 bearing pointerunreliable. AFCS holdsroll level attitude.)

Directional gyro failureor HSI failure.Heading informationunreliable. (AFCS holdsroll level attitude.)

CORRECTIVE ACTION

Continue flight in anymode, using cyclic ATTDTRIM switch and collectiveto maintain airspeed andglidepath. (Monitor rawglideslope data.)

Check NAV 1 (DC) circuitbreaker in. Check VHFNAV 1 tuned properly,signal identified.Continue flight in HDGor ATT mode.

Check PILOT and CPLT HSIand GYRO CMPS (AC) circuitbreakers in. Continueflight in any modeexcept HDG.

FLIGHTCOUPLE

DIRECTOR FAILS TO PITOT-STATICMALFUNCTION

SYSTEM

HP1 and HP2 buttons - ON.

SAS/ATT button - ATT.

CPL button - Depress if CPL light notilluminated.

NOTE

The Flight Director will not coupleif HP1 or HP2 is inoperative.

In the event of an apparent malfunction of thecopilot altimeter, vertical speed indicator,and/or airspeed indicator, proceed as follows:

AUX SYS PITOT or STATIC switch (asapplicable) - OFF.

Flight director - Disengage vertical modes.

No Change.


412 FLIGHT MANUAL

Refer to Section 2.

No Change.

FLIGHT DIRECTOR DESCRIPTION

The flight director is designed for use as aworkload reliever to assist the pilot in controland navigation of the helicopter. The flightdirector has nine modes of operation, any ofwhich may be coupled to the helipilot systemfor fully automatic hands off flight pathcontrol. When decoupled from the helipilots,the flight director provides automatic flightpath computation and visual pitch and rollcommand indications to direct the pilot inmaneuvering the helicopter to maintain theselected flight path. When the flight director iscoupled in the appropriate modes, theautomatic flight control system will maneuverthe helicopter to perform the followingfunctions:

Maintain a constant pressure altitude (ALT).

Maintain a constant indicated airspeed(IAS).

Maintain a constant vertical speed climb ordescent (VS).

Turn to and maintain a selected magneticheading (HDG).

Capture and track a selected VOR radial(NAV or VOR APR).

Capture and track an ILS localizer andglideslope (ILS).

Capture and track a localizer back course(BC).

5

FLIGHT DIRECTOR

Initiate a missed approach (go-around)climbout (GA).

The flight director computer analyzes verticaland lateral flight and navigational data togenerate pitch and roll steering commandswhich are displayed visually on the attitudedirector indicator (ADI). The vertical channelcombines pitch attitude, airspeed, altitude,vertical speed, and glideslope deviationinformation to produce computed pitchcommand signals. The lateral channelcombines roll attitude, heading, and coursedeviation information to produce computedroll command signals. Automatic flight pathcontrol is achieved when the pitch and rollcommands from the flight director computerare coupled to the helipilot computers.

Should a flight or navigation data signalbecome invalid, the affected pitch or rollchannel will revert to attitude hold mode andthe respective command bar on the ADI willretract from view. If either helipilot fails or isdisengaged, the flight director will decoupleautomatically.

FLIGHT DIRECTOR CONTROLS

MODE SELECTOR

The mode selector (figure 7-1) enables thepilot to select the desired flight director modeby depressing the appropriate push-on/push-off button. Selected modes are annunciated byillumination of the respective mode selectbuttons. The NAV, BC, and VOR APR buttonshave two lights each (ARM and CAP) to advisethe pilot of the status of the flight directorcomputer. The ILS button legends (ARM andGS) advise when the computer has armed orcaptured the glideslope. Depressing the SBYbutton disengages all modes and tests theillumination of all mode selector lights.Turning the PILOT INSTR LT knob clockwisedims all mode selector lights for nightoperation.


412075-62

Figure 7-1. Mode selector

COUPLE BUTTON

The CPL button is a push-on/push-offbutton located on the helipilot control panelon the pedestal. When both helipilots (HP1and HP2) are engaged in the attituderetention mode (ATT), selecting any validFlight Director mode will couple the FlightDirector to the helipilots automatically, asindicated by illumination of the ON legend ofthe CPL button. The pilot may decouple theFlight Director by depressing the CPL button.When decoupled, the Flight Director willcontinue functioning in the selected mode,providing visual pitch and roll commands tothe pilot on the attitude director indicator(ADI). Once depressed, the CPL button mustbe depressed again to recouple any FlightDirector mode.

ATTITUDE TRIM SWITCH

The cyclic mounted ATTD TRIM switch can bemoved fore and aft to adjust pitch attitude andlaterally to adjust roll attitude duringdecoupled operation in attitude retentionmode. The switch is also used to make smallairspeed and vertical speed changes whencoupled in IAS or VS modes. (Large attitudechanges should be made by depressing the



FLIGHT DIRECTOR

cyclic FORCE TRIM button.) The ATTD TRIMswitch is disabled during operation in all otherflight director modes, or when either helipilotis disengaged or operated in SAS mode.

FORCE TRIM RELEASE BUTTON

The cyclic mounted FORCE TRIM releasebutton can be depressed to allow the pilot toreposition the cyclic control and pedalsmanually for large scale pitch, roll, and yawcorrections. Upon depressing the button, theforce trim magnetic brakes are released, theflight director modes are decoupledmomentarily, the helipilot pitch, roll, and yawactuators return to center positions, and thehelipilot computers are placed in a fast follow-up mode to track flight control positions. Uponreleasing the button, the helipilots and flightdirector will resume functioning in thepreselected modes. If previously decoupled inthe ATT mode, the helipilots will maintain theattitude existing at the time the button isreleased.

GO-AROUND BUTTON

The GO-AROUND button, located on thecollective control head, is a remote switchhaving the same function as the GA button onthe flight director mode selector. Depressingthe button places the flight director in go-around mode and disengages all other modes.In GA mode the flight director commands a rolllevel attitude and a pitch attitude which willprovide a 750 feet-per-minute rate of climb.(The pilot must adjust collective pitch tomaintain desired climb airspeed.)

NOTE

Refer to the Sperry Pilots Manual forBell Helicopter Model 412 IntegratedFlight Control System for additionalflight director information.

AUXILIARY PITOT-STATICSWITCHES

The AUX SYS PITOT and STATIC switchesprovide a means for isolating the flightdirector airspeed and altitude sensors fromthe copilot pitot-static system in the event ofleakage or other system malfunction. Whenthe PITOT switch is OFF the flight directorairspeed sensor is disconnected, rendering theIAS mode inoperative. Placing the STATICswitch in the OFF position disconnects boththe airspeed and altitude sensors of the flightdirector and thereby disables the ALT, IAS,and VS modes. The pilot should disengagethe affected vertical modes to preventundesirable flight control inputs when eitherswitch is in the OFF position.

FLIGHT DIRECTOR STANDBY BUTTON

The cyclic mounted NAV STBY button is aremote switch having the same functionas the SBY button on the flight directormode selector. Depressing the buttondisengages all flight director modes, tests theillumination of all mode selector lights,retracts the pitch and roll command bars onthe ADI, and places the flight director in astandby status. The pilot must then reselectthe modes if continued flight directoroperation is desired.

7/8

BHT-412-FMS-CAA-7

FLIGHT MANUAL

SUPPLEMENT FORINTERNAL HOIST

(214-706-003)

CERTIFIEDJANUARY 29, 1982

This supplement shall be attached to the Model 412Flight Manual when the 214-706-003 Internal Hoist hasbeen installed.

The information contained herein supplements theinformation of the basic Flight Manual; for Limitations,Procedures and Performance Data not contained in thissupplement, consult the basic Flight Manual.


INTERNAL HOIST

LOG OF PAGES

Original..... ......... January 29, 1982

RevisionNo.


Title ...........................A ..............................i/ii .............................1- 10 ........................

0000

January 29, 1982


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



INTERNAL HOIST

INTRODUCTION

The Internal Hoist, when installed, will permit the operatorto raise or lower loads up to 600 pounds (272 kilograms)allowing hoisting operations in confined areas. The three-sixteenth inch hoist cable is 256 feet (78 meters) in length.Each of the four cabin mounting locations allow the hoistto be extended 90 degrees outboard. Caution lights oneach side of the hoist illuminate when the hook reaches 20feet (6 meters) below the skids during retraction. Anelectrically actuated cable cutting device allows the crewto sever the cable in an emergency. A manually operatedcable cutter, accessible to the operator may be used tosever the cable if the electrical cable cutter fails.

i/ii



INTERNAL HOIST

NOTE

The contents of this supplement shallbe used in conjunction with the basicFlight Manual for helicoptersequipped with the 214-706-003Internal Hoist.

WARNING

THE HOIST OPERATOR SHALLWEAR THE SAFETY VEST ANDSTRAP OR A SUITABLESECURING SAFETY DEVICEWHILE OPERATING THE HOIST.

TYPE OF OPERATION

Hoist operations shall be conducted under theappropriate operating rules.

Operations with hoist installed is approved fornormal operations providing the hoist is notused and the hoist electrical system isdeactivated.

Hoist operations are approved during VMCconditions.

When the hoist is installed in a helicopter withhigh skid gear, with or without floats, the412-706-017 Cable Guard Kit shall beinstalled on the same side of the helicopter asthe hoist.

Hoist operations in the coupled mode areprohibited.

Step shall be stowed during hoistingoperations.

WEIGHT - CG LIMITATIONS

Actual weight changes shall be determinedafter hoist is installed and ballast readjusted, ifnecessary, to retain empty weight CG withinallowable limits.

Maximum gross weight including hoist load is11,600 pounds (5262 kilograms).

Maximum hoist load is 600 pounds (272kilograms). Obtain hoist load allowed from theappropriate Internal Hoist Loading Schedule.

LONGITUDINAL AND LATERALCG LIMITS SHALL NOT BEEXCEEDED DUE TO EXTERNALHOIST LOAD.


INTERNAL HOIST

NOTE

The butt line of the load with thehoist in the forward position is 60inches (1524 millimeters) fromcenterline. The butt line of theload with the hoist in the aftposition is 64 inches (1626millimeters) from centerline.


VNE with hinged panels locked open and cabindoors open is 20 KIAS. VNE with hingedpanels removed and cabin doors removed orsecured open is 60 KIAS.

ALLOWABLE HOIST LOAD

Select the appropriate Internal Hoist LoadingSchedule for the position of the hoist.

THE AIRSPEED WITHEXTERNAL LOAD IS LIMITED BYCONTROLLABILITY. CAUTIONSHOULD BE EXERCISED WHENCARRYING AN EXTERNALLOAD, AS THE HANDLINGCHARACTERISTICS MAY BEAFFECTED BY THE SIZE,WEIGHT, AND SHAPE OF THELOAD.

Enter the schedule at the proper helicoptergross weight. Follow the vertical line to itsintersection point with the proper diagonalline, and follow the horizontal line to theallowable hoist load.

NOTE

Internal Hoist Loading Schedules arebased on 170 pound (77.1 kilogram)pilot, copilot, and operator.


