bht-47g-3b-1-fm

BELL MODEL 47G-3B-1

HELICOPTER FLIGHT MANUAL

l

FLIGHT MANUALModel 47G-3B-1

LIST OF REVISED PAGES

RevisionPages

No. Date Revised FAA APPROVED

1 4-5-63 A,C & D2 4-11-63 A,C & D3 4-16-63 A,C & D4 4-22-63 A,C & D5 7-11-63 A,B 14,

24 & 25

6 11-22-63 A, 4 & 15

7 2-3-66 A,C,D, 9& 15

8 5-26-66 A,C, & D

9 12-15-66 A,B,2A,2B,3,4,4A, 14,14A, 19,25

10 2-8-67 A& B

11 3-31-67 A & 15

12 4-7-67 A & 2B

* 13 12-18-68 A,C & D

*NOTE: Revised text is indicated by ablack vertical line A-13

A Revised Dec. 18, 1968


LIST OF REVISED KIT PAGES

Name of Kit Page Date

Main Rotor Blades - NonTip Weighted 1 of 9 4-22-63

thru9 of 9

Take-Off Power, 1 of 2 2-8-67Time Limit Increase

Revised February 8, 1967 B


FAA APPROVED KITS and number of kitspages to be inserted in this manual whenkit is installed.

Name of Kit Pages

Main Rotor Dynamic Stop Assy ......Dual Controls .................Eight Day Clock ................Fire Extinguisher ............. .Night Flying ................ 2.Rotor Brake .................. 1First Aid ....................Narco, VHF Mark V, Radio ........ *100 AMP Generator .............Float Landing Gear .............. 3Cargo Sling .................. 4Heater ...................... 1Main Rotor Blades - Non-Tip Weighted 9Litter Carrier - Stokes ........... 3Take-Off Power, Time Limit

Increase ................... 2 ..AgMaster-Agricultural Sprayer .... 4Combustion Heater .............. 3 .

NOTE: *Flight Manual pages not required.

C Revised Dec. 18, 1968

FLIGHT MANUALModel 47G-3B-

The supplement kit pages, for handbookinsertion contain only the information whichis different from the basic manual.

Kit Number Date

47-120-263 ......... . Jan. 25, 1963. 47-706-609 ............ Jan. 25, 1963. 47-706-620 ............ Jan. 25, 1963

47-706-651 ............ Jan. 25, 1963* 7-706-653 ........... Jan. 25, 1963.47-706-654 ............ Jan. 25, 1963.47-706-656 ............ Jan. 25, 1963.47-706-659 ............ Jan. 25, 1963

. 47-706-637 ............ April 5, 1963.47-706-661 ......... . April 11, 1963.47-706-660 ........ . April 16, 1963.47-706-650 ........... April 16, 1963

.. ..................... April 22, 1963

.. 47-706-663 .......... April 22, 1963

. ..................... ........Feb. 3, 196647-706-686 ........... . May 26, 19667-706-433-1 ......... Dec. 18, 1968

Use Helicopter Serial No. when ordering kits.

Revised Dec. 18, 1968 D


TAIB LE OF

OPERATING LIMITATIONS

Weight Limitation ............... 1Airspeed Limitations ............. 1Altitude Limitations .............. 1Rotor Limitations ............... 2Power Plant Limitations ........... 2Power Operating Limits ........... 3Instrument Markings ............. 4Placards ..................... 5Center of Gravity Limits ........... 6Type of Operation ............... 6Loading Limitations .............. 7

S E C T I O NOPERATING PROCEDURES

Servicing ..................... 9Pre-Engine Starting .............. 9Starting and Fuel System Check ...... 10Warm-Up and Ground Test ......... 11Turbo-Supercharger Function and

Operation ................... 11Engine Power Check ............. 12Engine - Altitude Idle Check ........ 12Manifold Pressure Table ........... 14Engine Shut-Down Procedure ........ 15Hydraulic Boost Failure ........... 16Engine Failure ................. 16Supercharger Malfunction .......... 17Tail Rotor Failure ............... 17Ditching Without Power ............ 17

E


CONTENTS

PERFORMANCE INFORMATION

Performance Information .......... 19Maximum Rate of Climb ........... 20Hovering Ceiling ................ 24Airspeed vs. Altitude Chart ......... 26Airspeed Installation Correction

Table ...................... 27Operation vs. Allowable Wind ....... 27

CHARTS AND TABLES

Temperature Conversion Table ...... 29Velocity Conversion Table ......... 31Standard Atmospheric Table ........ 32Specific Humidity Chart .......... 33Density Altitude Chart ............ 34Helicopter Stations Diagram ........ 35

APPENDIXWeight and Balance Data ......... 37

F


ECTIONOPERATING LIMITATIONS

COMPLIANCE WITH SECTION 1

OF THIS MANUAL IS MANDATORY

WEIGHT LIMITATION.

1. Maximum approved gross weight 2950pounds.

AIRSPEED LIMITATIONS.

Note

All airspeed values given throughoutthis handbook are for CalibratedAirspeed (CAS).

1. Vne 105 MPH, sea level to 10,000 feet.

2. Vne as stated on supplemental kit pageswhen kit is installed.

3. Above 10,000 feet altitude, 3100 RPMminimum.

4. Above 10,000 feet decrease Vne 7 MPHper 1000 feet to 15,000 feet.

5. Above 15,000 feet decrease Vne 5 MPH*per 1000 feet.

ALTITUDE LIMITATIONS.

1. Maximum 20,000 feet.

1


2. Performance is limited by engine coolingcapabilities as shown in performance section.

ROTOR FLIGHT LIMITATIONS.

1. Maximum, 370 RPM.

2. Minimum, 322 RPM.

CAUTION ^

Avoid continuous operation at rotorspeed of 200 to 230 RPM to minimizevibration resonance of the stabilizerbar.

POWER PLANT LIMITATIONS.

LYCOMING ENGINE MODEL: TVO-435-B1.

1. Fuel octane, 100/130 minimum.

2. Fuel pressure, 4 to 8 PSI.

3. Idling RPM, 1500 minimum.

4. Operating RPM,3000to 3200.

5. Manifold pressure, 32.8 in. Hg. S.L.STD. DAY.

6. Compressor pressure 39.0 in. Hg.7. Oil pressure, 50 to 70 PSI

8. Oil temperature 113°C.

9. Cylinder head temperature 246°C.

10. Mixture control, RICH for all poweredflight.

2


POWER PLANT LIMITATIONS.

LYCOMING ENGINE MODEL: TVO-435-D1.

1. Fuel octane, 100/130 minimum.

2. Fuel pressure, 4 to 8 PSI.

3. Idling RPM, 1500 minimum.

4. Operating RPM, 3000 to 3200.

5. Manifold pressure 32.2 in. Hg. Sea LevelSTD. DAY.

6. Compressor pressure 39.0 in. Hg.

7. Oil pressure, 50 to 70 PSI.

8. Oil temperature 113°C.

9. Cylinder head temperature 246°C.

10. Mixture control, RICH for all poweredflight.

Revised December 15, 1966 2A


POWER OPERATING LIMITS.

LYCOMING ENGINE - TVO-435-D1.

COMPRESSOR PRESSURE - 39.0 In. Hg.

MAXIMUM CONTINUOUS POWER - 220 HP

26.6 In. Hg. MAP - S.L. to Full Throttle.

TAKE-OFF POWER - 270 HP. MAX.

5 MINUTE LIMIT BELOW 8000 FEET.2 MINUTE LIMIT ABOVE 8000 FEET.32.2 In. Hg MAP - S.L. to 5000 feet. In-crease MAP 0.2 In. Hg. per 1000 feetabove 5000 feet to critical altitude. Fullthrottle above critical altitude.

POWER CORRECTION FORTEMPERATURE.

For each 10°C Filter Air Temperature(FAT) deviation from Standard AltitudeTemperature correct MAP as follows:

MAXIMUM CONTINUOUS POWER.

Above Standard - Add 0.5 In. MAP.Below Standard - Subtract 0.5 In. MAP.

TAKE-OFF POWER.

Above Standard - Add 0.6 In. MAP.