INTERNAL HOIST

HOIST IN AFT LEFT POSITION - BOOM FULLY EXTENDED

600

07000 7400 7800 8200 8600 9000 9400 9800 10200 10600 11000 11400

GROSS WEIGHT PRIOR TO HOIST OPERATION - POUNDS

412100-19-4

HOIST IN FORWARD LEFT POSITION - BOOM FULLY EXTENDED

PILOT & HOIST OPERATOR

(PILOT, COPILOT & HOIST OPERATOR

600

000 00 00 00 00 000 007000 7400 7800 8200 8600 9000 9400 9800 10200 10600 11000 11400


412100-19-3

Internal hoist loading schedule (English) (Sheet 1 of 2)

3

600


INTERNAL HOIST

2

I

HOIST IN AFT RIGHT POSITION - BOOM FULLY EXTENDED


PILOT. COPILOT & HOIST OPERATOR

600

500

300

200

100

07000 7400 7800 8200 8600 9000 9400 9800 10200 10600 11000 11400


412100-19-2

HOIST IN FORWARD RIGHT POSITION- BOOM FULLY EXTENDED

PILOT ONLYPILOT & COPILOT


PILOT, COPILOT & HOIST OPERATOR

7000 7400 7800 8200 8600 9000 9400 9800 10200 10600 11000 11400GROSS WEIGHT PRIOR TO HOIST OPERATION - POUNDS

412100-19-1

Internal hoist loading schedule (English) (Sheet 2 of 2)



INTERNAL HOIST

HOIST IN AFT LEFT POSITION - BOOM FULLY EXTENDED



272

J 03000 3200 3400 3600 3800 4000 4200 4400 4600 4800 5000 5262

GROSS WEIGHT PRIOR TO HOIST OPERATION - KILOGRAMS

412100-18-4

HOIST IN FORWARD LEFT POSITION - BOOM FULLY EXTENDED



272

250

200

150150

100

50

03000 3200 3400 3600 3800 4000 4200 4400 4600 4800 5000 5262


412100-18-3

Internal hoist loading schedule (Metric) (Sheet 1 of 2)

5


INTERNAL HOIST

HOIST IN AFT RIGHT POSITION - BOOM FULLY EXTENDED



272

3000 3200 3400 3600 3800 4000 4200 4400 4600 4800 5000 5262


412100-18-2

HOIST IN FORWARD RIGHT POSITION - BOOM FULLY EXTENDED

PILOT ONLY

PILOT & COPILOT



< 3000 3200 3400 3600 3800 4000 4200 4400 4600 4800 5000 5262


412100-18-1

Internal hoist loading schedule (Metric) (Sheet 2 of 2)



INTERNAL HOIST

NOTE HOIST PWR switch - ON.

Ground crewmember should beinstructed to discharge helicopterstatic electricity before attachingload to hoist when possible.

Check hinged panels (if installed) for securityand operation of lock.

Check cabin doors (if installed) for security andproper operation. Check hoist for security andcondition, all connections secure.

NOTE

The hoist operator shall be familiar with hoistoperating procedures and instructions.

If the hoist is to be operated by the pilot, itmust be installed in the forward right position.

Establish hover over hoisting operation area.

Maintain zero ground speed until load is clearof obstructions.

BOOM switch - OUT, or use pilots collectiveHOIST switch.

If additional loads are carried duringhoisting operations, the load shouldbe placed on the side of thehelicopter opposite the hoistposition.

Check operators pendant installed.

Check HOIST PWR, HOIST CONT, andCABLE CUT circuit breakers - IN.

HOIST switch - DOWN.

NOTE

As hook nears the up or down limitsthe hoist speed automatically slows.

Discharge static electricity whenpossible and connect hoist hook toload observing allowable hoist load.

Check CABLE CUT switches (pedestal andhoist) - OFF: covers safetied.

NOTE

The hoist may be operated from thepilots collective switch box, or theoperators pendant switch. The pilotsswitch will override the operatorsswitch.

HOIST switch - UP.

CAUTION

USE CARE TO PREVENT HOOKAND CABLE FROM FOULINGON FUSELAGE OR LANDINGGEAR.

7

Section 2 412 FLIGHT MANUAL

INTERNAL HOIST

BOOM switch - IN to swing hoist boom andload into cabin, if possible.

Take off into wind if possible, allowingadequate hoist load clearance over obstacles ifload is not internal.

Airspeed - Within limits forhoist operations.


CAA APPROVED 412 FLIGHT MANUALSUPPLEMENT

ON CONTROL BOX ON EACHSIDE OF HOIST

Section 2

INTERNAL HOIST

ATTACHEDTO HOIST

ON CONTROL BOX ONTOP OF HOIST

ON PEDESTAL

PILOT COLLECTIVESTICK

412100-20

Internal hoist controls

9

Sections 3, 4, & 5

INTERNAL HOIST


HOIST LOAD JETTISON

For an emergency jettison of hoist cable andload, actuate CABLE CUT switch (pedestal orhoist) or crewmember can cut cable withmanual cable cutter.

No Change.

Hinged panel - Open or removed.

Cabin door - Secured open or removed.

Hoist - Check.

Pendant - Check.

HOIST PWR, HOIST CONT. CABLE CUTcircuit breakers - IN.

CABLE CUT switches - OFF. Safetied.

HOIST PWR switch - ON.

Hoist operation - Check using pilotscollective switch and operators pendantswitch.

BHT-412-FMS-CAA-8

Bell MODEL

412

FLIGHT MANUAL

SUPPLEMENT FORLITTER KIT OPERATIONS

(412-706-006)

CERTIFIED

JANUARY 29, 1982

This supplement shall be attached to the Model 412Flight Manual when the 214-706-006 Litter Kit has beeninstalled.

The information contained herein supplements theinformation of the basic Flight Manual; for Limitations,Procedures and Performance Data not contained in thissupplement, consult the basic Flight Manual.

Bell HelicopterTEXTRONA Subsidiary ol Textron Inc



LITTER KIT OPERATIONS

LOG OF PAGES

Original..... ........ January 29, 1982

RevisionNo.

RevisionNo.Page

Title ...........................A ..............................1 - 2..........................

Page

000






*NOTE

The contents of this supplement shallbe used in conjunction with the basicFlight Manual for helicoptersequipped with Litter Kit.


Actual weight change shall be determinedafter kit is installed and ballast readjusted if

necessary, to return empty weight CG withinallowable limits.

MINIMUM FLIGHT CREW

The minimum flight crew for litter operationsshall consist of a pilot and a secondcrewmember or cabin attendant, both ofwhom shall be trained in and capable ofassisting in litter patient emergencyevacuation procedures.

LITTER LOADING

Secure patients to litters, then load littersaboard the helicopter in sequence from top tobottom. When only two patients are carried,they should occupy the top and center litterpositions. When only one patient is carried, thecenter litter should be used.

LITTER UNLOADING

NOTE

Normal unloading procedures applywhen either passenger door can beopened. Refer to Section 3,Emergency Procedures for unloading

procedures when cabin doors cannotbe opened.

Open cabin door and unload litters andpatients from the helicopter in sequence frombottom to top.

Litters to be handled by one person insidecabin and one person outside cabin.

Sections 3. 4, & 5 412 FLIGHT MANUAL CAA APPROVEDSUPPLEMENT


UNLOADINGEMERGENCY EXITS

THROUGH Unstrap patient on center litter and removepatient through window opening.

NOTE

In the event that cabin doors cannotbe opened, litter patients shall beunloaded through emergencypop-out windows. After all litterpatients have been removed,ambulatory patients may then exit.

Remove emergency pop-out window bypushing at corners as marked.

Disconnect top litter at end near open windowand lower end to rest on center litter. Removepatient retention straps and slide patient downlitter and out through window opening.

Raise top and center litter ends near openwindow and engage center litter in bracketsfor top litter. Disconnect bottom litter. Raisebottom litter at end near open window and resthandles on the lower surface of the windowopening. Unstrap patient and slide patient uplitter and through window opening.

No change.

No change.

BHT-412-FMS-CAA-9

412

FLIGHT MANUAL

SUPPLEMENT FOREXTERNAL CARGO OPERATION

(212-706-103)


This supplement shall be attached to the CAA Model 412Flight Manual when the 212-706-103 External CargoSuspension Hook has been installed.

The information contained herein supplements theinformation of the basic Flight Manual; for Limitations.Procedures, and Performance Data not contained in thissupplement, consult the basic Flight Manual.


EXTERNAL CARGO OPERATION

LOG OF PAGES

Original ..... 0......... October 20, 1981

RevisionNo.Page

Title ...........................A ..............................i/ii .............................1 - 8..........................

RevisionNo.Page

0000

APPROVED:

CHIEF

October 20, 1981





INTRODUCTION

The External Cargo Suspension Hook, wheninstalled, will permit the owner to utilize thehelicopter for transportation of external cargo forcompensation or hire, when operated by a qualifiedpilot.




NOTE

The contents of this supplementshall be used in conjunction with thebasic flight manual for helicoptersequipped with External CargoSuspension Hook.

TYPE OF OPERATION

Operation of the helicopter with no load on theexternal cargo suspension hook is authorizedunder the standard airworthiness certificateunder VMC or IMC conditions withoutremoving the unit from the helicopter. With aload attached to the suspension assemblyoperation shall be conducted in accordancewith appropriate operating rules under VMCconditions.

The installation and use of the rear viewmirror contained in the kit is left to theoperators discretion.

The rear view mirror shall be covered orremoved for night flight.

Maximum gross weight including externalcargo load is 11,600 pounds (5262kilograms). Maximum external cargo load is4500 pounds (2041 kilograms).


VNE is 80 knots at or below 10,000 feet(3050 meters) density altitude for all grossweights with external cargo on suspensionunit. Above 10,000 feet (3050 meters)decrease VNE 2.5 knots per 1000 feet (305meters).

CAUTION

THE AIRSPEED WITHEXTERNAL CARGO IS LIMITEDBY CONTROLLABILITY.CAUTION SHOULD BEEXERCISED WHEN CARRYINGEXTERNAL CARGO, AS THEHANDLING CHARACTERISTICSMAY BE AFFECTED BY THESIZE, WEIGHT, AND SHAPE OFTHE CARGO LOAD.

WEIGHT - CG LIMITATIONS

Actual weight change shall be determinedafter kit is installed and ballast readjusted, ifnecessary, to retain empty weight CG withinallowable limits.

Light weight, high drag loads require a swivelconnector between the cargo hook and thesling to prevent unstable oscillations in flightabove 20 knots.



PLACARDS AND MARKINGS

OCCUPANCY LIMITEDTO CREW WITH

EXTERNAL LOADCLASS B LOADING

APPROVED

(Located on forward right side of overhead console)

DO NOT OPERATE)HEATER ABOVE 21DEG C OUT AIR TEMP

EMERFLOATS CARGO RELEASE

OPERATIONAL LIMITS

(Located on upper center part of instrument panel)

EXTERNAL LOAD UMIT4500 LBS

SEE FLIGHT MANUAL FORLOADING INSTRUCTIONSAND FLIGHT LIMITATIONS

(Located on under side of helicopter near suspension assembly)

412070-22

SUPPLEMENT

GROUND CREW INSTRUCTIONS

HT MANUAL Section 2


NOTE

Instruct ground crewmember to dischargehelicopter static electricity before attachingcargo by touching the airframe with a groundwire, or if a metal sling is used, the hookup ringcan be struck against the cargo hook. Ifcontact has been lost after initial grounding,the helicopter should be electricallyregrounded and, if possible, contactmaintained until hookup is completed.