Note

Cumulative total with altitude andtemperature adjustment 36.0 In.MAP maximum.

Below Standard - Subract 0.6 In. MAP.

2B Revised April 7, 1967


*POWER OPERATING LIMITS.

LYCOMING ENGINE TVO-435-B1.

COMPRESSOR PRESSURE 39.0 In. Hg.

MAXIMUM CONTINUOUS POWER - 220 HP

26.7 in. Hg. MAP- S.L. to 20,000 feet.

TAKE-OFF POWER (2 minute limit) 270 HP.

32.8 in. Hg MAP - S.L. to 8000 feet. In-crease MAP 0.4 in. Hg,per 1000 feetabove 8000 feet to critical altitude. Fullthrottle above critical altitude.

POWER CORRECTION FOR TEMPER-ATURE

For each 10°C Filter Air Temperature(FAT) deviation from Standard AltitudeTemperature correct MAP as follows:

MAXIMUM CONTINUOUS POWER.

Above Standard - Add 0.4 in. MAP.Below Standard - Subtract 0.4 in. MAP.

TAKE-OFF POWER (2 Minute Limit).

Above Standard - Add 0.8 in. MAP.

Note

Cumulative total with altitude andtemperature adjustment 36.0 in. MAPmaximum.

Below Standard - Subtract 0.8 in.MAP.

Revised December 15, 1966 3


TABLE OF INSTRUMENT MARKINGSRotor Yellow Arc 200 to 230 RPMTachometer Red Line 322 RPM

Yellow Arc 322 to 333 RPMGreen Arc 333 to 370 RPMRed Line 370 RPM

Engine Red Line 3000 RPMTachometer Green Arc 3000 to 3200 RPM

Red Line 3200 RPM

Airspeed Red Line 105 MPH

Manifold Green Arc 18.0 to 26.7 In. Hg.Pressure Yellow Arc 26.7 to 32.8 In. Hg.TVO-435-B1 Red Line 32.8 In. Hg.

Comp.Press Red Line 39.0In. Hg.Oil Temp. Green Arc 40 to 130CTransmission Red Line 130C

Oil Temp. Green Arc 40 to 113°CEngine Red Line 113 C

Oil Red Line 50 PSIPressure Green Arc 50 to 70 PSI

Red Line 70 PSI

Fuel Red Line 4 PSIPressure Green Arc 4 to 8 PSI

Red Line 8 PSI

Cylinder Red Line 100°CHead Green Arc 100 to 246°CTemperature Red Line 246°C

Carburetor Yellow Arc -2 ° to +32°CAir Temp.

Filter Air Yellow Arc -10 ° to +10°CTemperatureFuel Qty Red Arc E Radial to lowIndicator end of scale

4 Revised December 15, 1966


TABLE OF INSTRUMENT MARKINGSRotor Yellow Arc 200 to 230 RPMTachometer Red Line 322 RPM

Yellow Arc 322 to 333 RPMGreen Arc 333 to 370 RPMRed Line 370 RPM

Engine Red Line 3000 RPMTachometer Green Arc 3000 to 3200 RPM

Red Line 3200 RPM

Airspeed Red Line 105 MPH

Manifold Green Arc 18.0 to 26.6 In. Hg.Pressure Yellow Arc 26.6 to 32.2 In. Hg.TVO-435-D1 Red Line 32.2 In. Hg.

Comp. Press Red Line 39.0 In. Hg.

Oil Temp. Green Arc 40 to 130°CTransmission Red Line 130°C

Oil Temp. Green Arc 40 to 113°CEngine Red Line 113°C

Oil Red Line 50 PSIPressure Green Arc 50 to 70 PSI

Red Line 70 PSI

Fuel Red Line 4 PSIPressure Green Arc 4 to 8 PSI

Red Line 8 PSI

Cylinder Red Line 100°CHead Green Arc 100 to 246°CTemperature Red Line 246°C

Carburetor Yellow Arc -2 ° to +32°CAir Temp.

Filter Air Yellow Arc -10°to +10°CTemperatureFuel Qty Red Arc E Radial to lowIndicator end of scale

Revised December 15, 1966 4A

PLA

CA

RD

S


CENTER OF GRAVITY LIMITS. 01. 2950 lbs., -3 inches to +2.5 inches.

2. 2300 lbs., -3 inches to +4.0 inches.Straight line variation between above points.

Note

Station 0 is located 2 inches forwardof center line of main rotor mast.

CENTER OF GRAVITY vs.GROSS WEIGHT CHART.

29502900 | (2.5 @ 2950)

v; 2800

- 2700

2500

2400 (4.0 @2300) i2300 I

-3 -2 -1 0 +1 +2 +3 +4INCHES

OPERATIONAL CENTER OF GRAVITY ENVELOPE

TYPE OF OPERATION.

1. Basic configuration of the helicopterpermits its use as a three place aircraft limitedto VFR day operating conditions.

2. Alternate configurations permit the in-stallation and use of approved kits which willallow the helicopter to be utilized for variousspecialized operations. The approved kits whichcan be installed, for utility purposes, are listedon pages C and D for this Flight Manual.

6


LOADING LIMITATIONS.

STANDARD LOADING

Cabin LoadPounds Fuel Gals. External Load

Minimum 150 0 to Full To 2950 Lbs.Total

Maximum 575 0 to Full Gross Weight

ALTERNATE LOADING

CABIN DOORS REMOVED


Minimum 175 0 to Full To 2950 Lbs.Total


WARNING

HELICOPTER WEIGHT EMPTY,FUEL, CABIN LOAD AND EXTER-NAL LOAD SHALL NOT EXCEED2950 LBS. MAXIMUM GROSSWEIGHT.

LOADING RESPONSIBILITY.

It is the responsibility of the owner andpilotto insure safe loading of the helicopter. Theempty weight, empty weight CG and the usefulload are noted on the actual weight and balancesheet included in this manual for the helicopteras delivered from the factory.

7/8


OPERATING PROCEDURES

SERVICING.

1. Fuel, Aviation Grade:Minimum Octane 100/130Usable Fuel 57 U.S. Gallons

WARNING

Red Arc on fuel gage indicates thatfuel remaining in tank when quan-tity indicator reaches EMPTY (topend of Red Arc) is NOT USABLEin flight.

2. Oil, Aviation Grade:

SAE 50 Above 60°F.SAE 40 From 30° to 90°F.SAE 30 From 0° to 70°F.SAE 20 Below 10°F.Tank Capacity 2.5 U.S. Gallons.

PRE-ENGINE STARTING.

1. Flight controls, check for freedom ofmovement, adjust friction.

2. Mixture control, RICH.

3. Carburetor heat control, COLD.

4. Starter vibrator (STR. VIB.) switch,NORMAL.

5. Hydraulic (HYD SYSTEM) switch, ON.

Revised Feb. 3, 1966 9


6. Prime engine - Step a. without primer, astep b. with primer.

a. OPEN and CLOSE throttle ONE toTHREE times cold engine, NO prime hotengine.

b. HOLD FUEL PRIME switch ONONE to THREE seconds cold engine, NO primehot engine.

7. Throttle, CRACKED.

STARTING AND FUEL SYSTEM CHECK.

1. Battery switch, ON.

2. FUEL PUMP switch, ON -FUEL BOOSTFAIL light OUT.

3. Fuel pump pressure, 4 to 5 PSI.

Note

Engine can be started with fuelpump OFF: however, the pump shallbe operated for flight.

4. Ignition switch, BOTH.

5. Starter switch, DEPRESS and HOLD.

6. Fuel pressure after starting, 6.5 to 7.5PSI indicates proper operation of the enginefuel pump.

10


WARM-UP AND GROUND TEST.

1. Idle engine at 1500 to 1700 RPM untiloil pressure reaches 50 PSI minimum.

* 2. Throttle, INCREASE to smoothly ad-vance rotor speed to 167 RPM (1500 engineRPM) then close throttle to fully engage clutch.(Tachometer needles synchronized.)

Avoid continuous operation at rotorspeed of 200 to 230 RPM to mini-mize stabilizer bar resonance. Applysufficient cyclic control into the windto maintain the rotor in a near hori-zontal plane.

3. Increase engine RPM to approximately2300 and hold until oil temperature reaches40°C minimum.

4. Check magnetos at 3200 RPM and mini-mum pitch after head temperature reaches100°C. A drop of 200 RPM is permissible withno engine roughness.

TURBO-SUPERCHARGER FUNCTIONAND OPERATION.

The turbo-supercharger is essentially an airpump that increases the density of the carbu-retor inlet air over a wide range of atmospheric

11


conditions. The supercharger assembly in-corporates a hydraulically powered waste gatecontrol which automatically compensates foraltitude and temperature inlet variations byopening and closing the waste gate. At fullthrottle, this control will provide the requiredamount of supercharging to allow the engine toproduce the approximate take-off power fromsea level to critical altitude for all temper-ature variations. The supercharger compressorpressure will vary from 30 to 40 in. Hg. de-pending upon climatic conditions. At sea levelon a cold day the reading will be low and on ahot day and at altitude the reading will be high.The full throttle normal difference betweencompressor pressure and manifold pressureis approximately 2 in. Hg.

ENGINE POWER CHECK.

After lift off from surface establish an inground effect hovering altitude of approximately2 feet. Check manifold pressure gage and noteNo. 2 COMPressor PRESSure indicator read-ing, then check No. 1 MANifold PRESSure whichis the power required to hover reading. De-termine the actual difference between the tworeadings and subtract the normal difference of2 in. Hg. The pressure reading between theNo. 1 and No. 2 indicators after subtracting thenormal difference is the EXCESS POWERAVAILABLE in In. Hg. MAP.

ENGINE - ALTITUDE IDLE CHECK.

The altitude idle check should be performedprior to accomplishing altitude flights to insure12


against engine stoppage. This is necessary as thesupercharger will not provide the requiredpressure, at low RPM, to maintain the normalfuel-air ratio and therefore the engine will beoperating with a RICH mixture and subject tooverloading and stoppage when the throttle isclosed. Accomplish the check as follows:

1. Operate the helicopter in an In-Ground-Effect hovering altitude, at 3200 RPM, until

* temperatures stabilize.

2. Descend to establish ground contact,maintaining 3200 RPM, by reducing collectivepitch.

3. CLOSE THROTTLE and check engineidle RPM, with no rotor load, for reading of2000 to 2100 idle RPM.

Note

When operating at altitude retardthrottle slowly and maintain approxi-mately 2000 RPM to preclude enginestoppage.

13

MANIFOLD PRESSURE TABLE - 3200 RPM

MAXIMUM CONTINUOUS POWER TAKE-OFF POWER (2 MIN. LIMIT)PRESS FILTER AIR TEMP. °C FILTER AIR TEMP.ALT. FT.

-25 ° - 5 ° +15 ° +35 ° -25 ° - 5 ° +15 ° +35 °

0 25.1 25.9 26.7 27.5 29.6 31.2 32.8 34.42000 25.3 26.1 26.9 29.9 31.5 33.14000 25.4 26.2 27.0 30.2 31.8 33.46000 25.6 26.4 27.2 30.6 32.2 33.88000 25.7 26.5 27.3 30.9 32.5 34.1

10000 25.9 26.7 27.5 32.0 33.6 35.212000 26.1 26.9 33.1 34.7 -- ---14000 26.2 27.0 ---- ---- 34.2 F.T.16000 26.4 27.2 ---- ---- F.T. F.T.18000 26.5 27.3 ---- ---- F.T. F.T.20000 F.T. F.T. ---- ---- F.T. F.T.

NOTE: F.T.: Full Throttle.

TVO-435-D1 MANIFOLD PRESSURE TABLE - 3200 RPM

MAXIMUM CONTINUOUS POWER TAKE-OFF POWER (5 MINUTE LIMIT)

PRESS. FILTER AIR TEMP FILTER AIR TEMP.ALT. FT.

-25 ° 5° +15° +35° -25° - 5° +15° +35°

0 24.6 25.6 26.6 27.6 29.0 31.0 32.2 33.42000 24.8 25.8 26.8 30.0 31.2 32.44000 25.0 26.0 27.0 30.8 31.4 32.66000 25.2 26.2 27.2 30.8 32.0 33.2 ---- -8000 25.4 26.4 27.4 ---- 31.4 32.6 33.6 ---- O a

10000 25.6 26.6 27.6 ---- 32.0 33.2 34.0 --- m12000 25.8 26.8 --- ---- 32.6 33.8 --- ----_14000 26.0 27.0 --- --- 33.2 34.4 ---- .

16000 26.2 27.2 ---- ---- F.T. F.T. --- ----18000 26.4 27.4 _ ---- - F.T. F.T. --- ----20000 F.T. F.T. ---- _--- F.T. F.T. ---- ---

NOTE: Full Throttle.

FLIGHT MANUALModel 47G-33-1

NGINE SHUT-DOWN PROCEDURE.

1. Operate TVO-435-B1 engine at 2200 to2300 RPM for 5 minutes or longer after landingto reduce oil and exhaust temperatures andhereby prolong supercharger service life.

la. Idle TVO-435-D1 engine until cylinderhead temperature drops approximately 25°C.

2. Cyclic control stick, CENTERED orlightly into direction of wind.

3. Engine, stop by moving mixture controlto CUT-OFF.

4. Ignition switch, OFF after engine stops.

Note

When operating under conditions requir-ing frequent battery starts, it is permis-sible to stop the engine by turning theignition switch to OFF. This will de-crease the drain on the battery; however,it must be understood that this proce-dure may result in after firing.

5. Increase main rotor pitch, not to exceed1/3 the range, to reduce rotor RPM.

CAUTION

In high winds increase pitch carefullyand do not exceed 1/3 the pitch range.Apply cyclic control stick into the windto maintain the rotor in a near horizontalattitude.

6. Moor aft blade with mooring block bydrawing down lightly against static stop andtying web strap to tail boom.

Revised March 31, 1967 15


EMERGENCY PROCEDURES

HYDRAULIC BOOST FAILURE.

Hydraulic boost failure will be evident by feed-back forces being transmitted to the cyclicstick when a control motion is made. Feed-back forces may not be present or are negli-gible when the cyclic stick is held fixed orduring autorotation. Feed-back forces en-countered when moving the cyclic stick will beproportionate in intensity to an envelope offactors directly affected by airspeed, grossweight and climatic turbulence. When hydraulicboost power loss is detected, reduce cycliccontrol motions to the minimum required tocomplete the flight and MAKE NECESSARYMOVEMENTS AT A RATE OF TRAVEL NOTFASTER THAN ONE FULL DISPLACEMENT,stop to stop, PER SECOND.

If jamming of the controls or a condition of thecontrols tending to override the pilot is ex-perienced the HYD (hydraulic) SYSTEM switch,located on the instrument panel, should be im-mediately moved to OFF to relieve hydraulicpressure at the cylinders. The jammed cylindermay then be broken loose by exerting pressureon the control stick and the above emergencyprocedure followed.

ENGINE FAILURE.

Execute a normal autorotative descent andestablish a level attitude prior to ground con-tact. At a height of approximately 10 feet

16


pply collective pitch in sufficient quantity tostop descent as ground contact is made.

SUPERCHARGER MALFUNCTION.

Supercharger operation can be monitored by theNo. 2 COMPressor needle on the manifoldpressure gage. A malfunction of the super-charger will immediately be noticeable by eithera HIGH or LOW, No. 2 needle, indication andimmediate action should be initiated as follows:

HIGH COMPRESSOR READING

Throttle - DECREASE to obtainminimumpowerrequired, to avoid exceeding engine limits andthereby permit safe completion of flight.

LOW COMPRESSOR READING

Throttle - INCREASE to offset power loss andto obtain the power required to safely completethe flight.

TAIL ROTOR FAILURE.

1. Immediately initiate an autorotative de-scent and maintain an airspeed of at least 40MPH.

2. Execute a normal autorotative descentand landing.

DITCHING WITHOUT POWER.