EXTERIOR CHECK

Cargo suspension assembly - Condition andsecurity.

Rear view mirror (if installed) - Secure andclean.

The pedal release will functionregardless of CARGO REL switchposition.

CARGO REL switch - OFF.

Battery BUS 1 switch - OFF.

BEFORE TAKEOFF

CARGO REL switch - ARM; check CARGORELEASE ARMED caution light illuminates.

TAKEOFF

NOTE

CARGO HOOK REL circuit breaker - In.

Battery BUS 1 switch - ON.

CARGO REL switch (overhead) - ARMcheck CARGO RELEASE ARMED cautionlight illuminates.

Cyclic CARGO RELEASE button - Depressand hold; pull down on cargo hook; hookshould open. Release button and cargo hook;hook should close and lock.

Cargo release pedal (between directionalcontrol pedals) - PUSH and hold; pull downon cargo hook; hook should open. Releasepedal and cargo hook; hook should close andlock.

Better directional control may berealized by avoiding relative windsfrom the right front quadrant whileperforming external cargooperations.

Hover helicopter at sufficient height to allowcrewmember to discharge static electricityand to attach cargo sling to cargo hook.

NOTE

Attachment of cargo sling to thehook can be observed by means ofthe rear view mirror.

Ascend vertically directly over cargo, thenslowly lift cargo from surface.

3

Sections 2 & 3 412 FLIGHT MANUAL CAA APPROVEDSUPPLEMENT


Pedals - Check for adequate directionalcontrol.

Hover power - Check torque required tohover with external load.

NOTE

The Height - Velocity Diagram is nota limitation for external cargooperations under an appropriateoperating certificate.

Takeoff into the wind if possible, allowingadequate sling load clearance over obstacles.

IN-FLIGHT OPERATION

Airspeed - Within limits for adequatecontrollability of rotorcraft - loadcombination.

Flight path - As required to avoid flight withexternal load over any person, vehicle orstructure.

DESCENT AND LANDING

CARGO REL switch (overhead) - ARM priorto final approach.

Flight path and approach angle - As requiredfor wind direction and obstacle clearance.

NOTE

Control movements should be madesmoothly and kept to a minimum toprevent oscillation of sling load.

CARGO R EL switch (overhead)- As desired.

NOTE

The pedal release will functionregardless of CARGO REL switchposition.

Execute approach to a hover with cargo clearof the surface. When stabilized at a hover,descend slowly until cargo contacts surface.Maintain tension on sling.

Cyclic CARGO RELEASE button - Depress torelease sling from hook.

NOTE

Release of sling load from the hookcan be confirmed visually throughrear view mirror.

Section 3EMERGENCY AND MALFUNCTION PROCEDURES

CARGO FAILS TO RELEASEELECTRICALLY

In the event that cargo hook will not release thesling when the CARGO RELEASE button isdepressed, proceed as follows:

Maintain tension on sling.

Cargo release pedal (between directionalcontrol pedals) - PUSH.




No change with no load attached.

EXTERIOR CHECK TAKEOFF

Cargo suspension assembly - Condition andsecurity.

Rear view mirror (if installed) - Secure andclean.

CARGO HOOK REL circuit breaker - IN.

Battery BUS 1 switch - ON.

CARGO REL switch (overhead) - ARM;check CARGO RELEASE ARMED cautionlight illuminates.

Cargo hook - Check electrical and manualoperation.

CARGO REL switch - OFF.

Battery BUS 1 switch - OFF.

BEFORE TAKEOFF

CARGO REL switch - ARM; check CARGORELEASE ARMED caution light illuminates.

Cargo hook - Discharge static and connect.

Ascend vertically over cargo. Slowly lift cargo.

Pedals - Check directional control.

Hover power - Check torque.

Takeoff into wind.

IN-FLIGHT OPERATION

CARGO REL switch - As desired.

Airspeed - Within limits for controllability.

Flight path - As required.

DESCENT AND LANDING

CARGO REL switch - ARM.

Flight path and approach angle - As required.

Execute approach to a hover with cargo clearof surface. Descend slowly until cargocontacts surface. Maintain tension on sling.

Cyclic CARGO RELEASE button - Depress.

5



EXTERNAL CARGOTABLES

LOADING The External Cargo Loading Table (Metric) listsexternal cargo weights and moments from 40to 2268 kilograms in 40 kilogram increments.

from 50 pounds through 5000 pounds in 50pound increments. Moments have beencalculated for external cargo CG at station138.0.



EXTERNAL CARGO LOADING TABLE - ENGLISH

Cargo Moment Cargo Moment Cargo MomentWeight F.S. 138.0 Weight F.S. 138.0 Weight F.S. 138.0

(Lbs) (Lbs) (Lbs)

50 6900 1800 248400 3550 489900100 13800 1850 255300 3600 496800150 20700 1900 262200 3650 503700200 27600 1950 269100 3700 510600250 34500 2000 276000 3750 517500

300 41400 2050 282900 3800 524400350 48300 2100 289800 3850 531300400 55200 2150 296700 3900 538200450 62100 2200 303600 3950 545100500 69000 2250 310500 4000 552000

550 75900 2300 317400 4050 558900600 82800 2350 324300 4100 565800650 89700 2400 331200 4150 572700700 96600 2450 338100 4200 579600750 103500 2500 345000 4250 586500

800 110400 2550 351900 4300 593400850 117300 2600 358800 4350 600300900 124200 2650 365700 4400 607200950 131100 2700 372600 4450 614100

1000 138000 2750 379500 4500 621000

1050 144900 2800 386400 4550 6279001100 151800 2850 393300 4600 6348001150 158700 2900 400200 4650 6417001200 165600 2950 407100 4700 6486001250 172500 3000 414000 4750 655500

1300 179400 3050 420900 4800 6624001350 186300 3100 427800 4850 6693001400 193200 3150 434700 4900 6762001450 200100 3200 441600 4950 6831001500 207000 3250 448500 5000 690000

1550 213900 3300 4554001600 220800 3350 4623001650 227700 3400 4692001700 234600 3450 4761001750 241500 3500 483000

412900-43

7



EXTERNAL CARGO LOADING TABLE - METRIC

Cargo Moment Cargo MomentWeight 3505 mm Weight 3505 mm

(kg) (kg - mm) (kg) (kg - mm)100 100

40 1402 1240 4346280 2804 1280 44864

120 4206 1320 46266160 5608 1360 47668200 7010 1400 49070

240 8412 1440 50472

360 12618 1560 54678400 14020 1600 56080

440 15422 1640 57482480 16824 1680 58884

412900-44

BHT-412-FMS-CAA-1 0.4

SUPPLEMENTGROUP "A" OPERATIONS

412-705-018S/N 36087 AND SUB

CAA CERTIFIED11 NOVEMBER 1996

This supplement shall be attached to Model 412EPFlight Manual when GROUP "A" OPERATIONS kit hasbeen installed.

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

COPYRIGHT NOTICE

COPYRIGHT 1996

11 NOVEMBER 1996

BHT-412-FMS-CAA-1 0.4

NOTICE PAGE

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

Bell Helicopter Textron Inc.P. O. Box 482

Fort Worth, Texas 76101-0482

BHT-412-FMS-CAA-10.4

LOG OF REVISIONS

Original ........... 0 .............. 11 NOV 96

LOG OF PAGES

REVISIONNO.

REVISIONNO.PAGE PAGE

FLIGHT MANUAL

Title .................................... 0NP ...................................... 0

A - B .................................. 0i- ii .................................. .01 - 34 .................................. 0

NOTE

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

A

BHT-412-FMS-CAA-10.4 CAA APPROVED

LOG OF APPROVED REVISIONS

Original ........... 0..............11 NOV 96

CIVIL AVIATION AUTHORITYSAFETY REGULATION GROUPAVIATION HOUSESOUTH AREAGATWICK AIRPORTGATWICKWEST SUSSEX RH6 OYR


GENERAL INFORMATION

INTRODUCTION

The information contained in this supplement is for group "A" operations. For limitations,normal procedures, emergency and malfunction procedures, and performance data notcontained in this supplement, consult the appropriate sections of this flight manual.

DEFINITIONS:

GROUP "A" Operation of the helicopter in such a manner that ifTAKEOFF one engine fails at any time after the start of the

1. At or prior to CDP, return to and safely stop onthe takeoff area; or

2. At or after CDP, climb out from point of failureand attain single engine forward flight.

GROUP "A"LANDING

CRITICAL DECISIONPOINT

LANDING DECISIONPOINT

COMPLETEDTAKEOFF DISTANCEREQUIRED

REJECTEDTAKEOFF DISTANCEREQUIRED

TAKEOFF SAFETYPATH

Operation of the helicopter in such a manner that ifone engine fails at any time after the start of alanding approach the helicopter can:

1. At or after LDP, continue the approach and safelyland and stop on the clear heliport; or

2. At or prior to LDP, climb out from point of failureand attain single engine forward flight.

The last point In the takeoff path at which a rejectedtakeoff can be assured, and the first point at whicha completed takeoff can be assured.

That point on the landing profile after which thehelicopter is committed to landing

The horizontal distance from the start of theprescribed takeoff procedure to a point at least 50feet above the takeoff surface where VTOSS and apositive rate of climb are attained following anengine failure occurring at or after CDP.

The horizontal distance from the start of theprescribed takeoff procedure to the point where thehelicopter is brought to a safe stop on thedesignated surface following an engine failureoccurring at or prior to CDP.

The distance traveled from where the aircraftreaches VTOSS at or above 50 feet AGL to 1,000 feetAGL.


TAKEOFF SAFETY

LANDING DISTANCEREQUIRED

BALKED LANDING

The airspeed that will assure the required climbperformance with one engine inoperative

The horizontal distance necessary to achieve atakeoff flight path at VTOSS and an altitude of 50 feetor higher, with one engine Inoperative at or prior toLDP; or the horizontal distance necessary to landthe helicopter without further Incident, with oneengine inoperative at or after LDP.

The discontinuation of a landing approach and theinitiation of a climbout. Group "A" balked landingcapability following an engine failure is assured ator prior to LDP.

ABBREVIATIONS:

AGL

CDP

CDT

GROC

LDP

VMIN IFR

VTOSS(V 2 )

Vy

WAT

Above Ground Level

Critical Decision Point

Critical Decision Time

Gross Rate of Climb

Landing Decision Point

Minimum Airspeed forIFR

Takeoff Safety Speed

Best Rate of ClimbSpeed

Weight-Altitude-Temperature

CAA APPROVED BHT-412-FMS-CAA-10.4

Section 1

1-5. CONFIGURATION

Standard landing gear or high skid gearwith or without emergency floats (floatsstowed).

1-6. WEIGHT AND CENTER OFGRAVITY

1-6-C. TAKEOFF AND LANDINGWEIGHT VS ALTITUDE

Refer to Gross Weight-Altitude-AmbientAir Temperature Limits Chart (figure 1-1).Charts designated Part A may be used forgross weights to 10,000 pounds (4636 kg).Part B charts may be used for grossweights to 10,800 pounds (4899 kg). Part Ccharts may be used for gross weights to11,900 pounds (5398 kg).

has not been conducted in areas betweenParts A, B, and C.

1-7. AIRSPEED

1-7-A. CROSSWIND LIMITATIONS

The crosswind limit for takeoff and landingis 20 knots. Refer to the unfactoredHeadwind Component Chart inPERFORMANCE subsection.

Takeoff or landing downwind or withquartering tailwinds is prohibited.

1-8. ALTITUDE

Maximum altitude for takeoff and landingis 4000 feet pressure altitude.

Interpolation of data between charts fordifferent parts is not permitted. Testing

1


PART A W.A.T. LIMITS CHART

VTOSS IS 40 KIAS G.W. TO 10,000 LBS (4536 kg)

GROSS WEIGHT

PART A WEIGHT - ALTITUDE - TEMPERATURE FOR TAKE-OFF AND I ANDING


412FS-CAA-10.4-1-1-1

Figure 1-1. Gross weight-altitude-ambient air temperature limits chart - takeoff andlanding (Sheet 1 of 3)

6000

5000


PART B W.A.T. LIMITS CHART


3000

2000

1000

GROSS WEIGHT

PART B WEIGHT- ALTITUDE - TEMPERATURE FOR TAKE-OFF AND LANDING

46 KIAS VTOSS G.W. TO 10.800 LB (4899 kg)

412FS-CAA-10.4-1-1-2

Figure 1-1. Gross weight-altitude-amblent air temperature limits chart - takeoff andlanding (Sheet 2 of 3)

3

VTOSS IS 55 KIAS G.W. TO 11900 LBS (5398 kg)


PARTC W.A.T.UMITS CHART

412FS-CAA-10.4-1-1-3

Figure 1-1. Gross weight-altitude-amblent air temperature limits chart - takeoff andlanding (Sheet 3 of 3)


2-7. BEFORE TAKEOFFPerform Power Assurance Check, refer tobasic manual.

2-8. TAKEOFF

2-8-A. STANDARD TYPETAKEOFFObtain CDP information - Refer toLimitations of this Supplement and figure2-1.

Collective - Flat pitch.

ENG - 100%RPM (Nl).

Altimeter - Set, note indication withcollective fully down.

Instruments - Normal operating range.

SEAT BELT and NO SMOKE switches - Asdesired.

Area - Clear.

Hover at approximately 4 feet (1.2 meters)skid height and note torque.

Adjust ADI pitch bar to indicate level.

Initiate a takeoff from hover using a MASTTORQUE of 10% above that required tohover and 10° nose down attitude.

NOTE

Do not exceed MAST TORQUE,ITT, or GAS PROD RPM (N1) limits.

Maintain pitch attitude as the helicoptermoves forward to achieve the correct CDPshown on the takeoff flight path profilediagram (figure 2-1).

NOTECDP height is determined byreference to the pilots barometricaltimeter. Indicated altitude withcollective full down on the takeoffsurface is used as a ground levelreference.

After attaining CDP, accelerate thehelicopter to 65 KIAS and continue theclimb.

2-10. DESCENT ANDLANDING

2-10-A. STANDARD TYPELANDING

NOTE

A standard type landing isinitiated from a LDP at 40 KIASand an altitude of 100 feet abovethe runway, either in level flight orwith a rate of decent of not morethan 500 feet per minute (figure 2-2).

Flight controls - Adjust friction to desiredlevel.

GOV switches - AUTO.

Throttles - Fully open.

ENG RPM - 100% RPM (N,,).

FORCE TRIM switch - As desired

STEP switch - As desired.

Altimeter - Set to nearest reportingstation.

SEAT BELT and NO SMOKE sign - Asdesired.

5

TAKE-OFF FLIGHT PATH PROFILEMAXIMUM CONTINGENCYPOWER RATING AFTER POWERFAILURE. THEN REDUCE TO MAXIMUMCONTINUOUS OEI AT 500 FT (152 m) AGL.

HEIGHT

VTOSS MINIMUM

412FS-CAA-10.4-2-1

Figure 2-1. Takeoff flight path profile


LANDING FLIGHT PATH PROFILE

FT.

LANDING DISTANCE

412FS-CAA-10.4-2-2

Figure 2-2. Landing flight path profile

7


Section 3

3-1. INTRODUCTIONTables 3-1 through 3-4 list panel wording,fault conditions, and corrective actions foremergencies and malfunctions that mightoccur during takeoff after CDP, duringlanding prior to LDP, and during landingafter LDP.

3-3. ENGINE

3-3-A. SINGLE ENGINE FAILURE

DURING TAKEOFF PRIOR TO CDP

An engine failure prior to reaching CDPwill necessitate a landing back to thetakeoff surface. If height permits, apositive deceleration to reduce forwardairspeed is required. As the helicopterdescends, it should be leveled and thecollective should be used as required tocushion the landing. Some forward groundspeed is normally required at touchdown.

Maintain control of the helicopter.

Collective - Adjust to maintain ROTORRPM and OEI power limits.

Flair to reduce ground speed.

Assume landing attitude beforetouchdown.

Throttle (affected engine) - Closed.

Complete shutdown of affected engine.

DURING TAKEOFF AFTER CDP

In the event of an engine failure followingCDP, airspeed should be Increased to thetakeoff safety speed (TOSS) or maintained,

whichever is higher. Climb out to 500 feetabove the takeoff surface and accelerate to65 KIAS. Reduce power to maximumcontinuous OEI limits. Refer to singleengine enroute weight-altitude-temperaturechart (figure 3-1).

CAUTION

DURING COLD WEATHEROPERATIONS, CAREFULLYMONITOR TORQUE OF THENORMAL ENGINE WHEN ONEENGINE FAILS OR IS SHUT DOWNIN FLIGHT.

NOTE

During takeoff, after CDP, it ispermissible to droop ROTOR RPMto 91% during the transition fromtwin engine to single engine flightfollowing an engine failure.ROTOR RPM should be regainedto normal operating range at orbefore attaining appropriate bestrate of climb speed.



Airspeed - If below VTOSS, smoothlyincrease to VTOSS and initiate a climb.

Throttle (affected engine) - Close.


ENG (unaffected engine) - Set to 100%RPM (Nll).

AFTER CDP - ENROUTE CLIMB


Refer to figure 3-2 Enroute net rate ofclimb chart.

* DURING LANDING PRIOR TO LDP

Execute the same procedures as for singleengine failure on takeoff after CDP orproceed to LDP and use the procedurebelow.

* DURING LANDING AFTER THE LDP



Flair to reduce speed.

Assume landing attitude beforetouchdown.

Throttle (affected engine) - Closed.


The helicopter, with an emergency, iscommitted to land after LDP. The landingis accomplished using up to the maximumpower of the remaining engine whilemaintaining rotor speed within limits.

9


6000

4000

3000

2000

i -

100078 80 82 84 86 88 90 92 94 96 98 100 102 104 106 108 110 112 114 116 119

36 37 38 39 40 41 42 43 44 45 46 47 48 49 5'0 51 52 53 54GROSS WEIGHT

ENROUTE WEIGHT - ALTITUDE - TEMPERATURE - MAXIMUM CONTINUOUS OEIPOWER - VY = 70 KIAS 7,500 TO 11,900 LB (3402 TO 5398 Kg)

412FS-CAA-10.4-3-1

Figure 3-1. Single engine enroute weight-altitude-temperature chart

CAA APPROVED10,000


12,000

(5443)

11,500\(5216)

11,000(4990)

10,500(4763)

10,000(4536)

NET R/C - FT. MIN

ENROUTE NET RATE OF CLIMB - ONE ENGINE INOPERATIVEMAXIMUM CONTINUOUS OEI - 70 KIAS - ENGINE RPM 97%

GENERATOR 150 AMPS - HEATER OFF - INOP ENGINE SECURED

Figure 3-2. Enroute net rate of climb chart

600 2000

412FS-CAA-10.4-3-2

11


Table 3-1. Warning lights-Takeoff prior to CDP

PANELWORDING

MASTER CAUTION

FAULT CONDITION

Warning or caution light(s)illuminated.

Fire indication in No. 1 orNo. 2 engine compartment

CORRECTIVE ACTION

Land Immediately

FIRE PULL(1 OR 2)

Land immediately.Pull affected FIRE PULL handle.Select MAIN fire extinguisher; itnecessary, select RESERVE fireextinguisher.

BAGGAGE FIRE Smoke in baggage Land immediately.compartment Inspect tailboom area for damage.

ENG OUT(1 or 2)

X MSNPRESSURE

GAS PROD abnormally low,below 53 + 2% RPM (N,), onNo. 1 or No. 2 engine.

Land immediately.Refer to ENGINE OUT procedures.

O I L Transmission oil pressure Land immediately.below limit.

XMSN OIL TEMP Transmission oiltemperature above limit.

Land immediately.

C BOXPRESSURE

O I L Combining gearbox oilpressure below normal.

Land immediately.

C BOX TEMP

BATTERY TEMP

Combining gearboxtemperature above limit.

Battery case temperatureabove limits.

Land immediately.

Land immediately.BATTERY BUS 1 and BUS 2switches - OFF.

WARNING

BATTERY SHALL NOT BE USEDFOR ENGINE START AFTERILLUMINATION OF BATTERY TEMPLIGHT. BATTERY SHALL BEREMOVED AND SERVICED INACCORDANCE WITHMANUFACTURER'S INSTRUCTIONSPRIOR TO RETURN TO SERVICE.

Rotor brake linings not Land immediately.retracted.

ROTOR BRAKE


Table 3-2. Warning lights-Takeoff after CDP

PANELWORDING

MASTER CAUTION

FAULT CONDITION

Warning or Caution light(s)illuminated

CORRECTIVE ACTION

Accelerate to VTOSS. Reset MASTERCAUTION light; take appropriatecorrective action as required byilluminated segment(s).

Accelerate to VToss. Pull affectedFIRE PULL handle. Select MAIN fireextinguisher. Close throttle ofaffected engine. Select RESERVEfire extinguisher if necessary. Landas soon as possible.

FIRE PULL(1 or 2)

Fire indication in No.1 orNo. 2 engine compartment.

BAGGAGE FIRE

ENG OUT(1 or 2)

X MSNPRESSURE

Smoke in baggage Land immediately.compartment Inspect tailboom area for damage.

GAS PROD abnormally low,below 53 ± 2% RPM (N,), onNo.1 or No.2 engine

O I L Transmission oil pressurebelow limit.

XMSN OIL TEMI

C BOXPRESSURE

C BOX TEMP

P Transmission oiltemperature above limit.