1. Execute a normal autorotative descentand establish contact at minimum surface speed.

2. Apply full lateral stick to the RIGHTto roll the helicopter onto the RIGHT side.

17/18


IPERFORMANCE INFORMATION

The Bell Model 47G-3B-1 is a dependable, ver-satile, utility type helicopter with the ability toprovide both low and high altitude performanceover a wide range of climatic conditions. Thisperformance is made possible by the Lycoming IEngine TV0435-B1 or TV0435-D1 with an Air rResearch exhaust driven supercharger. Thiscombination is capable of delivering rated powerat high ambient temperatures and high altitudes.

The performance capabilities of the helicopterunder varying climatic conditions and grossweights are shown on the charts contained in

ehis section. The data listed on the charts iserived from actual flight test and is intended

to provide useful information to be used inconducting flight operations.

Note

Temperature values shown on theperformance charts are for the pres-sure altitudes stated.

Revised December 15, 1966 19

MAXIMUM RATE OF CLIMB FEET PER MINUTE3200 RPM TAKE-OFF POWER (1) MAX. CONT POWER (2) AT 45 MPH

Gross Pressure At At At AtWeight Altitude -25°C - 5C +15°C +35°CPounds Feet -13°F +23°F +59°F +95°F

(1) (2) (1) (2) (1) (2) (1) (2)2450 SL 1200 589 1200 587 1200 593 1200 596

2,000 1200 629 1200 634 1200 6354,000 1200 641 1200 651 1200 659 - -6,000 1200 661 1200 660 1200 660 -8,000 1189 659 1189 660 1189 650

10,000 1200 649 1200 650 1178 65112,000 1200 627 1189 63714,000 1200 593 1132 60116,000 1052 543 931 557 -18,000 754 489 662 45420,000 358

MAXIMUM RATE OF CLIMB FEET PER MINUTE (Cont)3200 RPM TAKE-OFF POWER (1) MAX. CONT POWER (2) AT 45 MPH

Gross Pressure At At At AtWeight Altitude -25°C - 5°C +15C +35°CPounds Feet -13°F +23°F +59°F +95°F

(1) (2) (1) (2) (1) (2) (1) (2)2650 SL 1110 540 1105 533 1098 535 1095 531

2,000 1105 573 1098 572 1095 568 - -4,000 1100 584 1095 583 1090 590 - -6,000 1095 592 1088 590 1085 587 - -8,000 1075 590 1074 587 1069 571 - -

10,000 1084 577 1080 570 1056 565 - - '12,000 1080 550 1065 552 - - -14,000 1075 510 993 507 - - -16,000 917 443 775 414 - - -18,000 602 348 409 228 - - -20,000 125 70

MAXIMUM RATE OF CLIMB FEET PER MINUTE (Cont)3200 RPM TAKE-OFF POWER (1) MAX. CONT POWER (2) AT 45 MPH

Gross Pressure At At At AtWeight Altitude -25°C - 5°C +15°C +35°CPounds Feet -13°F +25°F +59° F +95°F

(1) (2) (1) (2) (1) (2) (1) (2)2850 SL 988 485 982 476 975 472 970 461

2,000 982 511 975 504 970 494 -4,000 978 514 970 509 968 5096,000 970 517 966 509 960 5058,000 952 509 951 504 949 490

10,000 960 493 958 490 931 47512,000 958 471 941 461 -14,000 950 423 841 391 -16,000 768 330 560 23218,000 394 162 79 -20,000

MAXIMUM RATE OF CLIMB FEET PER MINUTE (Cont)3200 RPM TAKE-OFF POWER (1) MAX. CONT POWER (2) At 45 MPH

Gross Pressure At At At AtWeight Altitude -25°C -5°C +15°C +35°CPounds Feet -13 ° F +25° F +59° F +95° F

(1) (2) (1) (2) (1) (2) (1) (2)

2950 SL 912 410 909 403 900 399 895 3862,000 909 436 900 430 895 423 - -4,000 902 -442 895 434 889 435 - -6,000 895 452 888 435 882 435 -8,000 873 436 871 434 867 422 - -

10,000 880 425 875 420 852 409 - -12,000 875 402 861 396 - -- -14,000 870 359 742 30816,000 667 246 375 -18,000 205 ---20,000 -

Co __

HOVERING CEILING - PRESSURE ALTITUDE FT.

OUTSIDE AIR DRY AIR 80% RELATIVE HUMIDITY

Gross Temperature In Ground Out of Ground In Ground Out of GroundWeight °C °F Effect (2) Effect Effect (2) EffectPounds

2450 -45 -49 20,000 * 18,600 20,000 * 18,600-35 -31 20,000 18,300 20,000 18,300-25 -13 19,680 17,900 19,680 17,900-15 + 5 19,320 17,450 19,320 17,450

5 +23 18,970 16,950 18,910 16,950+ 5 +41 - 16,400 - U 16,350

2650 -40 -40 19,180 17,200 19,180 17,200c=, -30 -22 18,800 16,700 18,800 16,700

20 -4 18,410 16,100 18,410 16,100-10 +14 17,990 15,500 17,990 15,500

0 +32 17,500 14,800 17,410 14,800_O +10 +50- 14,050 - | 13,950

0@..

HOVERING CEILING - PRESSURE ALTITUDE FT. (Cont)

2850 -35 -31 17,900 15,400 17,900 15,400-25 -13 17,390 14,600 17,390 14,600-15 + 5 16,820 13,700 16,820 13,700

5 +23 16,210 12,800 16,180 12,8005 +41 15,590 11,800 15,490 11,700

+15 +59 10,800 10,450

2950 -30 -22 16,940 12,750 16,940 12,750-20 - 4 16,300 11,900 16,300 11,900-10 +14 15,690 11,000 15,690 11,000

0 +32 15,000 10,000 15,000 9,950+10 +50 - 8,950 - 8,600+20 +68 - 7,900 7,200

NOTE: (1) Data based on 3200 RPM and Take-Off Power(2) In Ground Effect Hovering based on 2 foot skid height.

40- - - --0 ROSS WEIGHT -2950 LBS -J400 ALT. - SEA LEVEL

ROTOR RPM - 355

300 /////// AVOID CONTINUOUS OPERATION300 IN SHADED AREA

AL T UDEFEETI TIII ' -1il: -F200 I I II -

n\ THIS REGION SAFE OVER

100 SMOOTH LANDING SURFACE ONLY

0 20 40 60 80 100M P.H.

0 0 0


AIRSPEED INSTALLATION CORRECTIONTABLE.

BASIC CONFIGURATION

* Model 47G-3B-1

Indicated Air Speed (IAS) corrected for posi-tion and instrument error equals CalibratedAir Speed (CAS). Determine Corrected IASfrom the following table:

IAS CAS

20 MPH 22.5 MPH25 MPH 26.0 MPH30 MPH 30.5 MPH35 MPH 35.0 MPH40 MPH 40.0 MPH45 MPH 44.5 MPH50 MPH 49.5 MPH60 MPH 58.0 MPH70 MPH 67.0 MPH80 MPH 76.0 MPH90 MPH 86.0 MPH

100 MPH 95.5 MPH105 MPH 100.5 MPH110 MPH 105.0 MPH

OPERATION vs. ALLOWABLE WIND

Helicopter flight and landing operations can besafely accomplished with wind conditions up to20 MPH: however, this is not to be considereda limiting value as maximum operating windvelocities have not been established.

27/28


ECTIONCHARTS AND TABLES

INTRODUCTION

The charts and tables contained in this sectionprovide information and conversion data usefulto the operator, for purposes of transposinginformation to the type desired.

TEMPERATURE CONVERSION

TABLE

°F °C °F °C

-85 -65 -54-76 -60 -51-67 -55 -48-58 -50 -46-49 -45 -43-40 -40 -40-31 -35 -37-22 -30 -34-13 -25 -32- 4 -20 -29

5 -15 -2614 -10 -2323 - 5 -2132 0 -1841 5 -1550 10 -12

29


TEMPERATURE CONVERSION

TABLE (Cont.)

°F C F °C

59 15 - 9

68 20 - 777 25 - 486 30 - 195 35 2

104 40 4113 45 7122 50 10131 55 13

140 60 16149 65 18158 70 21

167 75 24

176 80 27185 85 29194 90 32203 95 35212 100 38221 105 41230 110 43239 115 46248 120 49257 125 52266 130 55275 135 57284 140 60293 145 63302 150 66311 155 68320 160 71329 165 74

30

* -FLIGHT MANUALModel 47G-3b-1

VELOCITY CONVERSIONTABLE

Knots MPH Knots MPH

0 0 0

4 5 6

9 10 12

13 15 17

17 20 23

22 25 2926 30 3530 35 4035 40 4639 45 5243 50 5848 55 6352 60 6956 65 75

61 70 81

65 75 8669 80 9274 85 98

78 90 10482 95 11087 100 11591 105 12195 110 127

100 115 132104 120 138108 125 144113 130 150117 135 155122 140 161126 145 167130 150 173

31


STANDARD ATMOSPHERICTABLE

Pressure Standard AtmosphericAltitude Temperature Pressure

Feet °F °C Inches Hg

0 59.0 15.0 29.921,000 55.4 13.0 28.862,000 51.9 11.0 27.823,000 48.3 9.1 26.814,000 44.7 7.1 25.845,000 41.2 5.1 24.896,000 37.6 3.1 23.987,000 34.0 1.1 23.098,000 30.5 - 0.8 22.229,000 26.9 - 2.8 21.38

10,000 23.3 - 4.8 20.5811,000 19.8 - 6.8 19.7912,000 16.2 - 8.8 19.0313,000 12.6 -10.8 18.2914,000 9.1 -12.7 17.5715,000 5.5 -14.7 16.8816,000 1.9 -16.7 16.2117,000 - 1.6 -18.7 15.5618,000 - 5.2 -20.7 14.9419,000 - 8.8 -22.6 14.3320,000 -12.3 -24.6 13.7521,000 -15.9 -26.6 13.1922,000 -19.5 -28.6 12.6323,000 -23.0 -30.6 12.1024,000 -26.6 -32.5 11.5925,000 -30.2 -34.5 11.1026,000 -33.7 -36.5 10.6227,000 -37.3 -38.5 10.16

32


DENSITY ALTITUDE CHART

34

NOTE: STATION - Centerine of weld cluster Just for d of levelinglugs 2 inches forward of center lne of mast) Leveling lugon lower left-hond longeron aft of most

I >

30275

76.25 31.0 0 31.0

2 265.753

I -" =I II"II ==1 ! el am / =1 ...


APPENDIX

37/38

FLIGHT MANUAL

Model 47G-3B-1

EQUIPMENT Date: April 22, 1963FAA APPROVED

MAIN ROTOR BLADES - NON TIP WEIGHTED

INTRODUCTION

The non-tip weighted main rotor blades are ap-proved for an alternate blade installation andphysical interchangeability with the tip-weightedblades can be easily accomplished. With the al-ernate blades installed the helicopter is limited

to 2850 pounds gross weight and 260 HP for take-off. However, the maximum continuous powerwill remain unchanged.

SECTION 1 OPERATING LIMITATIONS

WEIGHT LIMITATION

1. Maximum approved gross weight 2850pounds.

POWER PLANT LIMITATIONS

LYCOMING ENGINE - TVO-435-B1

5. Manifold pressure, 31.4 In. Hg. sea levelstandard day.

POWER OPERATING LIMITS


31.4 In. Hg. MAP - S.L. to 9,000 feet. IncreaseMAP 0.4 In. Hg. per 1,000 feet above 9,000 feetto critical altitude. Full throttle above criticalaltitude.

Revised December 15, 1966 Page 1 of 9




POWER PLANT LIMITATIONS

LYCOMING ENGINE - TVO-435-D1

5. Manifold pressure, 31.1 In.Hg. sea levelstandard day.



31.1 In. Hg. MAP - S.L. to 5,000 feet. IncreaseMAP 0.4 In. Hg. per 1,000 feet above 5,000 feetto critical altitude. Full throttle above criticalaltitude.


TABLE OF INSTRUMENT MARKINGS

Change Manifold Pressure gage markings toread as follows:

Green Arc - 18.0 to 26.7 In. Hg.Yellow Arc - 26.7 to 31.4 In. Hg.Red Line - 31.4 In. Hg.



EQUIPMENT Date: April 22, 1963VUPMET FAA APPROVED



LYCOMING ENGINE - TVO-435-D1

TABLE OF INSTRUMENT MARKINGS

hange Manifold Pressure gage markings toread as follows:

Green Arc - 18.0 to 26.6 In. Hg.Yellow Arc - 26.6 to 31.1 In. Hg.Red Line - 31.1 In. Hg.

CENTER OF GRAVITY LIMITS

1. 2850 pounds, -3 inches to +3.2 inches.

CENTER OF GRAVITY vs GROSS WEIGHTCHART

2800 AX GROSS T. 2850 LBS.

2600

2400 F- FORWARD C.G LIMIT

2200220 AFT C.G LIMIT

2000 -

1E,, Ill-3 -2 0 *1 2 3 +4

HELICOPTER STATION, INCHES





SECTION 1 (Cont)

LOADING LIMITATIONS

STANDARD LOADING


Minimum 150 0 to Full To 2850 lbs.Total


ALTERNATE LOADING

CABIN DOORS REMOVED


Minimum 175 0 to Full To 2850 lbs.Total


WARNING

HELICOPTER WEIGHT EMPTY, FUEL,CABINLOAD AND EXTERNAL LOAD SHALL NOT EX-CEED 2850 LBS. MAXIMUM GROSS WEIGHT.






SECTION 2 OPERATING PROCEDURES

MANIFOLD PRESSURE TABLE

The Take-Off Power Manifold Pressure Limitsto be used when the alternate non-tip weightedmain rotor blades are installed are as follows:


PRESS TAKE-OFF POWER (2 MIN. LIMIT)

ALT. FT. FILTER AIR TEMP °C

-25" -5 ° 15 ° 35 °

0 28.0 29.6 31.2 32.82,000 28.3 29.9 31.54,000 28.7 30.3 31.96,000 29.0 30.6 32.28,000 29.3 30.9 32.5

10,000 30.1 31.6 33.212,000 31.1 32.714,000 32.2 33.816,000 F.T. F.T. -18,000 F.T. F.T. -20,000 F.T. F.T.

NOTE: F.T. = Full Throttle





SECTION 2 (Cont)

LYCOMING ENGINE TVO-435-D1


The Take-Off Power Manifold Pressure Limitsto be used when the alternate non-tip weightedmain rotor blades are installed as follows:


PRESS TAKE-OFF POWER (5 MIN.LIMIT

ALT. FT. FILTER AIR TEMP °C-25 - 5 +15 +35

0 28.7 29.9 31.1 32.32000 28.9 30.1 31.34000 29.1 30.3 31.56000 29.6 30.8 32.0 -8000 30.1 31.3 32.5

10000 30.6 31.8 33.012000 31.1 32.314000 31.6 32.816000 F.T. F.T.18000 F.T. F.T.20000 F.T. F.T. -

(Take-Off Power ForNon-Tip Weighted Rotor)

NOTE: F.T. = Full Throttle


FLIGHT MANHUALFLIGHT MANUALModel 47G-3B-1



SECTION 3 PERFORMANCE INFORMATION

The MAXIMUM RATE of CLIMB in FEET PERMINUTE for TAKE-OFF POWER (column (1) )when the non-tip weighted main rotor bladesare installed is as follows:





SECTION 3 (Cont)MAXIMUM RATE OF CLIMB - FEET PER MINUTE

3200 RPM TAKE-OFF POWER (1) AT 45 MPH

GROSS PRESS At At At AtWT. ALT. -25C - 5°C +15°C +35°C

LBS. FT. -13°F +23°F +59°F +95°F

(1) (1) (1) (1)2450 0 1092 1092 1092 1092

2,000 1092 1092 1092 -4,000 1092 1092 1092 -6,000 1092 1092 1092 -8,000 1092 1092 1092

10,000 1092 1092 1092 -12,000 1087 1087 - -14,000 1082 1116 -16,000 1014 953 - -18,000 684 640 - -20,000 336 - - -