Accelerate to VTOSS. Secureappropriate engine. Refer to ENGINEOUT procedure. Land as soon aspossible.

Accelerate to VTOSS. Reduce power;verify fault on XMSN OIL pressuregage. Land as soon as possible.

Accelerate to VTOSS. Reduce power;verify fault on XMSN OILtemperature gage. Land as soon aspossible.

Accelerate to VTOSS. Reduce power;verify fault on GEAR BOX pressuregage. Land Immediately

Accelerate to VTOSS. Reduce power;verify fault on GEAR BOXtemperature gage. Land as soon aspossible.


Combining gearbox oiltemperature above limit.

13

BHT-412-FMS-CAA-1 0.4 CAA APPROVED

Table 3-2. Warning lights-Takeoff after CDP (Cont)

PANELWORDING

BATTERY TEMP

FAULT CONDITION

Battery case temperatureabove limit

CORRECTIVE ACTION

Accelerate to VTOSS. BATTERY BUS1 and BUS 2 switches - OFF. Landas soon as practical.

WARNING


ROTOR BRAKE Rotor brake linings notretracted

Accelerate to VTOSS. Check rotorbrake handle fully up in detent. Iflight remains on, land as soon aspossible.

PANELWORDING

MASTER CAUTION


Table 3-3. Warning lights-Landing prior to LDP

FAULT CONDITION


FIRE PULL(1 or 2)

Fire indication in No.1 orNo.2 engine compartment.

CORRECTIVE ACTION

Reset MASTER CAUTION light; takeappropriate corrective action asrequired by illuminated segment.

Pull affected FIRE PULL handle.Select MAIN fire extinguisher. Closethrottle of affected engine. SelectRESERVE fire extinguisher, ifnecessary. Land as soon aspossible

BAGGAGE FIRE

ENG OUT(1 or 2)

Smoke in baggage Land immediately.compartment. Inspect tailboom area for damage.

GAS PROD abnormally low,below 53 2% RPM (N1), onNo.1 or No.2 engine.

XMSNPRESSURE


XMSN OIL TEMP Transmission oiltemperature above limit.

Maintain VTOSS. Secure appropriateengine. Land as soon as possible.Refer to ENGINE OUT procedure.

Reduce power. Verify fault on XMSNOIL pressure gage. Landimmediately.

Reduce power. Verify fault on XMSNOIL temperature gage. Land as soonas possible.

Reduce power. Verify fault on GEARBOX pressure gage. Land as soonas possible

Reduce power. Verify fault on GEARBOX temperature gage. Land assoon as possible.

C BOXPRESSURE


C BOX OIL TEMP Combining gearbox oiltemperature above limit.

15


Table 3-3. Warning lights-Landing prior to LDP (Cont)

PANELWORDING

BATTERY TEMP

FAULT CONDITION


CORRECTIVE ACTION

BATTERY BUS 1 and BUS 2switches - OFF. Land as soon aspractical

WARNING


ROTOR BRAKE Rotor brake linings notretracted.

Check rotor brake handle fully up Indetent. If light remains on, land assoon as possible.


Table 3-4. Warning lights-Landing after LDP

PANELWORDING

MASTER CAUT

FIRE PULL(1 or 2)

BAGGAGE FIRE

ENG OUT(1 or 2)

X M S NPRESSURE

XMSN OIL TEM

C BOXPRESSURE

C BOX TEMP

BATTERY TEMI

ROTOR BRAKE

ION

FAULT CONDITION


Fire indication in No.1 orNo.2 engine compartment.

Smoke in baggagecompartment.

GAS PROD abnormally low,below 53 ± 2% rpm (N), onNo.1 or No.2 engine.


P Transmission oiltemperature above limit.

O I L Combining gearbox oilpressure below normal

Combining gearboxtemperature above limit.


Rotor brake linings notretracted.

CORRECTIVE ACTION

Land immediately

Land immediately.Pull affected FIRE PULL handle.Close throttle of affected engine.Select MAIN fire extinguisher; ifnecessary, select RESERVE fireextinguisher.

Land immediately.Inspect tailboom area for damage

Land immediately.Refer to ENGINE OUT procedures.

Land immediately.

Land immediately.

Land immediately.

Land immediately.

Land immediately.BATTERY BUS 1 and BUS 2switches - OFF.

WARNING


Land immediately.

17


Section 4

4-1. INTRODUCTION

The power performance data presented inthis section is based on enginemanufacturers minimum specificationpower for the PT6T-3D engine withinstallation losses.

The takeoff and landing data presented inthis section is based on test performed ona level asphalt runway 75 feet wide. Theminimum runway length for standardtakeoff and landing procedures varies withwind, gross weight, pressure altitude, andtemperature.

4-2. POWER ASSURANCECHECK

Refer to Section 4 of applicable BasicFlight Manual for power assurance chartsto determine if the engine (power sections)can produce installed specification power.

The hover check is preformed prior totakeoff. The in-flight check is provided forin-flight monitoring of engine performance.If either engine (power section) does notmeet the requirements of the hover or in-flight power assurance check, group "A"performance will not be achievable. Thecause of engine power loss, or excessiveInterturbine temperature (ITT) or GASPROD RPM (N,) shall be determined assoon as practical. Refer to appropriateengine maintenance manual.

4-5. HOVER CEILING

The Unfactored Headwind Componentchart (figure 4-1) is provided with anexample to determine critical crosswindand corrected headwind for group "A"takeoff and landings. The headwindcomponent, as calculated from theheadwind component chart, is applied toparts A, B, and C of the Takeoff SpaceRequired charts.

4-6. TAKEOFF DISTANCE

4-6-A. REJECTED TAKEOFFDISTANCE REQUIRED

The rejected takeoff distance required Isthe space necessary to takeoff, climb toCDP, encounter an engine failure at CDP,return to takeoff surface, and stop safely.The rejected takeoff distance required isobtained from either part A, B, or C of theRejected Takeoff Distance Required charts(figure 4-2).

4-6-B. TAKEOFF SPACEREQUIRED

The takeoff space required is thehorizontal distance required to takeoff,climb to CDP, encounter an engine failure,accelerate to VTOSS, and climb to 50 feetAGL above the takeoff space. Takeoffspace required is obtained from either partA, B, or C of the Takeoff Space Requiredcharts (figure 4-3) using the headwindcomponent from the Unfactored HeadwindComponent chart (figure 4-1).

4-5-A. HEADWIND COMPONENT


4-6-C. TAKEOFF FLIGHT PATH

The takeoff flight path begins at the end ofTakeoff Space Required, at 50 feet AGL orhigher, above the takeoff space and atVTOSS, Parts A, B, or C of the Takeoff FlightPath charts (figure 4-4) provide data for 50to 500 feet and 500 to 1,000 feet AGL.These charts provide altitude gain for each100 feet (30.5 meters) horizontal distancetraveled.

4-7. CLIMB AND DESCENT

4-7-A. ENROUTE CLIMB

Refer to figure 4-5 OEI Enroute net climbgradient chart.

Landing space required is the distancenecessary to come to a stop from LDP withone engine inoperative.

Landing space required is obtained fromthe Landing Space Required chart (figure4-6).

4-9-B. CORRECTED LANDINGDISTANCE

Corrected landing distance from LDP islanding distance corrected for wind factor.

The headwind component is obtained fromcalculation of the Unfactored HeadwindComponent chart (figure 4-1), and appliedto the Landing Space Required chart(figure 4-6) to obtain corrected landingdistance.

4-9. LANDING DISTANCE

4-9-A. LANDING SPACEREQUIRED

19

x


35

40

35

30

25

CROSSWIND COMPONENT- KT.

EXAMPLE

4. REPORTED WIND SPEED ............................... 20 KNOTS

6. FOLLOW THE SHAPE OF THE CURVED UNES. TO WIND

COMPONENT SCALE AND READ HEADWIND COMPONENT ....... 17 KNOTS

412FS-CAA-10.4-4-1

Figure 4-1. Unfactored headwind component chart

REJECTED TAKE-OFF AREA REQUIRED

PART A

GW 7.500 TO 10.000 LB (3402 TO 4536 Kg)

VTOSS = 40 KIAS CDP = 30 KIAS AT 15 FT (4.6m)

10

OAT - C

CAA APPROVED BHT-412-FMS-CAA-1 0.4

Figure 4-2. Rejected takeoff distance required (Sheet 1 of 3)

21



PART B

GW 7,500 TO 10.800 LB (3402 TO 4899 Kg)


22

I0 10 20



PART C

EXAMPLE: OATPRESSURE ALTITUDEWIND


412FS-CAA-10.4-4-2-3


23


TAKE-OFF SPACE REQUIRED

PART A


412FS-CAA-10.4-4-3-1

Figure 4-3. Takeoff space required chart (Sheet 1 of 3)



PART B

GW 7.500 TO 10.800 LB (3402 TO 4899 Kg)


Figure 4-3. Takeoff space required chart (Sheet 2 of 3)

EXAMPLE: OAPRWI

FOTORE

25


412FS-CAA-10.4-4-3-3412FS-CAA-I0.4-4-3-3



PART C

GW 7,500 TO 11,900 LB (3402 TO 5398 Kg)


0Figure 4-3. Takeoff space required chart (Sheet 3 of 3)


412FS-CAA-10.4-4-4-1

Figure 4-4. Takeoff flight path (Sheet 1 of 6)

27

PART A


VTOSS = 40 KIAS


PART B

2000(609.6)

10.800

10,000(4536)



45 KNOTS - MAXIMUM CONTINGENCY POWER

412FS-CAA-10.4-4-4-3



45 KNOTS - MAXIMUM CONTINUOUS OEI500 TO 1000 FEET (152 TO 305 METERS) ABOVE SURFACE

412FS-CAA-10.4-4-4-4



I

c


PART C

10

30

41 2FS-AA-10.4-4-4-5


31

PART C

OAT-'C

(3402)


MAX. GROSS



2000

ENROUTE NET GRADIENT OF CLIMB - ONE ENGINE INOPERATIVEMAXIMUM CONTINUOUS OEI - 70 KIAS - ENGINE RPM 97%

GENERATOR 150 AMPS - HEATER OFF - INOP ENGINE SECURED

412FS-CAA-10.4-4-5

Figure 4-5. OEI Enroute net climb gradient chart

33

I ®40 -30 -20 -10 0 10 20 30 40 50

OAT - C


LANDING SPACE REQUIRED - 100 FT. HEIGHT TO STOP

GW 7,500 TO 11,900 LB (3402 TO 5398 kg)

LANDING DECISION POINT 100 FEET (30.5 METERS) @ 40 KIAS

RATE OF DESCENT 500 FT/MIN.Figure 4-6.Landing space required

Figure 4-6. Landing space required chart

BHT-412-FMS-CAA-12

MODEL 412

FLIGHT MANUAL

SUPPLEMENT FORNIGHTSUN SEARCHLIGHT

(212-899-333)

CERTIFIEDDECEMBER 4, 1981

This supplement shall be attached to the Model 412 FlightManual when the 212-899-333 Nightsun Searchlight hasbeen installed.