2650 0 1010 1005 998 9952,000 1005 998 995 -4,000 1000 995 990 -6,000 995 988 985 -8,000 985 984 979 -

10,000 984 980 976 -12,000 976 970 - -14,000 965 978 - -16,000 882 795 - -18,000 537 389 - -20,000 105 - - -

2850 0 895 889 882 8772,000 889 882 877 -4,000 885 877 875 -6,000 877 873 867 -8,000 869 868 866 -

10,000 867 865 857 -12,000 861 853 - -14,000 848 827 - -16,000 736 578 - -18,000 334 61 - -20,000





* SECTION 3 (Cont)

HOVERING CEILING - PRESSURE ALTITUDE - FT*

GROSS TEMPER 80% RELATIVEWT. ATURE DRY AIR HUMIDITY

POUNDSPC IGE** OGE IGE** OGE

2450 -45 20,000 18,350 20,000 18,350-35 20,000 17,950 20,000 17,950-25 19,520 17,550 19,530 17,550-15 19,160 17,180 19,160 17,180- 5 18,780 16,730 18,700 16,690

5 - -

2650 -40 19,020 17,000 19,020 17,000-30 18,600 16,460 18,600 16,460-20 18,150 15,900 18,150 15,900-10 17,700 15,470 17,650 15,470

0 17,250 14,910 17,150 14,84010 - - -

2850 -35 17,600 14,100 17,600 14,100-25 17,150 13,190 17,150 13,190-15 16,650 12,290 16,650 12,290

5 16,150 11,390 16,100 11,3905 15,500 10,440 15,500 10,310

15 9,460 - 9,000

NOTE: *Data Based on 3200 RPM and Take-Off Power with260 H.P. Limit

**In-Ground Effect Hovering Based on 2 Foot SkidHeight



EQUIPMENT Date: Jan. 25, 1963FAA APPROVED

NIGHT FLYING.

* The Night Flying Kit No. 47-706-653 consistsof a ground adjustable landing light, two rotatinganti-collision beacon lights, navigation lights,cockpit lights, instrument lights, electricalcables, circuit breaker switches and the re-quired hardware. Installation of the kit will per-mit night flying operations when ground contactflight conditions can be maintained. The beaconlights will provide a significant increase in theconspicuity of the helicopter, which is especiallydesirable due to the continued increase in airtraffic density, and are now required by thecurrent Civil Air Regulations.



Actual weight change shall be determined afterkit is installed and ballast readjusted, if nec-essary, to return empty weight CG within allow-able limits.

NIGHT FLIGHT LIMITATIONS.

Night flight operation is limited to visual con-tact flight conditions. Orientation shallbe main-tained through visual reference to ground ob-jects solely as a result of lights on the groundor adequate celestial illumination.

Page 1 of 2


EQUIPMENT Date: Jan. 25, 1953FAA APPROVED

NIGHT FLYING.

SECTION 1 (Cont)

OPERATION.

Turn beacon light OFF during flight in or nearvisible moisture to prevent uncommon re-flections and possible pilot vertigo.

NOTE

Keep cabin glass clean to preventhalation. Limit operation of beaconlights on the ground, to prolong bulblife and to avoid mistaken identityas an emergency ground vehiclewhich uses a similar light.


NIGHT FLIGHT.

This helicopter has not been demonstrated tocomply with the handling standards for instru-ment flight.

Page 2 of 2


EQUIPMENT Date: Jan. 25,1963FAA APPROVED

ROTOR BRAKE

INTRODUCTION

The Bell Rotor Brake Kit, No. 47-706-654,consists of a tube expander type rotor brakeassembly, pressure reducer valve, checkvalve,brake cylinder, operating control handle andthe required tubing, hoses, fittings and attach-ing hardware. Installation of the rotor brakepermits rapid deceleration of the rotor afterengine shut-down.



Actual weight change shall be determined afterkit is installed and ballast readjusted, if nec-essary, to return empty weight CG to withinallowable limits.


ENGINE SHUT-DOWN PROCEDURE

5A. Apply rotor brake after rotor speedhas decreased to 100 RPM.

Page 1 of 1



FLOAT LANDING GEAR

INTRODUCTION

The Bell Float Landing Gear Kit, No. 47-706-661, consists of two multi-cell type inflatablefloats, float mounting tubes, mounting crosstubes, spoilers, attachment fittings and all hard-ware required to equip the helicopter for wateroperation. The spoilers, 47-706-212, mountednear the forward end of the float mounting tubesmust be installed for all flight operations. Oper-ation with floats is approved with or without thenight flying kit; however, when equipped withnight flying equipment a new landing light shieldshall be installed to prevent landing light reflec-tions, from the forward end of the floats.



1. Vne 90 MPH (78 knots) sea level to 5000feet.

2. Above 5000 feet altitude, 3100 RPMminimum, decrease Vne three MPH (2.6 knots)per 1000 feet.

Page 1 of 3


EQUIPMENT Date: April 11,1963FAA APPROVED

FLOAT LANDING GEAR

ALTITUDE LIMITATIONS

1. Maximum, 15,000 feet.


Actual weight change shall be determined afterkit is installed and ballast readjusted, if nec-essary, to return empty weight CG within allow-able limits.


SERVICING

FLOAT PRESSURE

1. BASE ALTITUDE - Float pressure 1.5PSI.

2. FLIGHT TO LOWER ALTITUDE - In-crease pressure 0.5 PSI per 1000 feet BELOWbase altitude, to minimum operating altitude.

3. FLIGHT TO HIGHER ALTITUDE- Limitclimbing flight to 10,000 feet differential pres-sure altitude, ABOVE 10,000 differential altitudeREDUCE float pressure 0.5 PSI per 1000 feet.

Page 2 of 3


EQUIPMENT Date: April 11,1963AA APPROVED

FLOAT LANDING GEAR

WARM-UP AND GROUND TEST

CAUTION

Anchor or moor helicopter priorto starting the engine to prevent ro-tating, due to torque, before the tailrotor reaches effective RPM.

TAXIING

Taxi at slow speed to prevent float bows fromnosing under.

NOTE

Safe operation can be accomplishedin waves up to 18 inches (trough tocrest) and 360° turns can be executedin winds up to 20 MPH.

SECTION 3 PERFORMANCE DATA

RATE OF CLIMB

Reduce basic MAXIMUM RATE OF CLIMBperformance data 70 FEET, PER MINUTEwhen operating with Float Landing Gear.

Page 3 of 3

FLIGHT MANUALModel 47 G-3B-1

EQUIPMENT Date: April 16, 1963FAA APPROVED UNDER

CAR PART 8

CARGO SLING

INTRODUCTION

The Bell Cargo Sling Kit No. 47-706-660 wheninstalled will provide a method of carrying ex-ternal cargo. The sling is attached to the centerframe near the helicopter cg and is capable ofcarrying the maximum payload pounds allowablewith the helicopter automatic touch-down, elec-trical manual and (emergency) mechanical man-ual release features. The kit contains the cargosuspension assembly, mounting brackets andshackles, center frame mounted stop assem-blies mechanical release control and cable,electrical switches, circuit breaker, wiring andall hardware and parts necessary for a com-plete installation OPERATIONS with cargo onthe sling SHALL BE CONDUCTED INACCORD-ANCE WITH CIVIL AIR REGULATIONS PART 8.

NOTE

A swivel link is not supplied with theCargo Sling Kit; however, it is recom-mended that a link be installed'be-tween the suspension cable and thecargo hook.


AIRSPEED LIMITATIONS

Extreme caution should be exercised whencarrying cargo loads as controllability may beaffected, due to the size and shape of the cargoload.

Page 1 of 4


EQUIPMENT Date: April 16, 1963FAA APPROVED UNDER

CAR PART 8

CARGO SLING

SECTION 1 (Cont)


Actual weight change shall be determined afterkit is installed and ballast readjusted, if neces-sary, to return empty weight cgwithin allowablelimits.

AREA OPERATING LIMITS

Operations shall not be conducted over denselypopulated areas, in congested air lanes, or inthe vicinity of busy airports where passengertransport operations are being conducted with-out the Approval of the Local FAA Administra-tor wo will prescribe the Specific OperatingLimitations.

ECONOMIC OPERATING LIMITATIONS.

Persons and cargo shall not be carried forkcompensation or hire in restricted category air- Wcraft. For purposes of explanation crop dusting,seeding and other specialized operations, includ-ing the carriage of materials necessary for suchoperations, shall not be considered as the car-riage of persons or cargo for compensation orhire.PASSENGERS PROHIBITED DURINGSPECIAL PURPOSE OPERATIONS.

Persons other than the minimum crew neces-sary for the purpose involved shall not becarried during special purpose operations inrestricted category aircraft.

Page 2 of 4


EQUIPMENT Date: April 16, 1963oW~ FAA APPROVED UNDERCAR PART 8

CARGO SLING

SECTION 1 (Cont)

MULTIPLE AIRWORTHINESS OPERATION

Operation of the helicopter is authorized underCAR PART 6 when cargo is not being carriedand the sling is secured to the forward controlguard. With cargo attached to the sling opera-tion shall be conducted in accordance with CARPART 8. Installation or removal of the slingis considered a minor alteration and can beaccomplished by a certified mechanic withappropriate airframe rating who will deter-mine the airworthiness of the helicopter.


OPERATION.

1. ACTIVATE circuit by pushing CARGORELEASE circuit breaker IN.

2. POSITION, instrument panel, CARGORELEASE switch to SAFE (off) when attachingcargo, then MOVE switch to MANUAL orAUTO, as desired, after cargo is attachedand hook is locked.

Page 3 of 4


EQUIPMENT Date: April 16, 1963FAA APPROVED UNDER@

CAR PART 8

CARGO SLING

SECTION (Cont)

OPERATION (Cont)

NOTE

When cargo release switch is posi-tioned at AUTO cargo canbe releasedby the electric manual switch or bytouchdown; however, a cargo mini-mum weight of 125 pounds is re-quired for automatic operation ofthe cargo hook.

3. PULL mechanical manual release con-trol HANDLE to drop cargo in the event of anelectrical failure.

NOTE

Mechanical release will function re-gardless of CARGORELEASE switchposition

Page 4 of 4



CABIN HEATER

a^& INTRODUCTION

The Bell Cabin Heater Kit, No. 47-706-650,provides heated air to the cabin and utilizes thedissipated heat from the engine oil cooler. Thekit consists of an oil cooler mounted collector,nose, by-pass valve, plenum chamber, adjust-able air outlet valves, heater ON or BY-PASScontrol and the required parts and hardware tocomplete the installation. Pressurized air forheater operation is derived from the enginecooling fan; therefore, heat is always availablewhen the heat control handle is in the UP posi-tion and by-passed overboard when the handle isDOWN.


PLACARDS

WARNING-HEATER OPERATION FORALL FLIGHTS UNDER 10 MPH HEAT-ED AIR MUST BE BY-PASSED OVER-BOARD. (Control handle down.)


Actual weight change shall be determined afterkit is installed and ballast readjusted, if neces-sary, to return empty weight CG within allow-able limits.

OPERATION

Above 77°F (25°C) OAT remove the collectorfrom the oil cooler, to prevent excessive engineoil temperature.

Page 1 of 1



LITTER CARRIERS - STOKES

INTRODUCTION

The Bell-Litter Carrier Kit, No. 47-706-663, isapproved for use with the skid or float type land-ing gear. The kit consists of two Stokes litterswhich are mounted on the landing gear crosstubes, one on each side of the helicopter, andall attachment fittings, supports and hardwarerequired to complete the installation.

SECTION 1 OPERATING LIMITATION


1. Vne 90 MPH sea level to 5000 feet.

2. Above 5000 feet altitude, decrease Vnethree (3) MPH (2.6 knots) per 1000 feet.

ALTITUDE LIMITATIONS

1. Maximum, 15,000 feet.


Actual weight change shall be determined afterthe kit is installed and ballast relocated, if nec-essary, to return empty weight CG to within al-lowable fore and aft and lateral limits.

Page 1 of 3


EQUIPMENT Date: April 11 1963FAA APPROVED


SECTION 1 (Cont)

EMPTY WEIGHT CENTER OF GRAVITYCHART.

190 IMOST AFT

TAIL HEAVY

NOSE HEAVYWEIGHT EMPTY C.G., INCHES AFT OF STA. ZERO

The empty weight CG lateral moment of theskid or float equipped helicopter, with StokesLitters installed, SHALL BE WITHIN 500 inch-pounds right as viewed facing forward.

OPERATION

1. Pilot shall be located to the left.

2. Asymmetric litter loading shallbeontheright.

Page 2 of 3




SECTION 1 (Cont)

LOADING LIMITATIONS

1. Maximum allowable weight in cabin, 400pounds with either one or both litters occupied.

2. The approved capacity of each litter is225 pounds.

ASYMMETRIC LOADING LIMITATIONS

1. With pilot ONLY the right-hand litterload SHALL NOT EXCEED the pilot's weightby more than 30 pounds.

2. Pilot plus center seat loading of 105pounds or more will permit right-hand litter tobe loaded to litter capacity.


* RATE OF CLIMB

Reduce basic MAXIMUM RATE OF CLIMB per-formance data 70 FEET PER MINUTE, for floator skid gear equipped helicopters, when oper-ating with the litters installed.

Page 3 of 3


QUIPMENT Date: February 3, 1966FAA APPROVED

TAKE-OFF POWER, TIME LIMIT INCREASE

INTRODUCTION

The time limit for use of TAKE-OFF POWERcan be increased from the present 2 minutelimit to a 5 minute limit when the 47-620-600-

7 transmission is installed in the Model 47G-B-1 helicopter.


NOTE

The 47-620-600-27 transmission isa mandatory requirement whenTAKE-OFF POWER is to be usedfor periods in excess of 2 minutes.

Take-Off Power (5 minute limit) 270 HP.Take-off power use is limited to the take-offand climb-out phases of flight and shall not besed for sustained level flight.


TAKE-OFF POWER (5 minute limit) 270Hp.

POWER CORRECTION FOR TEMPERATURE

TAKE-OFF POWER (5 minute limit).

Revised February 8, 1967 Page 1 of 2

FLIGHT MANUALModel 47G-3G-1

EQUIPMENT Date: February 3, 1966FAA APPROVED

TAKE-OFF POWER, TIME LIMIT INCREASE



TAKE-OFF POWER (5 minute limit).

NO CHANGE IN MANIFOLD PRESSUREVALUES

Page 2 of 2


EQUIPMENT Date: May 26, 1966FAA APPROVED

MgMASTER-AGRICULTURAL SPRAYER

INTRODUCTION

The Bell AgMASTER Agricultural Spray Kit,No. 47-706-686 is designed for rapid installationand removal. The two hopper tanks are con-structed of corrosion resistant fiberglas andhave a structural capacity of 600 pounds pertank. The system crossfeeds the spray liquidbetween the two tanks therefore servicing ofthe system can be accomplished from eithertank.

SECTION I OPERATING LIMITATIONS


1. Vne 80 MPH (69 knots) sea level to10,000 feet, with spray equipmentinstalled.

2. Above 10,000 feet decrease Vne 5 MPH(4 knots) per 1000 feet.

3. Spraying at airspeed below 15 MPH (13knots) is prohibited.

4. Spraying while hovering or in sidewardor rearward flight is prohibited.

ALTITUDE LIMITATIONS.

Maximum Altitude, 15,000 feet.

Page 1 of 4



AgMASTER-AGRICULTURAL SPRAYER

SECTION 1 (Cont)

WARNING

The use of spray liquids having aflash point lower than kerosene isprohibited.


1. Take-off power, two minute limit.

2. Supplement for TAKE-OFF POWER,TIME LIMIT INCREASE shall not be usedwith spray equipment installed.

PLACARDS

T.O. POWER - 2 MIN. LIMITWITH SPRAYER INSTALLED


1. Forward: 3.0 inches forward of Sta-tion 0.

2. Aft: 2.5 inches aft of Station 0.

3. No variation with Gross Weight.

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

Page 2 of 4



AgMASTER- AGRICULTURAL SPRAYER

SECTION 1 (Cont)

TYPE OF OPERATION

1. Flight operations, with spray equipmentinstalled, is limited to VFR day conditions.

2. Operation under FAR PART 27 (former-ly CAR PART 6) is approved with spray equip-ment installed and system DRY (tanks empty).