The information contained herein supplements the informationof the basic Flight Manual; for Limitations, Procedures, andPerformance Data not contained in this supplement, consultthe basic Flight Manual.


POST OFFICE BOX 482 * FORT WORTH, TEXAS 76101


NIGHTSUN SEARCHLIGHT

LOG OF PAGES

Original ..... 0 ..... December 4, 1981


RevisionNo.

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

000

APPROVED: December 4, 1981

CHIEF






INTRODUCTION

The Nightsun Searchlight is a high intensity lightwhich mounts on the lower nose of the helicopter.The xenon arc light may be started, aimed andfocused from the operators panel inside thehelicopter. The kit consists of the NightsunSearchlight, mounts, hardware, cable, and operatorspanel.

i/ii




*11NOTE WEIGHT/CG LIMITATIONS

The contents of this supplement shallbe used in conjunction with the basicflight manual for helicoptersequipped with the NightsunSearchlight.

Actual weight changes shall be determinedafter kit is installed and ballast readjusted, ifnecessary, to return empty weight CG withinallowable limits.

PLACARDS AND DECALS

CAUTION

DO NOT USE NIGHTSUN SEARCHLIGHTBELOW 50 FT AGL OR IN FOG CONDITIONS.MONITOR LOADMETER WHEN USINGNIGHTSUN SEARCHLIGHT.

412099-5

CREW LIMITATIONS

Operation of the Nightsun Searchlight isrestricted to the copilot or operator position.

EXTERIOR CHECK

Nightsun Searchlight - Security andwiring. Lens for cleanliness. Refer toOperators Manual for detailed servicing andcleaning instructions.

PRESTART CHECK

SCHLT PWR and SCHLT CONT circuitbreakers - IN.

1

Sections 2. 3, 4. & 5 412 FLIGHT MANUAL CAA APPROVEDSUPPLEMENT


INFLIGHT OPERATION

NIGHTSUN SEARCHLIGHT MASTERswitch - ON.

NIGHTSUN SEARCHLIGHT START switch- START, hold in start positionapproximately 5 seconds, or until ignitionhas occurred.

CAUTIO N

HOLDING SWITCH IN STARTPOSITION AFTER IGNITIONMAY DAMAGE EQUIPMENT.

Aim and focus - As desired.

CAUTION

DO NOT AIM THE BEAMTOWARD OTHER AIRCRAFT ORVEHICLES BECAUSE OFTEMPORARY BLINDINGEFFECT.

BEFORE LANDING

NIGHTSUN SEARCHLIGHT MASTERswitch - OFF.

No Change

No Change

No Change

BHT-412-FMS-CAA-24

Bell MODEL 412

ROTORCRAFTFLIGHT MANUAL

SUPPLEMENT FORSEAT CUSHION KIT

412-706-019

CERTIFIED2 NOVEMBER 1987

This supplement shall be attached to Model 412 Flight Manualwhen the 412-706-019 Seat Cushion Kit has been installed.

The information contained herein supplements the informationof the basic Flight Manual. For Limitations, Procedures, andPerformance Data not contained in this supplement, consultthe basic Flight Manual.



2 NOVEMBER 1987

Log of Pages

BHT 412-FMS-CAA-24

412 ROTORCRAFTFLIGHT MANUAL


LOG OF REVISIONS

Original.....0 ......... 2 November 1987

LOG OF PAGES

REVISIONNO.


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

0000

APPROVED: 2 NOVEMBER 1987



A



INTRODUCTION

BHT 412-FMS-CAA-24

INTRODUCTION

The Seat Cushion Kit is installed in conjunction with theUtility Passenger Seat Kit and provides increasedcomfort level for passengers.

i/ii



Section 1 & 2

BHT 412-FMS-CAA-24

Section 1

WEIGHT/CG LIMITATIONS PLACARDS AND MARKINGS

Actual weight change shall be determinedafter Seat Cushion Kit is installed and ballastreadjusted if necessary to return empty weightCG within allowable limits.

DOORS MUST BE KEPTCLOSED DURING FLIGHT IFSEAT CUSHIONS INSTALLED

Section 2~~~E

BEFORE TAKEOFF

Passenger doors - Closed.

1-1/1-2

BHT-412-FMS-CAN-30

MODELS 412/412EP

ROTORCRAFT

FLIGHT MANUAL

CANADIAN ADDENDUM TOTHE SUPPLEMENTS FOR

INTERNAL HOISTAND


APPROVED FOR DOTNOVEMBER 9, 1989

This addendum shall be attached to the Models 412 and 412 EPFlight Manual when Internal Hoist or External CargoSuspension Unit is installed.

The information contained herein supplements the informationof the basic Flight Manual. For Limitations, Procedures, andPerformance Data not contained in this addendum, consult thebasic Flight Manual.

Bell Helicopter TEXTRONA Subsidiary of Textron Inc

COPYRIGHT NOTICE POST OFFICE BOX 482. FORT WORTH, TEXAS 76101

COPYRIGHT 1994

AND BELL HELICOPTER TEXTRON REISSUE - 23 JUNE 1994A DIVISION OF TEXTRON CANADA LTD

ALL RIGHTS RESERVED

412 ROTORCRAFT FAA APPROVEDFLIGHT MANUAL SUPPLEMENT

BHT-412-FMS-CAN-30 FOR DOT

LOG OF REVISIONS

Original ..... 0 ..... 09 Nov 89Reissue..... ...... 23 Jun 94

LOG OF PAGES

RevisionPage No.

Title ............................ 0A ..... .... .... .... ..... .... .. . ..01/2 ............................. 0

NOTICE

This addendum provides additional information to that contained within theInternal Hoist and External Cargo Hook Operation FAA Flight ManualSupplements.

APPROVED:

MANAGER

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


This page applies to Canadian Registered helicopters only.

A

FAA APPROVEDSUPPLEMENTFOR DOT

Section I


Section 1

BHT-412-FMS-CAN-30

FLIGHT CREW LIMITATIONS

No person shall be carried during internalhoisting or external cargo hook operations unlessthat person:

HEIGHT-VELOCITY LIMITATIONS

The Height-Velocity limitations of the basicmanual are not limitations for hoisting or externalcargo hook operations.

a. is a crewmember;

b. is a crewmember trainee; or

c. performs a function essential to theoperation.

This page applies to Canadian Registered helicopters only.


* MODEL

ROTORCRAFTFLIGHT MANUAL

SUPPLEMENTUNITED KINGDOM REGISTERED

HELICOPTERS412-705-016

AND412-705-018CAA CERTIFIED

11 NOVEMBER 1996

This supplement shall be attached to Model 412EPFlight Manual when UNITED KINGDOM REGISTEREDHELICOPTERS kit has been installed.

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

COPYRIGHT NOTICECOPYRIGHT 1996BELL * HELICOPTER INC.AND BELL HELICOPTER TEXTRON INCA DIVISION OF TEXTRON CANADA LTD

ALL RIGHTS RESERVED


POST OFFICE BOX 482 · FORT WORTH. TEXAS 76101

11 NOVEMBER 1996


NOTICE PAGE

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

Bell Helicopter Textron Inc.P. O. Box 482

Fort Worth, Texas 76101-0482

NP


LOG OF REVISIONS

Original ........... 0 .............. 11 NOV 96

LOG OF PAGES

REVISIONNO.


Title ..................................... 0N P ...................................... 0

A B .................................. 0i/ii ....................................... 01 - 52 .................................. 0

NOTE

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

A


LOG OF APPROVED REVISIONS

Original ........... 0 .............. 11 NOV 96

APPROVED:

CIVIL AVIATION AUTHORITYSAFETY REGULATION GROUPAVIATION HOUSESOUTH AREAGATWICK AIRPORTGATWICKWEST SUSSEX RH6 OYR


Section 1

1-2. BASIS OF CERTIFICA-TION

This helicopter is certified under BCARGroup A.

1-3. TYPES OF OPERATION

The basic configured helicopter isapproved for fifteen-place seating and iscertified for operation under non-icingconditions.

1-9. MANEUVERING

1-9-B. CLIMB AND DESCENT

Maximum IMC rate of climb or descent is1000 feet per minute.

Maximum IMC approach slope is 5degrees.

1-13. POWER PLANTThe IMC configured helicopter is certifiedfor operation during day or night non-icingconditions.

Refer to Flight Manual Supplement BHT-412-FMS-CAA-10.4 for additionallimitations procedures and performancedata for GROUP A operations.

1-5. CONFIGURATION

1-5-A. REQUIRED EQUIPMENTAppropriate equipment as required byBCAR and AND shall be installed.

Instrument markings (Figure 1-2)

NOTE

Operation in maximumcontinuous OEI or maximumcontingency power range isintended for emergency use only,when one engine becomesinoperative due to an actualmalfunction. Routine operation inmaximum continuous OEI ormaximum contingency powerrange can affect engine warrantyand service life.

1-5-C. DOORS OPEN /REMOVEDFor overwater operations with emergencyfloats installed all doors shall be installed.

1-7. AIRSPEEDThe Vno is VNE minus 10 knots (Figure 1-1).

NOTE

Operation in excess of twinengine takeoff power limits ispermitted only for maintenancepurposes in accordance with thePratt & Whitney MaintenanceManual or Annual AirworthinessFlight test in accordance with theapproved CAA Flight TestSchedule.


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

1-13-A-1. ONE ENGINEINOPERATIVE (OEI)

Continuous 1037%

MaximumContingency (2½minute) Range 103.7% to 109.2%MaximumContingency 109.2%

1-13-B. POWER TURBINE RPM(N1.)

Maximum transient (2seconds maximum) 101.0%

Maximum for Starting(2 sec. max. above960 °C) 1090 °C

1-13-C-2. ONE ENGINEINOPERATIVE (OEI)

1-13-C-2-a. Gage PN 212-075-067-115

Maximum Continuous 820 °CMaximum Contingency 820 to 925 °C(2'/2 minute) RangeMaximum Contingency 925 °C

NOTEEither ITT gage shall be installedIn pairs.

1-13-C-2-b. Gage PN 212-075-067-119

Maximum Continuous 820 °C

MaximumContingency (2½minute) Range 820 to 940 °CMaximumContingency 940 °C

1-13-C. INTERTURBINETEMPERATURE (ITT)

1-13-C-1. TWIN ENGINEOPERATION

1-13-C-1-a. Gage PN 212-075-067-115

Continuous 300 to 810 °CMaximum Continuous 810 °C

Maximum Transient (5sec. max. above 810°C) 925 °CMaximum for Starting(2 sec. max. above960 °C) 1090 °C

NOTEEither ITT gage shall be installedin pairs.

1-13-C-1-b. Gage PN 212-075-067-119

Continuous 300 to 810 °C

Maximum Continuous 810 °CMaximum Transient (5sec. max. above 810°C) 940 °C

1-13-D. ENGINE TORQUE

1-13-D-1. ONE ENGINEINOPERATIVE (OEI)

Continuous

Maximum Continuous

MaximumContingency (2½minute)

MaximumContingency

5 to 73.2%

73.2%

73.2 to 81%

81%

1-15. ROTOR

1-15-D. ROTOR RPM (NR) - OEI

Continuous operation 97 to 100%


TWIN 103.1% CONTINUOUSMAX CONTINGENCY OEI 109.2% OEI 103.7%

412FSCAA-57.4-1-1

Figure 1-1. Placards and decals

3

CAA APPROVED

n


Section 2

No change from basic manual.