3. Operation with the spray system WET(Spray liquid in tanks) shall be conducted inaccordance with FAR PART 137.

LOADING LIMITATIONS

Cabin Loading: 185 pounds minimumNo change maximum


SPRAY OPERATION

1. Sprayer CLUTCH and VALVE circuitbreakers, IN.

2. Sprayer pump CLUTCH switch, ON.

for 3. Spray VALVE switch, OPEN and HOLDfor release of spray liquid.

4. Spray VALVE switch, CLOSE and mom-entarily HOLD to stop spray liquid flow.

Page 3 of 4



AgMASTER-AGRICULTURAL SPRAYER

SECTION 2 (Cont)

EMERGENCY OPERATION

DUMP-OFF-CLUTCH switch, LIFT switchguard and move switch to DUMP to jettisonspray liquid from tanks.


The basic Flight Manual, Maximum Rate ofClimb performance data shall be reduced by150 FEET PER MINUTE, when the spray kitis installed.

Page 4 of 4


EQUIPMENT Date: December 18, 1968FAA APPROVED

COMBUSTION HEATER

INTRODUCTION

Combustion Heater Kit, 47-706-433-1, consistsof a Janitrol combustion type heater rated at25,000 BTU, blower and housing, heat distri-butors and controls, exhaust outlet, thermostatcontrol, fuel regulator and shut-off valve,heater starting switch, blower ON and OFFswitch, overheat warning light, ducts, fireshut-off control, electrical wiring and attachinghardware. Heat is distributed into cabinthrough ducts to individually controlled rotatingdistributors for defrosting bubble or heatingcabin. Temperature is controlled by rotatingthe thermostat control, located on box beam.Heater start switch, blower switch and over-heat warning light are located on the instru-ment panel. A push-pull control for fire shut-off valve is mounted on box beam and shouldbe operated only in case of heater fire ormalfunction of heater.


Actual weight change shall be determined afterkit is Installed and ballast readjusted, if nec-essary, to return empty weight C.G. withinallowable limits.

PLACARDS

WARNING - HEATER OPERATIONFOR ALL FLIGHT UNDER 10KNOTS HEATER MUST BE "OFF".

Page 1 of 3


EQUIPMENT Date: December 18, 1968FAA APPROVEDV

COMBUSTION HEATER (Contd)


NOTE

This restriction is imposed toprevent carbon monoxide fromentering cabin.


STARTING HEATER

1. HTR PWR circuit breaker ON.

2. HTR CONT circuit breaker ON.

3. BATTery switch ON.

4. Heater fail light, press in to test light.

5. Firewall shut-off release knob IN.

6. Heater/Blower switch in HTR position.

7. Move heater start switch to HTR posi-tion and HOLD for approximately 10 secondsthen release it.

8. Turn thermostat control to desiredtemperature.

NOTE

Heater fail light should ILLUMI-NATE before heater starts and goOUT after heater ignites.

Page 2 of 3


EQUIPMENT Date: December 18, 1968FAA APPROVED

COMBUSTION HEATER (Contd)


SHUT-OFF HEATER

1. HTR/BLO (heater/blower) switch OFF*position.

2. HTR/BLO (heater/blower) switch BLOposition, allow several minutes to cool andpurge heater unit, then turn switch OFF.

3. HTR/PWR circuit breaker OFF.

4. HTR/CONT circuit breaker OFF.

5. BATTery switch OFF.

EMERGENCY PROCEDURE

*In case of HEATER FIRE "PULL UP" controlfor FIRE SHUT-OFF valve and set HTR/BLO(heater/blower) switch to "OFF" position.

NOTE

To obtain outside air into cabin setHTR/BLO (heater/blower) switch toBLO position.

Page 3 of 3

FLIGHT MANUALExternal Loads Supplement

Models 47G-2, 2A, 2A-1, 3, 3B, 3B-1, 4

EQUIPMENT Date: June 18, 1965FAA APPROVED

CARGO SLING

INTRODUCTION

The Bell Cargo Sling Kit, No. 47- 706- 660 when in-stalled, will permit the owner or operator, with avalid Rotorcraft External Load Operator Certifi-ate, to utilize the helicopter for transportation of

xternal cargo, for compensation or hire, whenoperated by a qualified pilot.

The information contained in this supplement ispresented with the prime intent of furnishing im-portant data that can be used in the RotorcraftLoad Combination Flight Manual. The Combina-tion Flight Manual, required by FAR 133, willbe prepared by the applicant, obtaining theRotorcraft External Load Operator Certificate,and submitted to the FAA for approval.

The cargo sling kit incorporates automatic touch-gown, electrical manual and (emergency) me-chanical manual cargo release features.


ATTENTION

This helicopter meets the structuraland design requirements of CARPART 6 (New No. FAR PART 27):providing the data contained in thissupplement are included in and im-posed by the Combination FlightManual.

Page 1 of 5


Models 47G-2, 2A, 2A-1, 3. 3B, 3B-1, 4


CARGO SLING

SECTION 1 (Cont)

WEIGHT LIMITATIONS

Gross Weight not to exceed maximum allowablefor the basic helicopter.


Limited by controllability. Caution should beexercised as handling characteristics may beaffected due to the size and shape of the cargoload. (Establish airspeed during Flight demon-stration.)

PLACARDS

Make placard stating Approved Load Class(es)and Occupancy Limitation and conspicuously adisplay in the cabin.

Make placard stating - External Load Limit1000 LBS and install on or next to the cargoattaching hook.

NOTE

1000 pounds is the allowable LoadingLimit on the Cargo Sling.

Page 2 of 5

* -


Models 47G-2, 2A, 2A-1, 3, 3B, 3B-1, 4


CARGO SLING

SECTION 1 (Cont)

CENTER OF GRAVITY

The CG of the Cargo Sling when installed islocated at station plus 2.0, which is the ofthe main rotor mast.

Actual weight change should be determined afterkit is installed and ballast readjusted, if neces-sary to return empty weight CG within allowablelimits.

TYPE OF OPERATION

The helicopter meets the airworthiness require-ments of FAR 133, for Class (state class(es))rotorcraft load combinations with external cargoloads up to 1000 pounds and total gross weightnot to exceed the maximum allowable for thebasic helicopter.

Operation under CAR PART 6 (New No. FARPART 27) can be conducted with the cargo slinginstalled: Providing cargo is not being trans-ported and the sling is secured to the forwardcontrol guard.

Page 3 of 5


Models 47G-2, 2A, 2A-1, 3, 3B, 3B-1, 4


CARGO SLING


STATIC ELECTRICITY DISCHARGE

Provide ground crew with instructions as fol-lows: Discharge helicopter static electricity,before attaching cargo, by touching the airframewith a ground wire or if a metal sling is used,the hook-up ring can be struck against thecargo hook. If contact has been lost after initialgrounding the helicopter should be electricallyregrounded and, if possible, contact maintaineduntil hook-up is completed.

CARGO SLING OPERATION

Check CARGO RELEASE circuit breaker IN.

Position, instrument panel, CARGO RELEASEswitch to SAFE (off) when attaching cargo, thenMOVE switch to MANUAL or AUTO, as de-sired, after cargo is attached rnd hook is locked.

NOTE

When the CARGO RELEASE switchis positioned at AUTO, cargo can bereleased by the electrical manualswitch or by touch-down; however, acargo minimum weight of 125poundsis required for automatic operationof the cargo hook.

Page 4 of 5


Models 47G-2, 2A, 2A-1, 3, 3B, 3B-1, 4

* EQUIPMENT Date: June 18, 1965FAA APPROVED

CARGO SLING

SECTION 2

OPERATING PROCEDURES (Cont)

PULL mechanical manual release lever HANDLEto drop cargo in the event of an electricalfailure.

NOTE

The cargo mechanical release willfunction regardless of position ofthe CARGO RELEASE switch.

Page 5 of 5

bht-47g-3b-1-fm

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