Section 3

3-3. ENGINE LOAD position, the battery willprovide approximately 75.9minutes of electrical power.

3-3-A. SINGLE ENGINE FAILURE

NOTE

Minimum allowable rotorspeed atmaximum gross weight may droopto 76% NR during OEI landing.

3-9. AUTOMATIC FLIGHTCONTROLS SYSTEM

3-9-C. AFCS HARDOVER ORABNORMAL CONTROLDISTURBANCE

3-7. ELECTRICAL SYSTEM

3-7-A. DC POWER FAILURE

NOTE

WARNING

IF AP1 OR AP2 FAILS OR ISDISENGAGED, REDUCEAIRSPEED TO 115 KIAS OR LESSAND REMAINDER OF FLIGHTSHALL BE EXECUTED HANDS ON.

A fully charged battery willprovide sufficient electrical powerfor approximately 22.6 minutesunder normal conditions. Withemergency load switch in EMERG


Section 4

4-5. HOVER CEILING

4-5-A. HOVER CEILING - IGE

Adequate cyclic and directional control areavailable at the gross weights allowed bythe Hover Ceiling IGE charts in relativewinds up to 35 knots from any direction ator below 3000 feet H,. Improved controlmargins will be achieved by avoidingwinds in the critical relative wind azimuthareas (figure 4-1).

The Hover Celling In Ground Effect charts(figure 4-2) provide the maximum allowablegross weights for hovering IGE at allpressure altitude and outside airtemperature conditions with heater on oroff. Conversely, the hover ceiling altitudecan be determined for any given grossweight.

4-5-B. HOVER CEILING - OGE

The Hover Ceiling Out of Ground Effectcharts (figure 4-3) provide maximumweights for hovering OGE at all pressurealtitude and outside air temperatureconditions with heater on or off. Datapresented is valid up to 3000 ft HD.

CAUTION

OGE HOVER OPERATION MAYRESULT IN VIOLATION OFHEIGHT-VELOCITY LIMITATIONS.

Some of the OGE hover ceiling charts aredivided Into two areas as follows:

AREA A (unshaded area) as shown on thehover ceiling charts presents hoverperformance for which satisfactory cyclicand directional control have beendemonstrated in relative winds of 35 knotsfrom any direction at or below 3000 ft HD.Improved control margins will be achievedby avoiding winds In the critical relativewind azimuth areas.

AREA B (shaded area) as shown on hoverceiling charts presents additional hoverperformance which can be achieved Incalm winds or winds outside the criticalrelative wind azimuth areas.

NOTE

Tail rotor or cyclic control marginmay preclude operation in AREAB of the hover ceiling charts whenthe relative wind Is In therespective critical wind azimutharea.

4-6. TAKEOFF DISTANCE

The Takeoff Distance charts (figure 4-4)provide takeoff distance required to clear a50 foot (15 meter) obstacle in a zero windcondition, using a takeoff flight path whichwill avoid the critical areas of the Height-Velocity diagram (Section 1). Takeoff IsInitiated from a hover at 4 feet (1.2 meters)skid height with climbout speed of 45knots.

NOTE

Downwind takeoffs are notrecommended because thepublished takeoff distanceperformance cannot be achieved.


4-7. CLIMB AND DESCENT

NOTE

When climbing at 100% masttorque and OVER TORQUE lightilluminates, reduce power slightly.

4-7-A. TWIN ENGINE RATE OFCLIMB

weight combinations with heater off atmaximum continuous power.

NOTE

Published single engineperformance is intended foremergency use only when oneengine becomes inoperative dueto an actual malfunction. Routineoperation in maximumcontingency (2 1/2 minute) OEI ormaximum contingency OEI rangecan affect engine service life.

The Twin Engine Rate of Climb charts(figure 4-5) provide the rates of climb thatcan be obtained at all outside airtemperatures/pressures altitudes/grossweight combinations with heater on or offat maximum continuous power and takeoffpower.

NOTE

All rate of climb data are based onchanges in true altitude (pressurealtitude corrected for nonstandardtemperature).

4-7-B. SINGLE ENGINE RATE OFCLIMB

NOTE

OEI operations is howeverpermitted for maintenance, OEItraining, and airworthiness flighttest purposes.

4-9. LANDING DISTANCE

The Single Engine Landing Distance chart(figure 4-7) provides the landing distancesrequired to clear a 50 foot (15 meter)obstacle for all outside air temperatures,pressure altitudes, and gross weights.Landing distances are based on anapproach condition of 45 KIAS and 500feet per minute rate of descent and zerowind.

The Single Engine Rate of Climb charts(figure 4-6) provide the rates of climb thatcan be obtained at all outside airtemperature/pressure altitudes/gross

270°

270

SEE NOTE2


NOTE:1. Pedal critical windazimuth-hovering withthe relative wind within

SEE NOTE these azimuth anglescan result in inability tomaintain heading dueto large left pedalrequirements forcertain wind velocities.2. Longitudinal cycliccritical wind azimuth -

95 aft cyclic may belimited withlongitudinal AFCShardover.

SEE NOTE2

OGE CRITICAL RELATIVE WIND AZIMUTH

SEE NOTE1

412-FS-CAA-57.4 4-1IGE CRITICAL RELATIVE WIND AZIMUTH

Figure 4-1. Critical relative wind azimuths

9



POWER: SEE NOTE BELOWENG - 100% RPM IN2)GENERATOR 150 AMPS (EA.)

SKID HEIGHT 4 FEETHEATER ON OR OFF

-40°

TO 52°C

NOTE THESE IGE HOVERCEILINGS ARE BASED ONDENSITY ALTITUDE LIMITS FORTAKEOFF AND LANDING THISHELICOPTER CAN BE HOVEREDIGE AT THE INDICATED GROSSWEIGHTS WITH LESS THANTAKEOFF POWER FOR TEMPER.ATURES BELOW 48°C

MAXIMUM GROSS

WEIGHT LIMIT

MAX.

OAT HEATER ON (21°C)

50 60 8 9

11.9

10 11 12 LB X 1000-40-30-20-10 0 10 20

OAT - °C3.5 4.0 4.5 5.0

GROSS WEIGHT5.4 kg X 1000

Figure 4-2. Hover ceiling in ground effect (Sheet 1 of 2)

14,000 FT. DEN. ALT. LIMIT



MAXIMUM CONTINUOUS POWERENG - 100% RPM (N2)GENERATOR 150 AMPS (EA.)

SKID HEIGHT 4 FEETHEATER ON OR OFF

-40 ° TO 52°C

MAX GROSSWEIGHT LIMIT

OAT °COAT0 C

MAX OAT

AX OAT

HEATER ON (21°C)

-40-30-20 -10 0 10 20 30 40 5060 8 9 10 11 12 LBX 1000OAT -°C .

3.5 4.0 4.5 5.0 5.4 kg X 1000GROSS WEIGHT

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

11

HOVER CEILINGOUT OF GROUND EFFECT

TAKEOFF POWER SKID HEIGHT 60 FT.ENG - 100% RPM (N2) HEATER OFFGENERATOR 150 AMPS (EA.) 0 TO 52°C

CAUTION: OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V LIMITATIONS.


AREA A

LIMIT

60 8 9 10 11

3.5 4.0 4.5 5.0GROSS WEIGHT

12 LB X 1000

5.4 kg X 1000

Figure 4-3. Hover ceiling out of ground effect (Sheet 1 of 8)

14,000 FT. DEN. ALT. LIMIT



TAKEOFF POWER SKID HEIGHT 60 FT.ENG - 100% RPM (N2) HEATER OFFGENERATOR 150 AMPS (EA.) -40 TO O°C


-30-20-10 0 8 9 10 11 12 LBX 1000OAT- °C

3.5 4.0 4.5 5.0 5.4 kg X 1000GROSS WEIGHT


13



TAKEOFF POWER SKID HEIGHT 60 FT.ENG - 100% RPM (N2) HEATER ONGENERATOR 150 AMPS (EA.) 0 TO 20°C


TORQUELIMIT

O 10 20 8OAT -C .

3.5

9 10 11

4.0 4.5 5.0GROSS WEIGHT

12 LB X 1000

5.4 kg X 1000


LIMIT



TAKEOFF POWER SKID HEIGHT 60 FT.ENG - 100% RPM (N2) HEATER ONGENERATOR 150 AMPS (EA.) -40 TO 0 ° C


TORQUELIMIT

OAT - °C8 9 10 11 12 LB X 1000

3.5 4.0 4.5 5.0 5.4 kg X 1000GROSS WEIGHT


15



MAXIMUM CONTINUOUS POWER SKID HEIGHT 60 FT.ENG - 100% RPM (N2) HEATER OFFGENERATOR 150 AMPS (EA.) 0 TO 52°C


OAT- °C . . . .3.5 4.0 4.5 5.0 5.26 kg X 1000

GROSS WEIGHT




MAXIMUM CONTINUOUS POWER SKID HEIGHT 60 FT.ENG - 100% RPM (N2) HEATER OFFGENERATOR 150 AMPS (EA.) -40 TO 0° C


14.000 FT DEN. ALT LIMIT

LIMIT _

8 9 10 11

3.5 4.0 4.5 5.0GROSS WEIGHT

-40 -30 -20 -10 0OAT- °C

12 LB X 1000

5.26 kg5.26 kg X 1000


17


MAXIMUM CONTINUOUS POWER SKID HEIGHT 60 FT.ENG - 100% RPM (N2) HEATER ONGENERATOR 150 AMPS (EA.) 0 TO 20°C


0 10 20 8 9 10 11 12 LB X 1000

3.5 4.0 4.5 5.0 5.26 kg X 1000


GROSS WEIGHT


LIMIT



MAXIMUM CONTINUOUS POWER SKID HEIGHT 60 FT.

CAUTION OGE HOVER OPERATION MAY RESULT IN VIOLATION OF H-V LIMITATIONS.

8 9 10 11 12 LBX1000

3.5 4.0 4.5 5.0 5.26 kg X 1000GROSS WEIGHT



TAKEOFF DISTANCEOVER 50 FOOT OBSTACLE

HOVER POWER + 15% TORQUE INITIATED FROM 4 FT SKID HEIGHTENG - 100% RPM IN2) VTOCS = 45 KIASGENERATOR 150 AMPS IEA.) HEATER ON OR OFF

14,000 FT. DEN ALT. LIMIT

-MAX

OAT

AT

MAX OATHEATER ON

(21 -C)

i0-40-20 0 20 40 60 400 600 800 1000 1200 1400

OAT - 'C TAKEOFF DISTANCE - FT.

ENGLISH

Figure 4-4. Takeoff distance (Sheet 1 of 2)


TAKEOFF DISTANCEOVER 15 METER OBSTACLE

HOVER POWER + 15% TORQUEENG - 100% RPM (N2)GENERATOR 150 AMPS (EA.)

INITIATED FROM 1 2 meter SKID HEIGHTVTOCS = 45 KIAS

HEATER ON OR OFF

Figure 4-4. Takeoff distance (Sheet 2 of 2)



TAKEOFF POWER 70 KIAS

GENERATOR 150 AMPS (EA.)

2 RATE OF CLIMB WILL DECREASE



Figure 4-5. Twin engine rate of climb (Sheet 1 of 24)Figure 4-5. Twin engine rate of climb (Sheet 1 of 24)

22


GROSS WEIGHT 7000 LB (3175 kg)TAKEOFF POWER 70 KIASENG - 100% RPM (N2) HEATER ONGENERATOR 150 AMPS (EA.)

WITH ALL DOORS OPEN OR REMOVED CLIMB SPEED IS 60 KIAS2 RATE OF CLIMB WILL DECREASE

275 FT /MIN.

20.000

18.000 ATOAT LIMIT -20°C

30C-40 C


16,000

12.000

10.000

8,000

-6000

-5500

-5000

-4500

I-4000

-3500

- 3000

-2500

- 2000

\

-1500

-1000

-500

6,000

4,000

2,000

0400 800 1200 1600 2000 2400 2800 3200


(2.0) (4.0) (6. .0) (80) (10.0) (12.0) (14.0) (16.0)RATE OF CLIMB - (METERS/SECOND)

Figure 4-5. Twin engine rate of climb (Sheet 2 of 24)

23

20.000


ENG - 100% RPM IN21 HEATER OFF

275 FT. MIN

CAA APPROVED

0

0)

-6000

-1500





TWIN ENGINE RATE OF CLIMBGROSS WEIGHT 8000 LB (3629 kg)

TAKEOFF POWER 70 KIASENG - 100% RPM (N21 HEATER ONGENERATOR 150 AMPS (EA.)

WITH ALL DOORS OPEN OR REMOVED 1 CLIMB SPEED IS 60 KIAS2 RATE OF CLIMB WILL DECREASE

275 FT /MIN



25



TAKEOFF POWER 70 KIASENG - 100% RPM 9N2) HEATER OFFGENERATOR 150 AMPS (EA.)


275 FT /MIN

20.000 60006000

18000 -5500

16000 OAT 5000

-20 C30°C 4500

14,000

-4000 -4000

12,000

10,000 3000-3000

8.000 -2500

OAT LIMIT

0 400 800 1200 1600 2000 2400 2800 3200RATE OF CLIMB - FEET/MINUTE

(0) (2.0) (4.0) (6.0) (8.0) (10.0) (12.0) (14.0) (16.0)


Figurer 4-5. Twin engine rate of Climb (sheet 5 Ot 24)

L

L



70 KIASTAKEOFF POWER

GENERATOR 150AMPS IEA.I


275 FT /MIN

OAT -5500

-5000

-4500cc

-2000 K

-1500

-1000

-500


27

20,000

18,000

16,000

14,000


TWIN ENGINE RATE OF CLIMBGROSS WEIGHT 10.000 LB (4536 kg)

TAKEOFF POWER 70 KIASENG - 100% RPM (N2) HEATER OFFGENERATOR 150 AMPS (EA.)


275 FT /MIN

OAT LIMIT


20.000


TWIN ENGINE RATE OF CLIMBGROSS WEIGHT 10,000 LB 14536 kg)

TAKEOFF POWER 70KIASENG - 100% RPM (N2) HEATER ONGENERATOR 150 AMPS (EA.)


275 FT /MIN

-6000

-5500

-5000

-4500

-5

00 400 800 1200 1600 2000 2400 2800 3200


(0) (2.0) (4.0) (6.0) (8.0) (10.0) (12.0) 14.0) (16.0)


000

00





30

20,000

I


TWIN ENGINE RATE OF CLIMBGROSS WEIGHT 11,000 LB (4990 kg)

TAKEOFF POWER 70 KIASENG - 100% RPM (N2) HEATER ONGENERATOR 150 AMPS (EA.)


275 FT /MIN

(2.0) (4.0) (6.0) (8.0) (10.0) (12.0) (14.0) (16.0)RATE OF CLIMB - (METERS/SECOND)


31


32



GENERATOR 150 AMPS (EA.)

WITH ALL DOORS OPEN OR REMOVED 1 CLIMB SPEED IS 60 KIAS2. RATE OF CLIMB WILL DECREASE

275 FT /MIN

20,000

OAT


33

20.000

18,000

16,000

- 14,000

4.000

2,000

0



MAXIMUM CONTINUOUS POWERENG - 100% RPM (N2)GENERATOR 150 AMPS (EA.)

70 KIASHEATER OFF


275 FT /MIN

-6000

-5500

-5000


34

20,000

18,000

OAT16.000

14.000



MAXIMUM CONTINUOUS POWER 70 KIASENG - 100% RPM (N2) HEATER ONGENERATOR 150 AMPS (EA.)


275 FT /MIN

I

-6000

-5500

-5000

-4500c

-1500


35

20,000

18,000

16,000

14,000

12.000

10,000

8.000

6.000

4,000

2,000



MAXIMUM CONTINUOUS POWER 70 KIASENG - 100% RPM (N2) HEATER OFFGENERATOR 150 AMPS (EA.)


275 FT /MIN

-6000

-5500

-5000

-4500

LU

-4000

-3500

400 800 1200 1600 2000 2400 2800 3200RATE OF CLIMB - FEET/MINUTE


1000

500

0

(0)


20,000

18,000

16,000


TWIN ENGINE RATE OF CLIMBGROSS WEIGHT 8000 LB 13629 kg)

MAXIMUM CONTINUOUS POWERENG - 100% RPM (N21GENERATOR 150 AMPS (EA.)

70 KIASHEATER ON


275 FT /MIN



1500

1000

500


37


MAXIMUM CONTINUOUS POWER 70 KIASENG - 100% RPM (N21 HEATER OFFGENERATOR 150 AMPS (EA.)


275 FT /MIN





20,00



MAXIMUM CONTINUOUS POWER 70 KIASENG - 100% RPM (N2) HEATER ONGENERATOR 150 AMPS IEA.)

WITH ALL DOORS OPEN OR REMOVED 1. CLIMB SPEED IS 60 KIAS2. RATE OF CLIMB WILL DECREASE

275 FT /MIN

00 200 400 600 800 1000 1200 1400 1600




20,000



MAXIMUM CONTINUOUS POWER 70 KIASENG - 100% RPM (N2) HEATER OFFGENERATOR 150 AMPS (EA.)

WITH ALL DOORS OPEN OR REMOVED 1. CLIMB SPEED IS 60 KIAS2. RATE OF CLIMB WILL DECREASE

275 FT /MIN


1000

500


40




WITH ALL DOORS OPEN OR REMOVED 1 CLIMB SPEED IS 60 KIAS2. RATE OF CLIMB WILL DECREASE

275 FT /MIN.




41


TWIN ENGINE RATE OF CLIMB.GROSS WEIGHT 11,000 LB (4990 kg)

MAXIMUM CONTINUOUS POWERENG - 100% RPM IN2)GENERATOR 150 AMPS (EA.)

70 KIASHEATER OFF


275 FT /MIN

20,000

18,000

OAT

- 3000 I


(0) (1.0) (2.0) (3.0) (4.0) (5.0) (6.0) (7.01 (8.0)RATE OF CLIMB - (METERS/SECOND)

1000


42

ILU



MAXIMUM CONTINUOUS POWER 70 KIASENG - 100% RPM IN2) HEATER ONGENERATOR 150 AMPS (EA.)


275 FT /MIN

20,000

18,000




43



MAXIMUM CONTINUOUS POWER 70 KIASENG - 100% RPM IN2) HEATER OFFGENERATOR 150 AMPS (EA.I


275 FT /MIN

(O) (110) (2.0) (3.0) (4.0) (5.0) (6.0) (7.0) (8.0)RATE OF CLIMB - (METERS/SECOND)


44

20.000

18,000





275 FT /MIN.

1000

500


45

20,000

18,000

16,000

14,000LU

12,000


SINGLE ENGINE RATE OF CLIMBGROSS WEIGHT 7000 LB (3175 kg)

MAXIMUM CONTINUOUS POWER 70 KIASENG - 97% RPM (N2) HEATER OFFGENERATOR 150 AMPS INOPERATIVE ENGINE SECURED


275 FT /MIN

-6000

-5500

-5000

-4500


1200


20,000




MAXIMUM CONTINUOUS POWER 70 KIASENG - 97% RPM (N2) HEATER OFFGENERATOR 150 AMPS INOPERATIVE ENGINE SECURED


275 FT /MIN

-6000

-5500

-5000

-4500

- -1500

-1000

-500

1200

(6.0)

47

20.000



MAXIMUM CONTINUOUS POWER 70 KIASENG - 97% RPM (N21 HEATER OFFGENERATOR 150 AMPS INOPERATIVE ENGINE SECURED


275 FT /MIN

-6000

-5500

-5000

-4600

w


800

(4.0)


SINGLE ENGINE RATE OF CLIMBGROSS WEIGHT 10.000 LB (4536 kg)

MAXIMUM CONTINUOUS POWER 70 KIAS



49

20.00

18.00

16.00


SINGLE ENGINE RATE OF CLIMBGROSS WEIGHT 11,000 LB (4990 kg)

MAXIMUM CONTINUOUS POWER 70 KIASENG - 97% RPM (N21 HEATER OFFGENERATOR 150 AMPS INOPERATIVE ENGINE SECURED


275 FT /MIN

-6000

-5500

-5000

-4500

-2000 -1600 -1200 -800 -400 0RATE OF CLIMB - FEET/MINUTE



400

(2.0)

50

20.000

18,000

16,000 TWIN ENGINE M C PABSOLUTE CEILING -

14.000


SINGLE ENGINE RATE OF CLIMBGROSS WEIGHT 11.900 LB (5398 kg)

MAXIMUM CONTINUOUS POWERENG - 97% RPM (N21GENERATOR 150 AMPS

WITH ALL DOORS OPEN OR REMOVED

70 KIASHEATER OFF

INOPERATIVE ENGINE SECURED

1 CLIMB SPEED IS 60 KIAS2 RATE OF CLIMB WILL DECREASE

275 FT /MIN

4000

2000

1000

500

-2000 -1600 -1200 -800 -400RATE OF CLIMB - FEET/MINUTE

(-10.0) (-8.0) (-6.0) (-4.0) (-2.0)


0 400

(0) (2.0)


51

21/2 MINUTE OEIPOWER AS REQUIRED

ENG - 97% RPM (N2)GENERATOR 150 AMPS


SINGLE ENGINE LANDING DISTANCEOVER 50 FT. (15 M) OBSTACLE

Figure 4-7. Single engine landing distance

bht-412-fm-caa

Documents

verify actual

vertical planes

protective

feeder protection

twin engine

steady state

unit weight

single engine